59
" . .... .' . . AMC PAMPHLET AMCP 706·140 THIS IS A REPRINT WITHOUT CHANGE OF OROP ZO·UO RESEARCH AND DEVELOPMENT OF MATERIEL . ENGINEERING DESIGN HANDBOOK TRAJECTORIES, DIFFERENTIAL EFFECTS, AND DATA FOR PROJECTILES i r",. -" . ! ,. j HEADQUARTERS. U. S. ARMY MATERIEL COMMAND AUGUST 1963

AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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Page 1: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

AMC PAMPHLET AMCP 706middot140 THIS IS A REPRINT WITHOUT CHANGE OF OROP ZOmiddotUO

RESEARCH AND DEVELOPMENT OF MATERIEL

ENGINEERING DESIGN HANDBOOK

TRAJECTORIES DIFFERENTIAL EFFECTS AND DATA FOR PROJECTILES

i r -

j

HEADQUARTERS U S ARMY MATERIEL COMMAND AUGUST 1963

HEADQUARTERS UNITED STATES ARMY MATERIEL COMMAND

WASHINGTON 25 D C

30 August 1963

AMCP 706-140 Trajectories Differential Effects and Data for Projectiles forming part of the Army Materiel Command Engineering Design Handbook Series is published for the information and guidance of all concerned

SELWYN D SMITH JR Brigadier General USA Chief of Staff

OFFICIAL

R O DAV Colonel G Chief Adm nistrative Office

DISTRIBUTION Special

d

PREFACE This pamphlet one of the series which will c gtmprise the Ordnance Engineerin~

Design Handbook deals with the subjpct of Exterior Ballistics covering Trashy

jectories Differential Effects and Data for Projectiles The pamphlet pertains

to that phase of projectile life starting at the gun muzzle (or for a rocket at

burnout) and ending at the point of burst or impact The subject is covered in a

manner intended primarily to assist the ammunition designer in recognizing and

dealing with the design parameters of projectile weight shape Inuzzle velocity yaw

c drag and stability in designing for optimum results in range time of flight and

accuracy It is hoped that it will also prove helpful to other personnel of the Ordshy

nance Corps and of contractors to the Ordnance Corps Because of its complexity

it is possible to cover the subject only briefly in this volume but an attempt has been

made t~ incorporate references which will permit the designer or the student to

explore in more detail any phase of the subject

The bal1istics of bombs and of intermediate and long range missiles are not

covered in this pamphlet Neither are the problems associated with Interior

Bal1istics or of Terminal Ballistics These subjects will be covered by other

pamphlets

TABLE OF CONTENTS PAGE

PREFACE bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull

SVMBOLS iv

1 INTRODUCTION TO EXTERIOR BLLISTICS bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull

2 VACUUM TRAJECTORIES bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 1 a Equations of Motion 1 b Charact~ristics of Trajectori~s 2

3 AIR RESISTANCE bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 2 a Fortts Acting on a Missil~ Moving in Air 2

(1) Drag bull 2 (2) Crosswind Fortt 2 (3) Magnus middotForce 2

b Simplified Assumptions 2 c Drag Coefficient 2 d Drag Function bull 3 e Form Factor bullbull 3 f Ballistic Coefficimt 4 g Air Igtensity 4

)

4 DESCRIPTION OF TVPICAL PROJECTILES bullbullbull bullbullbullbullbullbullbullbull bullbullbullbullbull bullbullbullbullbullbull 4 a Proj~cti1e Type 1 4 b Projectile Ty~ 2 bull 5 c Proj~il~ Type 8 5 d HEAT Shdl 9O-mm TIOB 5

5 TRAJECTORIES IN AIR bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 5 a Equations of Motion 5 b Charact~ristics of Trajectori~s 5

( 1) Ballistic Tabl~s 5 (2) Graphs 8

6 SIACCI TABLES bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 9 a Spin-Stabilized Projectil~s 9

( I) Tabular Functions 9 (2) Ground Fire at Low EI~vations 9

(a) Formulas bull 9 (b) Example 10

(3) Antiaircraft Fir~ bullbull 10 (a) Formulas bull 10 (b) Exampl~bull 11

ii

--

-

shy

----

TABLE OF CONTENTS (continued) PAGF

(4) Aircraft Fire II (a) Formulas II (b) Example 13

(c) Interpolation _ 13

b Fin-Stabilized Projectiles 14

(I) Tabular Functions 14

(2) Appliltation 14 (a) Formulas 14 (b) Example 15

7 DJPmiddotERENTJAL EFFECTS 15

a Effects on Range 15 (I) Height of Target 15 (2) Elevation 16 (J) Muzzle Velocity 16 ( 4) Ballistic Coefficient 16 (5) Weight of Projectile 16 (6) Air Density 16 (7) Air Temperature 16 (8) Wind 17

h Effects on Igteflection 17 (I) Wind 17 (2) Drift 17

c Ballistic Density Temperature and Wind 17

REFERENCES bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull 18

GLOSSARy bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 19

TABLES

I Maximum Range for Projectile Type 1 67 II Maximum Range for Projectile Type 2 bull 7

III Maximum Range for Projectile Type 8 8

FIGURES

1 Projectile Shapes 21 2 Drag Coefficient vs Mach Number 22 J Time of Flight for Projectile Type 1 23 4 Time of Flight for Projectile Type 2 24 5 Time of Flight for Projectile Type 8 25 6 Trajectory Chart for Projectile Type 2 (12 graphs) 26 to 37 7 Trajectory Chart for Projectile Type 8 (12 graphs) J8 to 49

iii

SYMBOLS A-Azimuth measured from the direction of moshy

tion of the airplane (in aircraft fire)

A-Altitude function (Eq 63)

A-Axial moment of inertia

B-Drag coefficient in Ibjin2-ft (Eq 19)

C-Ballistic coefficient (Eq 22)

D-Drag

D-Angular deflection

F-Temperature in degrees Fahrenheit

G-Drag function (Eq 20)

H-Ratio of air density at altitude y to that at the surface (Eq 48)

H-Height of target

I-Inclination function (Eq 62)

K-Coefficient (See Eq 16 and 34)

L-erosswind force (lift)

M-Mach number (Eq 18)

M-Pseudo-Mach numbeT (Eq 65)

M-Overtumin~ moment about the center of gravity

M-log1oe=O43429 ~ approx)

N-Spin

P-Performance parameter (Eq Z7) P-Siacci range the distance ~sured along the

line of departure to a point directly above the projectile (Eq S4)

Q-Drop of the projectile (Eq SS)

R-Reynolds number (Eq 17)

R-Range

S-Space function (Eq 60)

T-Total time of flight

T-Time function (Eq 61)

V-Upper limit of integration of Siacci functions

V-Velocity

W-Wind speed

X-Total range of a trajectory

Y-Altitude of an airplane above sea level

Z-Linlar deflection

Z-Zenith angle

1--Velocity of sound

niameter of the largest cros~ section of the projectile (in Gbre drag law Eq 23)

c-Damping coefficient due to yawing moment lnd crosswind force (Eq 51)

c--Damping coefficient due to drag (Eq 33)

d-Caliber Or maximum diameter of projectile

f--Drag coefficient (in the Gavre drag law Fq bull 23)

g-Gravitational acceleration

h-Logarithmic rate of decrease of air density with altitude 000003158 per ft

h-Yawing moment damping factor

i-Form factor (Eq 21)

k-Logarithmic rate of decrease of sonic velocity with altitude 000000301 per ft _-shyk--Ratio of American to French drag function (Eq 24)

01-lass of the projectile

m-Slope of the tangent to the trajectory

n-logarithmic rate of change of muzzle velocity with projectile weight

p-Space function (Eq 28)

p-Projectile weight

ql-Indination fttlll~tion (Ell 30)

q-Altitude function (Eq 31)

s-Stability factor

t-Time of fli~ht (sometints the symld t is used to distinguish the time of flight from the Siald time function)

t-Time function (Eq 29)

u-Velocity of the projectile relative to the air

u-Component along the line of departure of the velocity relative to the air the argument of the Siacci functions

v-Velocity of the projectile relative to an inertial system

iv

I

w-True air speed of the airplane in aircraft fire

x-Horizontal distance from the origin of the trajectory

y-Vertical distance Irom the origin of the trashyjectory

I-Drift ~ (capital delta) or ~-Incnment of (foUowed

by a variable)

6-Density of air (in Givre dng law Eq 23)

T (gamma)-Factor inversely proportioaaI to the ballistic coefficient (Eq (6)

a (delta)-Yaw

(epsilon)-Angle of aite (Eq 72)

(theta)-Angle of indinatioa of the trajectory 1t (bppa)-Crosswind force damping factor

1amp (mu)-VilCOsity of the air

p (rho)-Density of the air

or (tau)-Temperature of the air

(phi)-Angle of departure

(omep)Angle of fall

Swsms One dot (example xl-Derivative with respect

to time

Two dots (example y)-Secoad derivative with respect to time

Stlbsm o-At t = 0 Y= 0 or a=o

I-Pertaining to or relative to Projectile Type I

2-Pertaining to or relative to Projectile Type Z

8-Pertaining to or relative to Projectile Type 8

I-First reviaion

2-Second revision

C-Due to I increase in ballistic coefficient

D-Drag

H-Due to height of target

R-Range component of

e-Effective

p-Due to projectile weight

s-Summital at the summit of a trajectory where

y=o s-Standard pertaining to standard conditions

t-Pertaining to or relative to some Typical Proshyjectile

v-Due to I unit increase in muzzle velocity

w-Due to wind

z-Cross component of

a-Yaw

or-Due to increase in the temperature of the atmosphere

t-Due to an increase in angle of departure

Ill-Terminal where y = 0 on the descending branch of the trajectory

v

r

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

middot15

N

N

10

KD

15

bull10

-1

~(

tT

l

---r~

--1

-I

I I

i 1

-

_~

1-

---+p~~-~r+1

i-H

i -

~

bull

tf-1t

iMtH

-++J

=

-~

rr~

---

+T~

i~~

TTT

shy

1-1-

1-++

-

-shy

-~

00

0

5 LO

15

2

0 u

10

1

5

40

4

5 aD

M

aCH

N

O

Fig

ure

l

Dra

g C

oef

fici

ent

VII

M

ach

Nu

mb

er

)

100 + ~

t f~ 11 +-lt

1 +

j -

~ 10 j

i+

t H-t-+

-+t~~ bull ~~i

10 I

~t-H

~

~ lrit-l ~fl70 -~

eo ~ I

i ~50 ~ III

~

40

30

20

10

2 8 8 LO r2

t 1-1-

-1 -i T l I 7 -~J- i-

I

LOG Cg

Figure 3 Time of Flight for Projectile Type 1

--~ i

110

140

120

--- --

80

40

20

o -04 -02 o 2 A 8 10

LOG C

Figure 4 Time of Flight for Projectile Type Z

Z4

I

i 100 o

10

-l-+--

H

eo

- shy

40

20

I

o -002 o 02 4 oS 08 10

180

120 ampl

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

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AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 2: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

HEADQUARTERS UNITED STATES ARMY MATERIEL COMMAND

WASHINGTON 25 D C

30 August 1963

AMCP 706-140 Trajectories Differential Effects and Data for Projectiles forming part of the Army Materiel Command Engineering Design Handbook Series is published for the information and guidance of all concerned

SELWYN D SMITH JR Brigadier General USA Chief of Staff

OFFICIAL

R O DAV Colonel G Chief Adm nistrative Office

DISTRIBUTION Special

d

PREFACE This pamphlet one of the series which will c gtmprise the Ordnance Engineerin~

Design Handbook deals with the subjpct of Exterior Ballistics covering Trashy

jectories Differential Effects and Data for Projectiles The pamphlet pertains

to that phase of projectile life starting at the gun muzzle (or for a rocket at

burnout) and ending at the point of burst or impact The subject is covered in a

manner intended primarily to assist the ammunition designer in recognizing and

dealing with the design parameters of projectile weight shape Inuzzle velocity yaw

c drag and stability in designing for optimum results in range time of flight and

accuracy It is hoped that it will also prove helpful to other personnel of the Ordshy

nance Corps and of contractors to the Ordnance Corps Because of its complexity

it is possible to cover the subject only briefly in this volume but an attempt has been

made t~ incorporate references which will permit the designer or the student to

explore in more detail any phase of the subject

The bal1istics of bombs and of intermediate and long range missiles are not

covered in this pamphlet Neither are the problems associated with Interior

Bal1istics or of Terminal Ballistics These subjects will be covered by other

pamphlets

TABLE OF CONTENTS PAGE

PREFACE bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull

SVMBOLS iv

1 INTRODUCTION TO EXTERIOR BLLISTICS bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull

2 VACUUM TRAJECTORIES bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 1 a Equations of Motion 1 b Charact~ristics of Trajectori~s 2

3 AIR RESISTANCE bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 2 a Fortts Acting on a Missil~ Moving in Air 2

(1) Drag bull 2 (2) Crosswind Fortt 2 (3) Magnus middotForce 2

b Simplified Assumptions 2 c Drag Coefficient 2 d Drag Function bull 3 e Form Factor bullbull 3 f Ballistic Coefficimt 4 g Air Igtensity 4

)

4 DESCRIPTION OF TVPICAL PROJECTILES bullbullbull bullbullbullbullbullbullbullbull bullbullbullbullbull bullbullbullbullbullbull 4 a Proj~cti1e Type 1 4 b Projectile Ty~ 2 bull 5 c Proj~il~ Type 8 5 d HEAT Shdl 9O-mm TIOB 5

5 TRAJECTORIES IN AIR bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 5 a Equations of Motion 5 b Charact~ristics of Trajectori~s 5

( 1) Ballistic Tabl~s 5 (2) Graphs 8

6 SIACCI TABLES bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 9 a Spin-Stabilized Projectil~s 9

( I) Tabular Functions 9 (2) Ground Fire at Low EI~vations 9

(a) Formulas bull 9 (b) Example 10

(3) Antiaircraft Fir~ bullbull 10 (a) Formulas bull 10 (b) Exampl~bull 11

ii

--

-

shy

----

TABLE OF CONTENTS (continued) PAGF

(4) Aircraft Fire II (a) Formulas II (b) Example 13

(c) Interpolation _ 13

b Fin-Stabilized Projectiles 14

(I) Tabular Functions 14

(2) Appliltation 14 (a) Formulas 14 (b) Example 15

7 DJPmiddotERENTJAL EFFECTS 15

a Effects on Range 15 (I) Height of Target 15 (2) Elevation 16 (J) Muzzle Velocity 16 ( 4) Ballistic Coefficient 16 (5) Weight of Projectile 16 (6) Air Density 16 (7) Air Temperature 16 (8) Wind 17

h Effects on Igteflection 17 (I) Wind 17 (2) Drift 17

c Ballistic Density Temperature and Wind 17

REFERENCES bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull 18

GLOSSARy bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 19

TABLES

I Maximum Range for Projectile Type 1 67 II Maximum Range for Projectile Type 2 bull 7

III Maximum Range for Projectile Type 8 8

FIGURES

1 Projectile Shapes 21 2 Drag Coefficient vs Mach Number 22 J Time of Flight for Projectile Type 1 23 4 Time of Flight for Projectile Type 2 24 5 Time of Flight for Projectile Type 8 25 6 Trajectory Chart for Projectile Type 2 (12 graphs) 26 to 37 7 Trajectory Chart for Projectile Type 8 (12 graphs) J8 to 49

iii

SYMBOLS A-Azimuth measured from the direction of moshy

tion of the airplane (in aircraft fire)

A-Altitude function (Eq 63)

A-Axial moment of inertia

B-Drag coefficient in Ibjin2-ft (Eq 19)

C-Ballistic coefficient (Eq 22)

D-Drag

D-Angular deflection

F-Temperature in degrees Fahrenheit

G-Drag function (Eq 20)

H-Ratio of air density at altitude y to that at the surface (Eq 48)

H-Height of target

I-Inclination function (Eq 62)

K-Coefficient (See Eq 16 and 34)

L-erosswind force (lift)

M-Mach number (Eq 18)

M-Pseudo-Mach numbeT (Eq 65)

M-Overtumin~ moment about the center of gravity

M-log1oe=O43429 ~ approx)

N-Spin

P-Performance parameter (Eq Z7) P-Siacci range the distance ~sured along the

line of departure to a point directly above the projectile (Eq S4)

Q-Drop of the projectile (Eq SS)

R-Reynolds number (Eq 17)

R-Range

S-Space function (Eq 60)

T-Total time of flight

T-Time function (Eq 61)

V-Upper limit of integration of Siacci functions

V-Velocity

W-Wind speed

X-Total range of a trajectory

Y-Altitude of an airplane above sea level

Z-Linlar deflection

Z-Zenith angle

1--Velocity of sound

niameter of the largest cros~ section of the projectile (in Gbre drag law Eq 23)

c-Damping coefficient due to yawing moment lnd crosswind force (Eq 51)

c--Damping coefficient due to drag (Eq 33)

d-Caliber Or maximum diameter of projectile

f--Drag coefficient (in the Gavre drag law Fq bull 23)

g-Gravitational acceleration

h-Logarithmic rate of decrease of air density with altitude 000003158 per ft

h-Yawing moment damping factor

i-Form factor (Eq 21)

k-Logarithmic rate of decrease of sonic velocity with altitude 000000301 per ft _-shyk--Ratio of American to French drag function (Eq 24)

01-lass of the projectile

m-Slope of the tangent to the trajectory

n-logarithmic rate of change of muzzle velocity with projectile weight

p-Space function (Eq 28)

p-Projectile weight

ql-Indination fttlll~tion (Ell 30)

q-Altitude function (Eq 31)

s-Stability factor

t-Time of fli~ht (sometints the symld t is used to distinguish the time of flight from the Siald time function)

t-Time function (Eq 29)

u-Velocity of the projectile relative to the air

u-Component along the line of departure of the velocity relative to the air the argument of the Siacci functions

v-Velocity of the projectile relative to an inertial system

iv

I

w-True air speed of the airplane in aircraft fire

x-Horizontal distance from the origin of the trajectory

y-Vertical distance Irom the origin of the trashyjectory

I-Drift ~ (capital delta) or ~-Incnment of (foUowed

by a variable)

6-Density of air (in Givre dng law Eq 23)

T (gamma)-Factor inversely proportioaaI to the ballistic coefficient (Eq (6)

a (delta)-Yaw

(epsilon)-Angle of aite (Eq 72)

(theta)-Angle of indinatioa of the trajectory 1t (bppa)-Crosswind force damping factor

1amp (mu)-VilCOsity of the air

p (rho)-Density of the air

or (tau)-Temperature of the air

(phi)-Angle of departure

(omep)Angle of fall

Swsms One dot (example xl-Derivative with respect

to time

Two dots (example y)-Secoad derivative with respect to time

Stlbsm o-At t = 0 Y= 0 or a=o

I-Pertaining to or relative to Projectile Type I

2-Pertaining to or relative to Projectile Type Z

8-Pertaining to or relative to Projectile Type 8

I-First reviaion

2-Second revision

C-Due to I increase in ballistic coefficient

D-Drag

H-Due to height of target

R-Range component of

e-Effective

p-Due to projectile weight

s-Summital at the summit of a trajectory where

y=o s-Standard pertaining to standard conditions

t-Pertaining to or relative to some Typical Proshyjectile

v-Due to I unit increase in muzzle velocity

w-Due to wind

z-Cross component of

a-Yaw

or-Due to increase in the temperature of the atmosphere

t-Due to an increase in angle of departure

Ill-Terminal where y = 0 on the descending branch of the trajectory

v

r

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 3: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

d

PREFACE This pamphlet one of the series which will c gtmprise the Ordnance Engineerin~

Design Handbook deals with the subjpct of Exterior Ballistics covering Trashy

jectories Differential Effects and Data for Projectiles The pamphlet pertains

to that phase of projectile life starting at the gun muzzle (or for a rocket at

burnout) and ending at the point of burst or impact The subject is covered in a

manner intended primarily to assist the ammunition designer in recognizing and

dealing with the design parameters of projectile weight shape Inuzzle velocity yaw

c drag and stability in designing for optimum results in range time of flight and

accuracy It is hoped that it will also prove helpful to other personnel of the Ordshy

nance Corps and of contractors to the Ordnance Corps Because of its complexity

it is possible to cover the subject only briefly in this volume but an attempt has been

made t~ incorporate references which will permit the designer or the student to

explore in more detail any phase of the subject

The bal1istics of bombs and of intermediate and long range missiles are not

covered in this pamphlet Neither are the problems associated with Interior

Bal1istics or of Terminal Ballistics These subjects will be covered by other

pamphlets

TABLE OF CONTENTS PAGE

PREFACE bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull

SVMBOLS iv

1 INTRODUCTION TO EXTERIOR BLLISTICS bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull

2 VACUUM TRAJECTORIES bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 1 a Equations of Motion 1 b Charact~ristics of Trajectori~s 2

3 AIR RESISTANCE bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 2 a Fortts Acting on a Missil~ Moving in Air 2

(1) Drag bull 2 (2) Crosswind Fortt 2 (3) Magnus middotForce 2

b Simplified Assumptions 2 c Drag Coefficient 2 d Drag Function bull 3 e Form Factor bullbull 3 f Ballistic Coefficimt 4 g Air Igtensity 4

)

4 DESCRIPTION OF TVPICAL PROJECTILES bullbullbull bullbullbullbullbullbullbullbull bullbullbullbullbull bullbullbullbullbullbull 4 a Proj~cti1e Type 1 4 b Projectile Ty~ 2 bull 5 c Proj~il~ Type 8 5 d HEAT Shdl 9O-mm TIOB 5

5 TRAJECTORIES IN AIR bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 5 a Equations of Motion 5 b Charact~ristics of Trajectori~s 5

( 1) Ballistic Tabl~s 5 (2) Graphs 8

6 SIACCI TABLES bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 9 a Spin-Stabilized Projectil~s 9

( I) Tabular Functions 9 (2) Ground Fire at Low EI~vations 9

(a) Formulas bull 9 (b) Example 10

(3) Antiaircraft Fir~ bullbull 10 (a) Formulas bull 10 (b) Exampl~bull 11

ii

--

-

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----

TABLE OF CONTENTS (continued) PAGF

(4) Aircraft Fire II (a) Formulas II (b) Example 13

(c) Interpolation _ 13

b Fin-Stabilized Projectiles 14

(I) Tabular Functions 14

(2) Appliltation 14 (a) Formulas 14 (b) Example 15

7 DJPmiddotERENTJAL EFFECTS 15

a Effects on Range 15 (I) Height of Target 15 (2) Elevation 16 (J) Muzzle Velocity 16 ( 4) Ballistic Coefficient 16 (5) Weight of Projectile 16 (6) Air Density 16 (7) Air Temperature 16 (8) Wind 17

h Effects on Igteflection 17 (I) Wind 17 (2) Drift 17

c Ballistic Density Temperature and Wind 17

REFERENCES bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull 18

GLOSSARy bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 19

TABLES

I Maximum Range for Projectile Type 1 67 II Maximum Range for Projectile Type 2 bull 7

III Maximum Range for Projectile Type 8 8

FIGURES

1 Projectile Shapes 21 2 Drag Coefficient vs Mach Number 22 J Time of Flight for Projectile Type 1 23 4 Time of Flight for Projectile Type 2 24 5 Time of Flight for Projectile Type 8 25 6 Trajectory Chart for Projectile Type 2 (12 graphs) 26 to 37 7 Trajectory Chart for Projectile Type 8 (12 graphs) J8 to 49

iii

SYMBOLS A-Azimuth measured from the direction of moshy

tion of the airplane (in aircraft fire)

A-Altitude function (Eq 63)

A-Axial moment of inertia

B-Drag coefficient in Ibjin2-ft (Eq 19)

C-Ballistic coefficient (Eq 22)

D-Drag

D-Angular deflection

F-Temperature in degrees Fahrenheit

G-Drag function (Eq 20)

H-Ratio of air density at altitude y to that at the surface (Eq 48)

H-Height of target

I-Inclination function (Eq 62)

K-Coefficient (See Eq 16 and 34)

L-erosswind force (lift)

M-Mach number (Eq 18)

M-Pseudo-Mach numbeT (Eq 65)

M-Overtumin~ moment about the center of gravity

M-log1oe=O43429 ~ approx)

N-Spin

P-Performance parameter (Eq Z7) P-Siacci range the distance ~sured along the

line of departure to a point directly above the projectile (Eq S4)

Q-Drop of the projectile (Eq SS)

R-Reynolds number (Eq 17)

R-Range

S-Space function (Eq 60)

T-Total time of flight

T-Time function (Eq 61)

V-Upper limit of integration of Siacci functions

V-Velocity

W-Wind speed

X-Total range of a trajectory

Y-Altitude of an airplane above sea level

Z-Linlar deflection

Z-Zenith angle

1--Velocity of sound

niameter of the largest cros~ section of the projectile (in Gbre drag law Eq 23)

c-Damping coefficient due to yawing moment lnd crosswind force (Eq 51)

c--Damping coefficient due to drag (Eq 33)

d-Caliber Or maximum diameter of projectile

f--Drag coefficient (in the Gavre drag law Fq bull 23)

g-Gravitational acceleration

h-Logarithmic rate of decrease of air density with altitude 000003158 per ft

h-Yawing moment damping factor

i-Form factor (Eq 21)

k-Logarithmic rate of decrease of sonic velocity with altitude 000000301 per ft _-shyk--Ratio of American to French drag function (Eq 24)

01-lass of the projectile

m-Slope of the tangent to the trajectory

n-logarithmic rate of change of muzzle velocity with projectile weight

p-Space function (Eq 28)

p-Projectile weight

ql-Indination fttlll~tion (Ell 30)

q-Altitude function (Eq 31)

s-Stability factor

t-Time of fli~ht (sometints the symld t is used to distinguish the time of flight from the Siald time function)

t-Time function (Eq 29)

u-Velocity of the projectile relative to the air

u-Component along the line of departure of the velocity relative to the air the argument of the Siacci functions

v-Velocity of the projectile relative to an inertial system

iv

I

w-True air speed of the airplane in aircraft fire

x-Horizontal distance from the origin of the trajectory

y-Vertical distance Irom the origin of the trashyjectory

I-Drift ~ (capital delta) or ~-Incnment of (foUowed

by a variable)

6-Density of air (in Givre dng law Eq 23)

T (gamma)-Factor inversely proportioaaI to the ballistic coefficient (Eq (6)

a (delta)-Yaw

(epsilon)-Angle of aite (Eq 72)

(theta)-Angle of indinatioa of the trajectory 1t (bppa)-Crosswind force damping factor

1amp (mu)-VilCOsity of the air

p (rho)-Density of the air

or (tau)-Temperature of the air

(phi)-Angle of departure

(omep)Angle of fall

Swsms One dot (example xl-Derivative with respect

to time

Two dots (example y)-Secoad derivative with respect to time

Stlbsm o-At t = 0 Y= 0 or a=o

I-Pertaining to or relative to Projectile Type I

2-Pertaining to or relative to Projectile Type Z

8-Pertaining to or relative to Projectile Type 8

I-First reviaion

2-Second revision

C-Due to I increase in ballistic coefficient

D-Drag

H-Due to height of target

R-Range component of

e-Effective

p-Due to projectile weight

s-Summital at the summit of a trajectory where

y=o s-Standard pertaining to standard conditions

t-Pertaining to or relative to some Typical Proshyjectile

v-Due to I unit increase in muzzle velocity

w-Due to wind

z-Cross component of

a-Yaw

or-Due to increase in the temperature of the atmosphere

t-Due to an increase in angle of departure

Ill-Terminal where y = 0 on the descending branch of the trajectory

v

r

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

middot15

N

N

10

KD

15

bull10

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~(

tT

l

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I I

i 1

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i ~50 ~ III

~

40

30

20

10

2 8 8 LO r2

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-1 -i T l I 7 -~J- i-

I

LOG Cg

Figure 3 Time of Flight for Projectile Type 1

--~ i

110

140

120

--- --

80

40

20

o -04 -02 o 2 A 8 10

LOG C

Figure 4 Time of Flight for Projectile Type Z

Z4

I

i 100 o

10

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40

20

I

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180

120 ampl

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Figure 5 Time of Flight i)r Ptojectile Typa 8

zs

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 4: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

TABLE OF CONTENTS PAGE

PREFACE bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull

SVMBOLS iv

1 INTRODUCTION TO EXTERIOR BLLISTICS bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull

2 VACUUM TRAJECTORIES bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 1 a Equations of Motion 1 b Charact~ristics of Trajectori~s 2

3 AIR RESISTANCE bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 2 a Fortts Acting on a Missil~ Moving in Air 2

(1) Drag bull 2 (2) Crosswind Fortt 2 (3) Magnus middotForce 2

b Simplified Assumptions 2 c Drag Coefficient 2 d Drag Function bull 3 e Form Factor bullbull 3 f Ballistic Coefficimt 4 g Air Igtensity 4

)

4 DESCRIPTION OF TVPICAL PROJECTILES bullbullbull bullbullbullbullbullbullbullbull bullbullbullbullbull bullbullbullbullbullbull 4 a Proj~cti1e Type 1 4 b Projectile Ty~ 2 bull 5 c Proj~il~ Type 8 5 d HEAT Shdl 9O-mm TIOB 5

5 TRAJECTORIES IN AIR bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 5 a Equations of Motion 5 b Charact~ristics of Trajectori~s 5

( 1) Ballistic Tabl~s 5 (2) Graphs 8

6 SIACCI TABLES bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 9 a Spin-Stabilized Projectil~s 9

( I) Tabular Functions 9 (2) Ground Fire at Low EI~vations 9

(a) Formulas bull 9 (b) Example 10

(3) Antiaircraft Fir~ bullbull 10 (a) Formulas bull 10 (b) Exampl~bull 11

ii

--

-

shy

----

TABLE OF CONTENTS (continued) PAGF

(4) Aircraft Fire II (a) Formulas II (b) Example 13

(c) Interpolation _ 13

b Fin-Stabilized Projectiles 14

(I) Tabular Functions 14

(2) Appliltation 14 (a) Formulas 14 (b) Example 15

7 DJPmiddotERENTJAL EFFECTS 15

a Effects on Range 15 (I) Height of Target 15 (2) Elevation 16 (J) Muzzle Velocity 16 ( 4) Ballistic Coefficient 16 (5) Weight of Projectile 16 (6) Air Density 16 (7) Air Temperature 16 (8) Wind 17

h Effects on Igteflection 17 (I) Wind 17 (2) Drift 17

c Ballistic Density Temperature and Wind 17

REFERENCES bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull 18

GLOSSARy bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 19

TABLES

I Maximum Range for Projectile Type 1 67 II Maximum Range for Projectile Type 2 bull 7

III Maximum Range for Projectile Type 8 8

FIGURES

1 Projectile Shapes 21 2 Drag Coefficient vs Mach Number 22 J Time of Flight for Projectile Type 1 23 4 Time of Flight for Projectile Type 2 24 5 Time of Flight for Projectile Type 8 25 6 Trajectory Chart for Projectile Type 2 (12 graphs) 26 to 37 7 Trajectory Chart for Projectile Type 8 (12 graphs) J8 to 49

iii

SYMBOLS A-Azimuth measured from the direction of moshy

tion of the airplane (in aircraft fire)

A-Altitude function (Eq 63)

A-Axial moment of inertia

B-Drag coefficient in Ibjin2-ft (Eq 19)

C-Ballistic coefficient (Eq 22)

D-Drag

D-Angular deflection

F-Temperature in degrees Fahrenheit

G-Drag function (Eq 20)

H-Ratio of air density at altitude y to that at the surface (Eq 48)

H-Height of target

I-Inclination function (Eq 62)

K-Coefficient (See Eq 16 and 34)

L-erosswind force (lift)

M-Mach number (Eq 18)

M-Pseudo-Mach numbeT (Eq 65)

M-Overtumin~ moment about the center of gravity

M-log1oe=O43429 ~ approx)

N-Spin

P-Performance parameter (Eq Z7) P-Siacci range the distance ~sured along the

line of departure to a point directly above the projectile (Eq S4)

Q-Drop of the projectile (Eq SS)

R-Reynolds number (Eq 17)

R-Range

S-Space function (Eq 60)

T-Total time of flight

T-Time function (Eq 61)

V-Upper limit of integration of Siacci functions

V-Velocity

W-Wind speed

X-Total range of a trajectory

Y-Altitude of an airplane above sea level

Z-Linlar deflection

Z-Zenith angle

1--Velocity of sound

niameter of the largest cros~ section of the projectile (in Gbre drag law Eq 23)

c-Damping coefficient due to yawing moment lnd crosswind force (Eq 51)

c--Damping coefficient due to drag (Eq 33)

d-Caliber Or maximum diameter of projectile

f--Drag coefficient (in the Gavre drag law Fq bull 23)

g-Gravitational acceleration

h-Logarithmic rate of decrease of air density with altitude 000003158 per ft

h-Yawing moment damping factor

i-Form factor (Eq 21)

k-Logarithmic rate of decrease of sonic velocity with altitude 000000301 per ft _-shyk--Ratio of American to French drag function (Eq 24)

01-lass of the projectile

m-Slope of the tangent to the trajectory

n-logarithmic rate of change of muzzle velocity with projectile weight

p-Space function (Eq 28)

p-Projectile weight

ql-Indination fttlll~tion (Ell 30)

q-Altitude function (Eq 31)

s-Stability factor

t-Time of fli~ht (sometints the symld t is used to distinguish the time of flight from the Siald time function)

t-Time function (Eq 29)

u-Velocity of the projectile relative to the air

u-Component along the line of departure of the velocity relative to the air the argument of the Siacci functions

v-Velocity of the projectile relative to an inertial system

iv

I

w-True air speed of the airplane in aircraft fire

x-Horizontal distance from the origin of the trajectory

y-Vertical distance Irom the origin of the trashyjectory

I-Drift ~ (capital delta) or ~-Incnment of (foUowed

by a variable)

6-Density of air (in Givre dng law Eq 23)

T (gamma)-Factor inversely proportioaaI to the ballistic coefficient (Eq (6)

a (delta)-Yaw

(epsilon)-Angle of aite (Eq 72)

(theta)-Angle of indinatioa of the trajectory 1t (bppa)-Crosswind force damping factor

1amp (mu)-VilCOsity of the air

p (rho)-Density of the air

or (tau)-Temperature of the air

(phi)-Angle of departure

(omep)Angle of fall

Swsms One dot (example xl-Derivative with respect

to time

Two dots (example y)-Secoad derivative with respect to time

Stlbsm o-At t = 0 Y= 0 or a=o

I-Pertaining to or relative to Projectile Type I

2-Pertaining to or relative to Projectile Type Z

8-Pertaining to or relative to Projectile Type 8

I-First reviaion

2-Second revision

C-Due to I increase in ballistic coefficient

D-Drag

H-Due to height of target

R-Range component of

e-Effective

p-Due to projectile weight

s-Summital at the summit of a trajectory where

y=o s-Standard pertaining to standard conditions

t-Pertaining to or relative to some Typical Proshyjectile

v-Due to I unit increase in muzzle velocity

w-Due to wind

z-Cross component of

a-Yaw

or-Due to increase in the temperature of the atmosphere

t-Due to an increase in angle of departure

Ill-Terminal where y = 0 on the descending branch of the trajectory

v

r

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

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tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 5: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

--

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----

TABLE OF CONTENTS (continued) PAGF

(4) Aircraft Fire II (a) Formulas II (b) Example 13

(c) Interpolation _ 13

b Fin-Stabilized Projectiles 14

(I) Tabular Functions 14

(2) Appliltation 14 (a) Formulas 14 (b) Example 15

7 DJPmiddotERENTJAL EFFECTS 15

a Effects on Range 15 (I) Height of Target 15 (2) Elevation 16 (J) Muzzle Velocity 16 ( 4) Ballistic Coefficient 16 (5) Weight of Projectile 16 (6) Air Density 16 (7) Air Temperature 16 (8) Wind 17

h Effects on Igteflection 17 (I) Wind 17 (2) Drift 17

c Ballistic Density Temperature and Wind 17

REFERENCES bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bull bullbull 18

GLOSSARy bullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbullbull 19

TABLES

I Maximum Range for Projectile Type 1 67 II Maximum Range for Projectile Type 2 bull 7

III Maximum Range for Projectile Type 8 8

FIGURES

1 Projectile Shapes 21 2 Drag Coefficient vs Mach Number 22 J Time of Flight for Projectile Type 1 23 4 Time of Flight for Projectile Type 2 24 5 Time of Flight for Projectile Type 8 25 6 Trajectory Chart for Projectile Type 2 (12 graphs) 26 to 37 7 Trajectory Chart for Projectile Type 8 (12 graphs) J8 to 49

iii

SYMBOLS A-Azimuth measured from the direction of moshy

tion of the airplane (in aircraft fire)

A-Altitude function (Eq 63)

A-Axial moment of inertia

B-Drag coefficient in Ibjin2-ft (Eq 19)

C-Ballistic coefficient (Eq 22)

D-Drag

D-Angular deflection

F-Temperature in degrees Fahrenheit

G-Drag function (Eq 20)

H-Ratio of air density at altitude y to that at the surface (Eq 48)

H-Height of target

I-Inclination function (Eq 62)

K-Coefficient (See Eq 16 and 34)

L-erosswind force (lift)

M-Mach number (Eq 18)

M-Pseudo-Mach numbeT (Eq 65)

M-Overtumin~ moment about the center of gravity

M-log1oe=O43429 ~ approx)

N-Spin

P-Performance parameter (Eq Z7) P-Siacci range the distance ~sured along the

line of departure to a point directly above the projectile (Eq S4)

Q-Drop of the projectile (Eq SS)

R-Reynolds number (Eq 17)

R-Range

S-Space function (Eq 60)

T-Total time of flight

T-Time function (Eq 61)

V-Upper limit of integration of Siacci functions

V-Velocity

W-Wind speed

X-Total range of a trajectory

Y-Altitude of an airplane above sea level

Z-Linlar deflection

Z-Zenith angle

1--Velocity of sound

niameter of the largest cros~ section of the projectile (in Gbre drag law Eq 23)

c-Damping coefficient due to yawing moment lnd crosswind force (Eq 51)

c--Damping coefficient due to drag (Eq 33)

d-Caliber Or maximum diameter of projectile

f--Drag coefficient (in the Gavre drag law Fq bull 23)

g-Gravitational acceleration

h-Logarithmic rate of decrease of air density with altitude 000003158 per ft

h-Yawing moment damping factor

i-Form factor (Eq 21)

k-Logarithmic rate of decrease of sonic velocity with altitude 000000301 per ft _-shyk--Ratio of American to French drag function (Eq 24)

01-lass of the projectile

m-Slope of the tangent to the trajectory

n-logarithmic rate of change of muzzle velocity with projectile weight

p-Space function (Eq 28)

p-Projectile weight

ql-Indination fttlll~tion (Ell 30)

q-Altitude function (Eq 31)

s-Stability factor

t-Time of fli~ht (sometints the symld t is used to distinguish the time of flight from the Siald time function)

t-Time function (Eq 29)

u-Velocity of the projectile relative to the air

u-Component along the line of departure of the velocity relative to the air the argument of the Siacci functions

v-Velocity of the projectile relative to an inertial system

iv

I

w-True air speed of the airplane in aircraft fire

x-Horizontal distance from the origin of the trajectory

y-Vertical distance Irom the origin of the trashyjectory

I-Drift ~ (capital delta) or ~-Incnment of (foUowed

by a variable)

6-Density of air (in Givre dng law Eq 23)

T (gamma)-Factor inversely proportioaaI to the ballistic coefficient (Eq (6)

a (delta)-Yaw

(epsilon)-Angle of aite (Eq 72)

(theta)-Angle of indinatioa of the trajectory 1t (bppa)-Crosswind force damping factor

1amp (mu)-VilCOsity of the air

p (rho)-Density of the air

or (tau)-Temperature of the air

(phi)-Angle of departure

(omep)Angle of fall

Swsms One dot (example xl-Derivative with respect

to time

Two dots (example y)-Secoad derivative with respect to time

Stlbsm o-At t = 0 Y= 0 or a=o

I-Pertaining to or relative to Projectile Type I

2-Pertaining to or relative to Projectile Type Z

8-Pertaining to or relative to Projectile Type 8

I-First reviaion

2-Second revision

C-Due to I increase in ballistic coefficient

D-Drag

H-Due to height of target

R-Range component of

e-Effective

p-Due to projectile weight

s-Summital at the summit of a trajectory where

y=o s-Standard pertaining to standard conditions

t-Pertaining to or relative to some Typical Proshyjectile

v-Due to I unit increase in muzzle velocity

w-Due to wind

z-Cross component of

a-Yaw

or-Due to increase in the temperature of the atmosphere

t-Due to an increase in angle of departure

Ill-Terminal where y = 0 on the descending branch of the trajectory

v

r

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 6: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

SYMBOLS A-Azimuth measured from the direction of moshy

tion of the airplane (in aircraft fire)

A-Altitude function (Eq 63)

A-Axial moment of inertia

B-Drag coefficient in Ibjin2-ft (Eq 19)

C-Ballistic coefficient (Eq 22)

D-Drag

D-Angular deflection

F-Temperature in degrees Fahrenheit

G-Drag function (Eq 20)

H-Ratio of air density at altitude y to that at the surface (Eq 48)

H-Height of target

I-Inclination function (Eq 62)

K-Coefficient (See Eq 16 and 34)

L-erosswind force (lift)

M-Mach number (Eq 18)

M-Pseudo-Mach numbeT (Eq 65)

M-Overtumin~ moment about the center of gravity

M-log1oe=O43429 ~ approx)

N-Spin

P-Performance parameter (Eq Z7) P-Siacci range the distance ~sured along the

line of departure to a point directly above the projectile (Eq S4)

Q-Drop of the projectile (Eq SS)

R-Reynolds number (Eq 17)

R-Range

S-Space function (Eq 60)

T-Total time of flight

T-Time function (Eq 61)

V-Upper limit of integration of Siacci functions

V-Velocity

W-Wind speed

X-Total range of a trajectory

Y-Altitude of an airplane above sea level

Z-Linlar deflection

Z-Zenith angle

1--Velocity of sound

niameter of the largest cros~ section of the projectile (in Gbre drag law Eq 23)

c-Damping coefficient due to yawing moment lnd crosswind force (Eq 51)

c--Damping coefficient due to drag (Eq 33)

d-Caliber Or maximum diameter of projectile

f--Drag coefficient (in the Gavre drag law Fq bull 23)

g-Gravitational acceleration

h-Logarithmic rate of decrease of air density with altitude 000003158 per ft

h-Yawing moment damping factor

i-Form factor (Eq 21)

k-Logarithmic rate of decrease of sonic velocity with altitude 000000301 per ft _-shyk--Ratio of American to French drag function (Eq 24)

01-lass of the projectile

m-Slope of the tangent to the trajectory

n-logarithmic rate of change of muzzle velocity with projectile weight

p-Space function (Eq 28)

p-Projectile weight

ql-Indination fttlll~tion (Ell 30)

q-Altitude function (Eq 31)

s-Stability factor

t-Time of fli~ht (sometints the symld t is used to distinguish the time of flight from the Siald time function)

t-Time function (Eq 29)

u-Velocity of the projectile relative to the air

u-Component along the line of departure of the velocity relative to the air the argument of the Siacci functions

v-Velocity of the projectile relative to an inertial system

iv

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w-True air speed of the airplane in aircraft fire

x-Horizontal distance from the origin of the trajectory

y-Vertical distance Irom the origin of the trashyjectory

I-Drift ~ (capital delta) or ~-Incnment of (foUowed

by a variable)

6-Density of air (in Givre dng law Eq 23)

T (gamma)-Factor inversely proportioaaI to the ballistic coefficient (Eq (6)

a (delta)-Yaw

(epsilon)-Angle of aite (Eq 72)

(theta)-Angle of indinatioa of the trajectory 1t (bppa)-Crosswind force damping factor

1amp (mu)-VilCOsity of the air

p (rho)-Density of the air

or (tau)-Temperature of the air

(phi)-Angle of departure

(omep)Angle of fall

Swsms One dot (example xl-Derivative with respect

to time

Two dots (example y)-Secoad derivative with respect to time

Stlbsm o-At t = 0 Y= 0 or a=o

I-Pertaining to or relative to Projectile Type I

2-Pertaining to or relative to Projectile Type Z

8-Pertaining to or relative to Projectile Type 8

I-First reviaion

2-Second revision

C-Due to I increase in ballistic coefficient

D-Drag

H-Due to height of target

R-Range component of

e-Effective

p-Due to projectile weight

s-Summital at the summit of a trajectory where

y=o s-Standard pertaining to standard conditions

t-Pertaining to or relative to some Typical Proshyjectile

v-Due to I unit increase in muzzle velocity

w-Due to wind

z-Cross component of

a-Yaw

or-Due to increase in the temperature of the atmosphere

t-Due to an increase in angle of departure

Ill-Terminal where y = 0 on the descending branch of the trajectory

v

r

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

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1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

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49

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 7: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

I

w-True air speed of the airplane in aircraft fire

x-Horizontal distance from the origin of the trajectory

y-Vertical distance Irom the origin of the trashyjectory

I-Drift ~ (capital delta) or ~-Incnment of (foUowed

by a variable)

6-Density of air (in Givre dng law Eq 23)

T (gamma)-Factor inversely proportioaaI to the ballistic coefficient (Eq (6)

a (delta)-Yaw

(epsilon)-Angle of aite (Eq 72)

(theta)-Angle of indinatioa of the trajectory 1t (bppa)-Crosswind force damping factor

1amp (mu)-VilCOsity of the air

p (rho)-Density of the air

or (tau)-Temperature of the air

(phi)-Angle of departure

(omep)Angle of fall

Swsms One dot (example xl-Derivative with respect

to time

Two dots (example y)-Secoad derivative with respect to time

Stlbsm o-At t = 0 Y= 0 or a=o

I-Pertaining to or relative to Projectile Type I

2-Pertaining to or relative to Projectile Type Z

8-Pertaining to or relative to Projectile Type 8

I-First reviaion

2-Second revision

C-Due to I increase in ballistic coefficient

D-Drag

H-Due to height of target

R-Range component of

e-Effective

p-Due to projectile weight

s-Summital at the summit of a trajectory where

y=o s-Standard pertaining to standard conditions

t-Pertaining to or relative to some Typical Proshyjectile

v-Due to I unit increase in muzzle velocity

w-Due to wind

z-Cross component of

a-Yaw

or-Due to increase in the temperature of the atmosphere

t-Due to an increase in angle of departure

Ill-Terminal where y = 0 on the descending branch of the trajectory

v

r

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

middot15

N

N

10

KD

15

bull10

-1

~(

tT

l

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-I

I I

i 1

-

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1-

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i-H

i -

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tf-1t

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-++J

=

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rr~

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i~~

TTT

shy

1-1-

1-++

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0

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15

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1

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i ~50 ~ III

~

40

30

20

10

2 8 8 LO r2

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-1 -i T l I 7 -~J- i-

I

LOG Cg

Figure 3 Time of Flight for Projectile Type 1

--~ i

110

140

120

--- --

80

40

20

o -04 -02 o 2 A 8 10

LOG C

Figure 4 Time of Flight for Projectile Type Z

Z4

I

i 100 o

10

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40

20

I

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180

120 ampl

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Figure 5 Time of Flight i)r Ptojectile Typa 8

zs

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 8: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

r

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

middot15

N

N

10

KD

15

bull10

-1

~(

tT

l

---r~

--1

-I

I I

i 1

-

_~

1-

---+p~~-~r+1

i-H

i -

~

bull

tf-1t

iMtH

-++J

=

-~

rr~

---

+T~

i~~

TTT

shy

1-1-

1-++

-

-shy

-~

00

0

5 LO

15

2

0 u

10

1

5

40

4

5 aD

M

aCH

N

O

Fig

ure

l

Dra

g C

oef

fici

ent

VII

M

ach

Nu

mb

er

)

100 + ~

t f~ 11 +-lt

1 +

j -

~ 10 j

i+

t H-t-+

-+t~~ bull ~~i

10 I

~t-H

~

~ lrit-l ~fl70 -~

eo ~ I

i ~50 ~ III

~

40

30

20

10

2 8 8 LO r2

t 1-1-

-1 -i T l I 7 -~J- i-

I

LOG Cg

Figure 3 Time of Flight for Projectile Type 1

--~ i

110

140

120

--- --

80

40

20

o -04 -02 o 2 A 8 10

LOG C

Figure 4 Time of Flight for Projectile Type Z

Z4

I

i 100 o

10

-l-+--

H

eo

- shy

40

20

I

o -002 o 02 4 oS 08 10

180

120 ampl

~ -+~ t-+-middot looK

~ 04

-I bull i

t

LOG C

Figure 5 Time of Flight i)r Ptojectile Typa 8

zs

-- en

c gt

0 0 0 shy -IV

0

-Iamp

J 0

tshy ~

o

J (

4

i

u i

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-lt

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tlt

bull mj

W

l~ ~

i~t

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6 8

10

12

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RIZO

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R

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(10

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s)

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6

(1 o

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) T

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lo

r P

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ctil

e T

yp

e Z

4

5deg

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ati

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s m

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elo

city

( (

14

27

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~

0 ~

~ ll gt0 Q)

0 c0

0

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J ~ f-I~

4 0N r

uc Q)Q - C

~

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~ 0 tl

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~

I I L

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tr

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~

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48

56

H

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IZO

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 9: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

TRAJECTORIES DIFFERENT~AL EFFECTS AND DATA FOR PROJECTilES

1 INDODUCTIolf TO EXTDloa BALLISTICS

BaUiltics is the science of the motion and effects of projectiles Exterior Ballistics deals with that part of the motioa between the pr0shyjector and the point of burst or impllCt

11Je projector may be any IOrt of weapon a sling-shot a bow a mortar a rifle a rocket launcher an airplane etc A projectile may be any body that is projected by such a weapon However in this punphJet the term projectile wiD be restricted to those missiles that are in free ftight through the air after beiDg propelJed by a gun or a rocket motor This term does not inshyclude bombs which are released from airplanes they wiD be considered in another pamphlet

he motiCn of a missile in ftight is raJly quite complicated Even a fin-stabiJiud pr0shyjectile or bomb that is not spinning about its Joncitudinal axil is swinging about a transverse a-cis and this urcets its motion The nose of a spining shelJ PftCe5SeS about the tangent to its traJectory and ita attitude gives rise to forces that not oaly urea its motion in a ftrtKaJ plane but aJao move it out of this plane To simplify the ~Ia~ ~wever it is usually assumed that a misSIle ads hke a particle subject to two forces (1) gravity which is directed vertica11y downshyward ~ (2) drag which is directed opposite to the direcbon of motion Gravity i assumed conshystant until 1956 the gravitatioaaJ acceleration was usually taken to be 32152 ft-r (980 msecI) and was used for aD tables rdelleel to in this teXt now the lstandard value is 32174 ft-r (980665 msecS) The drag depends 00 the -size of the missile its velocity the density of air 3nd other factors Under these conditions the motion tolshylows a smooth planar path which is called an ~~ Uistic trajectory- or Htrajectory for

Ie initial conditions for the trajectory of a particular missile are its initial ft1ocity and angle of departuremiddot For a projectile the initial velocity

en tenD _gk of til and the tenD -- u 1Ded ia this pamphlet repI t the aacie from the 1IoNotIIU to the line of departwe tbadore woa1d be ~ aceuntcI7 ClllllPIeIeIy ten8ed -k of

1

is the muzzle velocity and angle of deplrt I 1- is approximately the elevation of the w~tJOn

(fictitious values of these quantities may ~ used in the case of a rocket that bums OlOLSide the launcher) A bomb is released with the speed of the airplane generally in a horizontal direction If a gun is mounted in an airplane or other moving vehicle the initial conditions arc r ~ct~

by the motion of the vehicle In any case it is custonwy to compute trajectories for a fe seshylected values of initial velocity and elevation

Certain standard conditions are specified for a nonnal trajectory not only the initial velocity and angle of departure but also the weight of the projectile and a factor that depends on its shape the density temperature and lack of motion of the air and the height of the target relative to the projector In order to determine the effects of variations from these conditions it may be conshyvenient in some cases to compute non-standard trajectories however they can usua))y be cstishyrnnted in other ways as will be explained later

2 VACUUII TItA]ItCTORIES

a EtpUltioM of Moliota

A rough idea of an exterior ballistic trajectory may be pined by neglecting the air resistance considering only the effects of gra~ity Then if

x is the horizontal distance from the origin y i the vertieaJ distance from the origin t is the time of flight r is the gravitational acceleration

and ~ots ~ derivatives with respect to time the differential equations of motion are

i=O y= -g (1)

The initial UKlitions denoted by the suhscript 0 are

X = v cos a j =Vo sin a Xo = 0 y = 0

where v is the velocity a the angle of inclination By integrating equations (1) we find that at

any time

it = v cos BOo Y=v sit 80 - gt (2~ and by integrating (2)

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

middot15

N

N

10

KD

15

bull10

-1

~(

tT

l

---r~

--1

-I

I I

i 1

-

_~

1-

---+p~~-~r+1

i-H

i -

~

bull

tf-1t

iMtH

-++J

=

-~

rr~

---

+T~

i~~

TTT

shy

1-1-

1-++

-

-shy

-~

00

0

5 LO

15

2

0 u

10

1

5

40

4

5 aD

M

aCH

N

O

Fig

ure

l

Dra

g C

oef

fici

ent

VII

M

ach

Nu

mb

er

)

100 + ~

t f~ 11 +-lt

1 +

j -

~ 10 j

i+

t H-t-+

-+t~~ bull ~~i

10 I

~t-H

~

~ lrit-l ~fl70 -~

eo ~ I

i ~50 ~ III

~

40

30

20

10

2 8 8 LO r2

t 1-1-

-1 -i T l I 7 -~J- i-

I

LOG Cg

Figure 3 Time of Flight for Projectile Type 1

--~ i

110

140

120

--- --

80

40

20

o -04 -02 o 2 A 8 10

LOG C

Figure 4 Time of Flight for Projectile Type Z

Z4

I

i 100 o

10

-l-+--

H

eo

- shy

40

20

I

o -002 o 02 4 oS 08 10

180

120 ampl

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 10: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

x = (Vocos so)t y = (vo sin so)t - gt22 (3)

b Charculeristies of Trajectories From Equations (3) we find that the time at

any horizontal range is

t = xvocosso (4)

and hence the ordinate is

y = x tan so - gx22v02 cos2 so (5)

This is a parabola with a vertical axis The total range X is found by letting y =0 in

(5) and solving for x

X= (2v02 jg) sinsocosso= (v0

2g) sin2s0 bull (6)

This shows that the range is a maximum when so =45deg

The total time of flight T is found by substishytuting (6) for x in (4)

T = (2vog) sin -80 (7)

The components of the tenninal velocity are found by substituting (7) for t in (2)

x= Vocos so Y= - Vo sin bullbull (8) Hence the terminal velocity is

(9)v= Vobull

and the angle of fall (considered positive) is

(a) = 0 (10) By differentiating equation (5) with respect to

x we find that the slope of the trajectory at any point is

~ = tan - gxvo cos -8 (11)

At the summit the slope is 0 hence the horizontal range to the summit is

x = (vlIIg) sinsoC06 -80=X2 (12)

By substituting this for x in (5) we find the maxshyimum ordinate

y = (vo 2g) sin2 -80 = = (g8) T

By substituting (12) for time to the summit

(1 - cos 2-80) v4g (13)

x in (4) we find the

to = (vg) sinso = T 2 (14)

3 Ala RESISTANCE

a Forces Actig Oft G Missile MOfIiflg Air A missile moving in air encounters other forces

besides gravity The principal components of the force produced by motion through air are drag crosswind force and for a spinning projectile Magnus force

( 1) Drag is the component in the direction opshy

2

posite to that of the motion of the center of gravity This is the only component acting on a non-spinning projectile that is trailing perfectly

(2) Cro~mfld Forct in the component pershypendicular to the direction of motion of the center of gravity in the plane of yaw The yaw is the angle between the direction of motion of the center of gravity and the longitudinal axis of the missile This component is the cause of the drift of a spinning shell

(3) M agvs Force acts in a direction pe pendicular to the plane of yaw This is the iorce that makes a spinning golf ball or baseball swerve

b Simplified ASS14mptiofls

The motion caused by these forces is explained in detail in the Ordnance Corps Pamphlet Demiddot sign for Control of Flight Characteristics In general the motion of the center of gravity is affected by the motion about the center of gravity and occurs in three dimensions To simplify the calculations it is usually assumed that the only forces acting on the missile in free flight are drag and gravity The crosswind force is implied in the drift but this is detennined experimentally as a variation from the plane trajectory This approximation is satisfactory except at extremely high elevations where the summital yaw is Yery

large

c Dr~g Coefficintt The drag encountered by a projectile moving in -shy

air is defined b) the equation of motion

dv D IIImdt= - -mg SID v (IS)

where

m-is the mass of the projectile v-the velocity of the projectile relative to an

inertial system t-the time D-the drag g-the gravitational acceleration -8-the angle of inclination

The drag coeffieind is defined by the relation

K D = Dpdu (16)

where

Kn-is the drag coefficient p-the air density d-the caliber or maximum diameter u-the velocity of the projecttle relative to

the air

The drag coefficient is a function of the Reynolds

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

middot15

N

N

10

KD

15

bull10

-1

~(

tT

l

---r~

--1

-I

I I

i 1

-

_~

1-

---+p~~-~r+1

i-H

i -

~

bull

tf-1t

iMtH

-++J

=

-~

rr~

---

+T~

i~~

TTT

shy

1-1-

1-++

-

-shy

-~

00

0

5 LO

15

2

0 u

10

1

5

40

4

5 aD

M

aCH

N

O

Fig

ure

l

Dra

g C

oef

fici

ent

VII

M

ach

Nu

mb

er

)

100 + ~

t f~ 11 +-lt

1 +

j -

~ 10 j

i+

t H-t-+

-+t~~ bull ~~i

10 I

~t-H

~

~ lrit-l ~fl70 -~

eo ~ I

i ~50 ~ III

~

40

30

20

10

2 8 8 LO r2

t 1-1-

-1 -i T l I 7 -~J- i-

I

LOG Cg

Figure 3 Time of Flight for Projectile Type 1

--~ i

110

140

120

--- --

80

40

20

o -04 -02 o 2 A 8 10

LOG C

Figure 4 Time of Flight for Projectile Type Z

Z4

I

i 100 o

10

-l-+--

H

eo

- shy

40

20

I

o -002 o 02 4 oS 08 10

180

120 ampl

~ -+~ t-+-middot looK

~ 04

-I bull i

t

LOG C

Figure 5 Time of Flight i)r Ptojectile Typa 8

zs

-- en

c gt

0 0 0 shy -IV

0

-Iamp

J 0

tshy ~

o

J (

4

i

u i

t1

_ ~

-lt

tmili

~ttltt

tlt

bull mj

W

l~ ~

i~t

j

6 8

10

12

HO

RIZO

NTAL

R

AN

GE

(10

00

Yo

s)

-r

_t

-~tt~e~

F~gure

6

(1 o

f IZ

) T

raje

cto

ries

lo

r P

roje

ctil

e T

yp

e Z

4

5deg

elev

ati

on

IZ

OO

Ip

s m

uzz

le v

elo

city

( (

14

27

~

C ~)

N shy-Ilo

r -~

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 11: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

ORDP 20-140

number R and the Mach numher M The The non-dimensional drag coefficient KD for the Reynolds number is defined as 9O-null H EAT Shell T 108 is tabulated as a funcshy

tion of Mnch number (See References 3 4 5 andR=udp (17)

(I which may be obtained from the Ballistic Reshywhere is the viscosity of the air and the Mach search Laboratories Aberdeen Proving Ground number as Maryland)

M =ua (18) d Drag Function where a is the velocity of sound in the surroundshy The drag function G is computed by the formula ing medium The viscosity is related to the G= Bu (20)friction of the air the velocity of sound to its

with u in feet per second For convenience in elasticity At extremely low velocities the computing trajectories this has been tabulatedReynolds number causes greater variation but as a function of u2100 with u in meters perthe effect of the Mach number is larger when it second and either feet or yards per second for exceeds 05 The angle between the direction of Projectile Types 1 2 and 8 (See References 7motion of the center of gravity and the axis of 8 and 9) symmetry of the shell called yaw also affects the

drag coefficient but this is usually stripped out of e Form Factor the resistance firing data It is not practical to determine the drag coshy

Figure 2 (p 22) is a graph of drag coefficient efficient as a function of Mach number for all vs Mach number for the four typical projectiles projectiles Instead the drag coefficient of a proshywhose shapes are shown in Figure 1 (p 21) jectile whose shape differs only slightly from one These projectiles are described and the hasic of the typical projectiles is assumed to be proshyfirings explained in Section 4 It should be noted portional to the typical drag coefficient If Kilt that subscripts are used to distin~ish the typical is the drag coefficient of a Typical Projectile the projectiles to which the drag coefficients pertain form factor of a projectile whose drag coefficient a second subscript is sometimes added after a is KD is the ratio decimal point to denote a revision It is evident that all the drag coefficients increase rapidly in it = KDKDt (21) the vicinity of Mach number 1 The main differshy The form factor may be determined from the ence between curves is in the ratio of the maxishy time of flight at short ranges or from the range mum which occurs between Mach numbers 10 to impact or the position of burst at a few elevashyand 15 to the minimum subsonic value Although tions If it is desired to estimate the form factor of the drag coefficient has tgteen determined and tabshy a projectile without firing it the Ordnance Corps ulated for several other projectiles these four Pamphlet Design for Control of Flight Charshyrepresent the principal shapes for artillery proshy acteristics2 should be consulted It explains the jectiles effects on drag of variations in length and radius

KD is a non-dimensional coefficient and a conshy of head meplat diameter base area length of sistent set of units should be used in Equation shell and yaw ( 16) However it is customary to express the Generally the form factor of a projectile with density as a ratio the caliber in inches and the a square base and an ogive less than 175 calibers velocity in feet per second then since the drag high should be referred to Projectile Type 1 that is in poundals the drag coefficient is expressed in of a projectile with a square base and an ogive pounds per square inch per foot and is denoted by more than 175 calibers high to Projectile Type B Until 1956 the standard air density was 8 that of a projectile with a boattail to Projectile taken as Type 2 and that of a finned projectile to the

po =007513 Ibft3 =5217 X 1O-4 1bin2-ft TI08 Shell However there are exceptions to The practical drag coefficient these rules eg KDt is used for fin-stabilized morshyB = 5217 X 10-4 KD (19) tar shells at low velocities and KD2 fits the calcushy

lated drag coefficient for some longer fin-stabilized for Projectile Types I 2 and 8 is tabulated as a shells The drag coefficients of bombs are treated function of velocity for the standard velocity of elsewhere tosound

llo = 112027 fps 0076475 Ibl ft and the velocity of sound is 1I1689 fps -----rn 1956 the Department of Defense adopted the standshy also the viscosity is 1205 x 10-1 Ibft-sec but the effect ard atmosphere of the International Civil Aviation Organshy of Reynolds number is not considered in computing trashyization In this atmosphere at the surface the density is jectories

3

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

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N

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KD

15

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~(

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40

30

20

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Figure 3 Time of Flight for Projectile Type 1

--~ i

110

140

120

--- --

80

40

20

o -04 -02 o 2 A 8 10

LOG C

Figure 4 Time of Flight for Projectile Type Z

Z4

I

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40

20

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180

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 12: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

ORDP 20-140

f Ballistic Coelficient The ballistic coefficient relative to the tabulated

drag coefficient is defined by the formula

Ct = mitd2 (22)

where m is the mass of the projectile in pounds d is the caliber (or maximum diameter)

in inches g A ir Density

The air density is a function of altitude The exponential function adopted by the Ordnance Corpsmiddot is tabulated in References 7 and 11 The ratio of the density at an altitude y to that at the surface is H(y)

4 DF-SCRIPTION OF TYPICAL PROJECTILES

This pamphlet contains data that pertain speshycifically to four types of projectiles Types I 2 and 8 and the ~-mm HEAT Shell T lOR They can he applied to other shapes by using a form factor as explained in paragraph 3e

a Projectile Type 1

Most of the service projectiles used by the European artillery during the last third of the nineteenth century had square bases and ogival heads of various apical angles In Russia during the years 1868 and 1869 General Magenski conshyducted some experiments at St Petersbur~ to deshytermine the law of air resistance of projectiles with a semi-apical angle of 48deg22 (lA9-ealiber radius head) at velocities from 172 to 409 ms In Engshyland from 1866 to 1880 Bashforth conducted simshyilar experiments with projectiles of the same form (it may be that the tables were reduced to this form) at velocities from 148 to 825 ms In HoIshyland Colonel Hojel conducted a few such experishyments during 1883 the exact form is uncertain but the ogive was evidently somewhat longer than those of the Russian experiments In Germany the Krupp factory conducted a large number of air resistance experiments at Meppen Proving Ground starting in 1881 (the principal results were reported by Siacci in the Rivista for March 1896) the velocities varied from 368 to 910 ms and ~hree different types of projectiles

The tabulated trajectory data based on the old standshyard atmosphere give results that are nearly the same as those based on the new atmosphere providing a suitable change is made in the ballistic coefficient For example a 280-mm shell fired with a muzzle velocity of 1795 fps at an elevation of 45deg attains a range of 15790 yds the ballistic coefficient is 362 with ICAO atmosphere and 3SO with the old Ordnance Corps atmosphere This funcshytion was used in computing trajectories before 1956 when the Department of Defense adopted the standard atmosshyphere of the International Civil Aviation Organization

were used one was the same as the Russian (or the results reduced to the same) but the others probably had longer ogives In France a comshymission of the naval artillery conducted many such experiments at Gavre Proving Ground from 1873 to 1898 at velocities from 118 to 1163 ms they fired ogival projectiles with three semi-apical angles 45deg55 (164 CRH) 41 deg40 (198 CRH) and 31 deg45 (334 CRH) For further details see References 12 to 16

In analyzing the results of the experimentsIT the Gavre Commission of Experiments assumed that the drag could be expressed in the form

D =~ a2V2 f(V) (23) g

where D-is the drag (kg) ~-the density of the air (kgmll )

g-the gravitational acceleration (msec2) a-the diameter of the largest cross section of

the projectile (m) V-the velocity (ms)

The drag was treated as a function of velocitv without taking account of the velocity of sound although the dependence of drag on the velocity of sound was strongly suspected the coefficient f was plotted as a function of Valone After studying the results obtained with projectiles of various ogival angles the Commission confirmed the law deduced by Helie in 1888 that f(V) is proportional to the sine of the ogival angle at least for values from 40deg to 90deg within the experishymental errors

In 1917 Chief Engineer Garnier of the Gavre Commission published a table18 of log B and the corresponding logarithmic derivative with veshylocity as argument this B is equivalent to f(V) for an ogival projectile with a 2-ealiber radius head This ideal shape is what we call Projectile Type 1 (see Figure I) The Ordnance Departshyment of the United States Army then prepared a table of the logarithm of the drag function 1

G = kBV (24)

with V expressed in meters per second and the factor k to take account ot differences in definishytions and standards Below 600 ms k = 000114 but at higher velocities it is variable G was called the Gavre function later the symbol was changed to G1 to denote that it pertains to Proshyjectile Type 1

In the table of log G the argument V2100 varies from to 0 to 33000 (equivalent to 1817 ms or 5961 fps) G has been tabulated for V2100 up to 25000 (1581 ms or 5187 fps)

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 13: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

middotThe product Gv has also ~ tabulated as a fomction of v in feet per second up to 6000 ipS1O

b PrDjeclik T~lP l

A sketcb of ProjectIle Type 2 is shown in Figure L This projectile has a 6- boattail ~

caliber ionr and an ogivo-eonical head 27 calishybers long The eXpetimental 47-inch Shell E1 had thi shape However the resistance firings ere actually conducted with two types of 33-inch shell Type ISS with a Sdeg boattail and Type 157 with a 7 boattail The results were so dose that thq were grouped together to represent one tYPe T~e projectiies were fired from 1922 to 1925

at veJonties from 655 to 3187 ips The results of these nnngs were fitted by the tabulated drag function ~ (this is defined in paragraph 3d) Later it was extrapolated to 10000 ips by means oi theoretical considerations For the sake of greater smoothness and accuracy two revisions have been made Gu bull tabulated to 6000 ips and Gu bull to 7000 ips Gt 1 is approximately the same as Gt bull but Gu is lower at velocities above 2000 Ips

c PrDjectik Type 8

A sUtch of Projectile Type 8 is shown in Figshyure 1 Tnis projectile has a square base and a IItCant ogive 218 calibers high Its ogival radius is 10 calibers which is twice that of a tange~t oglve of the same neignt

The drag function G8 was calculated from data obtained oy the British Ordnance Board from t(fttsourcegt

(j) ieuurements (If a model in the National Pnysica Laboratory wind tunnel at Maen numoers from 022 tr O~~

(~ awsunce lirings ot ~-pounder Sc1eE at Macn numilers itOm 06S to ~a

f 3) Resistanee firings oi 3-inch shell at ~aci numbers from 03 to + L

V was irst tabuiatett to SOOO ips Later a reviselti table caIi~ Gbull t bull was extenlt1ed to 6000 ip3 T ne corresponding cirag oefiicient~ are apshyroxnnatelY P~nional to the British 1940 Law whici was first tabulated to SOOO ips and later revised above 3150 ips and extended middotto 6000 ips by a Ower Jaw

d HEAT SMI1 90-bullbull TI08

A sketch of the 9()mm High Explosive Antishytank Shell Tl~ is shown in Figure 1 This proshy~ecti1e hu tim ~ caliber in span at the end of a long boom and a conical ogive about 2 calibers high

The drag of this projtttie WllS determiaed at velocities from 700 to 2700 fops or free flight firings

in th~ larg~ Spark Range of the Exterior Balshylistic Laboratory at Aberdeen Proving Ground The dl2( coefficient (defined in paragraph 3c was fitted with a series of analytical expressions which were used in tabulating it as a fWlCtion (~ Mach number irom 01 to 27

5 TU]ECTORIItS IN AIR

a Eqll4lions of Jot Vivn Under standard conditions the equatio~lS ( 1shy

tion are

GH GHx=-c-x y=-c- r - gbull

where x is the horizontai rangt y-the altitud~

H-the air density ratio g-the gravitational acceleration (~~12

ftsec2 )

and dots denote derivatives with respect to timL The initial conditions are

Xo =0 Yo =0 Xc = VO CO~ ~ ~~ = 0 sin )01

where Vo is the initial velocity ao-the angle of departure

These equations cannot be solved analyticaHv but they can be solved by a method oi numericai integration explained n References 21 22 23 and 24

b CJuvoderistics of Traectonei ( 1) Ballisk Tabies Trajectory data have

been tabulated ior Proiectile T~s 1 amp10 2 ane for some bomb shapegt

The Exterior Ballistic Tables Baseci on Ntmiddotmiddot merical Integration (Reterences 7 25 and 20 pertain to Proiecte Type 1 The merer ~s toe unit of lengtt Tne trJectones were ci1pute~

iorwarci and tackwacmiddot [r(Jl1 the swnrri and cut off at several ltitudemiddot 1i c is the middotcummita ballistic c~fficien ci ~rajectory and y the maxshyimum ordinate of a partia trajectory the baliistic coetncipnt C 0 this parti4 1 trajectormiddot -1usfies ie relation

loglOC = loglcC - OltXXl045 y (26)

For each Y Cbullbull and summita1 velocity v bullbull Volume ghes the horizontal range time and velocity component~ 3t the beginning and end of the partial trajectory If the muzzle velxity angle oi departure and ballistic coefficient amiddote knOlo1 Volume Il moy be used to find the time of fli(lu tG the summit te the velocity at the summit the horizontal range to the summit and the maximum ordinate Then C can be comshyputed and trajectory data can he found in Volume I for the i-ven C aile v at various altitudes

s

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

middot15

N

N

10

KD

15

bull10

-1

~(

tT

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 14: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

However terminal values can be found more conshyveniently from Volume III which gives the horishyootal range X time of flight T angle of fall w and terminal velocity Vw the arguments are the same as in Volume II the muzzle velocity varies from 80 to 920 meters per second the angle of departure from 0deg to 80deg (at intervals of 1deg fom 0deg to 30deg and 2deg from 30deg to 80deg I the hallistic coefficient from 1000 to 1778 (at intershy als of 005 in log C)

The Brief rxterior Ballistic Tables for Proshywrtik- -ivrgte i (Reference 27) cOlltains values I hM wfr~ ohtaineej hy interpolation in Volume II I am conversiOll to English units (yards and fttT j~r trond The muzzle velocity varies from 200 rf )()(X) f(~T Igtf second in 100 foot per seconrl 1llremfntS The ilngle of departure varies from ISO to 75deg in 15deg increments Obviously intershyVlbtion for angle of departure in this table is difficult nfvertheless the table is useful for many

purpose The table of range for an elevation of 45deg whKh is n(~r1y the maximum ran~e is rqgtroshy

duced iXre (Tble 1) Tht Extcror Ballistic Table for Projectile

Tvpe 2 (Refuence 28) consists or three parts Tahle Sumnital and Tenninal Values Table I I Coordinates as Functions of Time of Flight ann a lor-e grah of Malimum Range vs Bal1isic Coefficient The tables have been extended to include data for everv 15deg from 0deg to 90deg T~le muzzle velocity varies irom 1200 to 5200 fett shysecond and the ballistic coefficient from 050 0 1000 The coordinates are given in yard ih~

time in seconds and the velocity in feet per second Tahle I gives the time to the summit the ho-ishy1Ontal range tn the summit the maximmiddotm ordinate the time of flight the total range lIshyangle of fall and the terminal velocity Table I l gies the horizontal rmge and altitude at e(ry 5 seconds of time Unfortunately the velocity

TABLE I MAXDJUM RANGE FOR PROJECTILE TYPE 1

ELEVATION 45deg

Range in yards Muzzle Velocity (vo ) in fps

log C 0000 i OoiO 0100 0100 0200 0250 I0300 0350 0400 10450 0500 O5lO 0000 IO6flO C 1000 i 1122 1259 1413 1585 1778[11195 2239 2512 2818 3162 354tI 39S1 44fr

_yo = ==1===1== =1==004 Xmiddot 397 ~~ 399 400 401 403 404 405middot 406 407 I 40fI ~ 409 [ 409 300 1447 R5t R64 171 tl77 AA3 ~ 892 I 897 000 1 ltlO4 gm 910 913 -400 14H1 ~ 1441 i 1462 I41l1 1499 1514 152R 1541 15~ 1564 1573 1H2 lfillO I lW71

00 71J77 2121 ~ 2162 2201 r137 2270 2300 2328 I 23M 2378 2399 2418 2416 24gt2 ____ i i ------ ---1---------------1---shy

liOO 2711 21162 j 2934 3003 3()67 312f 31111 3232 I 3279 3322 3161 3397 3-f I 3461 700 to) 1 jt~ 3749 3Mi6 3958 4(1)3 I 4140 4222 4301 4372 44~ 4500 4556 1 4fJ06 loll 10 447 I 44J 1 middot~)70 4724 4S70 500H 141 2f7 534 I4IM N19i 5690 5m I iW NIO 4Wtf 51~i gt349 )j56 i755 5947 fila1 6110 647f fl634 67CJ 0023 7054 7174

~OlJO_1 --~H~_i)~ _~l~ ~I 654=- 6792 7037 _~=-1_749f_ 7714 7919 8115 1l299 1I4~~

1100 i925 i 6~ tih1 AAflf I 7176 74S2 77fl4 HOmj 8166 8644 8913 9172 9420 I 9(gt5M 1200 il 621 6603 i 61~ 7314 7671 8027 x3Ml 8733 9077 9417 9749 10073 1~ 10ti91 1300 Ii 6521 i 69051 7293 7689 8087 8488 88m 9292 9693 10092 1~ 10872 11253111626 1400 II 67)9 I 7172 7~ ~25 8460 8905 9353 9804 10258 10711 11165 11616 12065 12508

_1~- filaquo79-1~I_~~ ~~I_~ 9294 9787 10287 10792 11301 11814 11329 12845 13360

lro 1 7JRimiddot 7tiit llli4 Rtill I 9141 9fJ64 110200 10747 11302 11869 12442 13021 13005 14194 17m i 7~1 7x73)~ 1112 94M t0021 I 105-l9 11193 11798 12421 13056 13701 14356 15019 1)4(1 1 7ifi9 ~kt27 9t7 1l7fi7 10368 1109lt9 1163C 112288 12967 13862 14374 15099 15839 t9110 i 77fgt2 ll~ H61 944 tlXlampl 1m07 11371 12059 12771 13i05 14262 15041 15839 16659

~__7113~ Ml 0093_~~ 10364_~~=-i 1174~_~_11403711485D 15706 165llO 17480

2too i Htllli I ~ 1 1l320 997211065 1t372 I 12121 12903 1371f 14567 IMM 16372 17323 1 18m6

2_110 I R2j)l HH~ 9M2 10225 110942 16971124AA 133Hl 141~ 15096 116049 17038 lfOl8 119136I I

ljtlfl k447 lOHI litll IG473 11225 1011 12X53 1372 4655 15624 116644 17706 18820 119975 l4 II I AAt2 I 1274 1975 10711 11iO t2336 1321gt 14141 15121 16152 17239 lR375 19)74 2m21 45tJO 1r174 I 94W 10U18 10961 117M2 1t52 1S57 14552 15585 16679 117834 Il1048 ~i30 21675

-2fD-1 89351 9642 10397 llIDI 12056 l~ 13931 ~s8 l004S j 17205 i 18430 1972S-Z1095 t~ 2700 9092 I 9823 10603 11438 13237 13275 14285 15362 16510 117731 I 19027 20405 21Hfi6 23412 2ltlO 9247 10001 1(M)7 11672 1Zi95 13SR2 141lJi 15764 1amplt70 18257middot 1~25 21091 22645 24294 2IJO 9m tOI77 11010 11903 12AAI J~ 14l~7 16165 t7429 lR782 20225 21778 23428 25184I

I3(0) 91gt49 J0351 11210 12132 13123 14187 Ii 15334 11)563 Cl5jI930312OH23 22464 24213 20083

6

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

a) M28 3461 MaD 3513 36M -35M-- --as-7--1--35Q-1middot-3lI05--1 3619 3631 3amp60 I ZolAti I ~5A 700 46ampa 4606 4651 4693 4733 4766 4800 4829 4865 4879 I 4899 4918 4934 4951 I 1M) 51TT 68llO 5934 0gt1 60amp4 6120 6172 6219 6200 6298 6333 6364 6394 I l4JI 900 10M 7174 72lU 7389 7484 7573 7662 7725 rnn 7852 I 79OT 7968 eoo m4 I

1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

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TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 15: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

TABLE I (Continued)

MAXIMUM RANGE FOR PROJEcrlLE TYPE 1 ELEVATION 45middot

Range in yards Muzzle Velocity (v) in fps

ILoc C Oa) 0amp110 0100 07~ 0800 0800 0900 0960 1000 1050 i1100 11~ l5~ ~7~ 4 58

1-111_3bullbull1-tmiddot467_ 6012+6middote23_6bullbull31-j0 7943 8913 1000 1 12 141 ~il

1 1 6UU _ 409 409 410 410 410 411 411 412 412 412 413 413 3 D m m m m m ~ m ~I m ~ ~ ~ bull ~ -tOO 1690 1597 1604 1611 1614 1619 1624 1627 1630 1634 I 1837 1639 d -043 SlO 236 2462 2467 24llO 2491 ~1 2511 251l I 2526 2533 2MO 2M6 ~ 25-os

1

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1000 I 8_ 8472 8634 8786 8928 9080 9180 9292 93lM 94891_9575 9663 I 1l7~ _~~~ ~------I----1middot----- - shy

1100 9a) 96M 9882 1001M 10296 10484 10660 10826 101J7V 11120 11252 11373 1181 II [~ II 13JO 10388 10891 10984 11268 11153amp 11794 l203R 12268 12487 12891 12882 13082 13228 13qt1

113)1) 11263 11628 llV90 12344 12688 3020 13339 13ampt4 131136 1~131m 14m IIAt7~ I1400 1~ 12llO8 1~ 13375 13796 14207 141lO4 14991 1l53lM 15722 111081 18394 16702 1fW1 UlOO 12845 13380 13812 14381 14881 15314 Itamp7 16331 16110 17235 17887 180lIO 18474 18852

~-11i06 ~ 14183 16370- -1-6636--1-1-71-og--l-1-7ff1-4 -1-8227- -18-786-- 19291 1998 JIt8f1 20756

1700 1ltampM6 1~19 1a186 16357 17030 11702 18371 19031 19682 20324 21659 1800 1MD9 15839 166118 17344 18108 18875 19643 Dt08 21162 21913

1100 158391661lO 16859 1839917491 18338 2029G19198 D)83 2093622253 ~2C711S1O~0middot ~2M28-- ~ jDQ 17480 19340 21270 __ ~20967 ---1---+--+---1

2100 17323 18306 19315 20353 21416 22497 2S59fl 2200 180118 1913amp ~ 21380 22561 23748 24972 26217 2300 U183gt 19975 21177 22421 ampmYT JS1r1 26385 2ml 2400 19674 Il821 22124 23478 24883 26334 27832 2D372 2SX) 3mo 21ff15 23082 24563 3lI083 27873 29321 31028

---I--~middot-----lmiddot_--I---+---i ---I 21096 22539 240M 2Sampt6 rrs1I 29048 llll61 32748 I 21886 23412 2ro4S 28763 28M4 30amp8 32446 22M5 24294 2lI04O 2nIIlO 129849 31910 34091

shy I23428 26184 27049 29037 31183 330UO 3S197 i - 24213 1 211083 I 2lDlO bull 30217 i 32Ii01 349+1 37558 i

Mvcoat j fPl

i 13JO 1 10gtbull bullI 2000bullbullbullbull 2400bullbullbull I 2800

33JObullbullbullbullbull 3lIOObullbullbullbull ~

middot +m ( 4800bull

~200

TABLE II MAXIMUM RANGE OFPROJECfILE TYPE 2

Range in Units of 10 Yards

-03 -C2

i~ 0 bullbullbull 7119 905 1078I819 983 1182 m 1061 1287 934 I 1131 139t

992 1218 Il50t 1051 1299 1617 1112 1384 17315

I

00 02 04 0800I

709 861 lOOt 12271121 851 1088 1335 182l1l5ampl

1001 1322 ItIllO an 2499 1143 UlOI 207l 3286

1284 I 1806 2179 1298 ~ 1426 r62 2928 4074 M89 I 1571 2335 M38 01 7201173) I 262G 4Oll8 91066a5

1874 2Qst 4834 7911 11335 3)37 3342 li846 9838 13888 2220 37V6 7196 12091 16752I

I

LO II I3XJ) 2lI8O 31183 I S3ll9 I 7006 I9034

11356

14019 1701 ~

components are not tabulated The graph has a in this pamphlet (Table II) cune of maximum range vs ballistic coefficient Some trajectories have been computed for Proshyfor every 400 feet per second muzzle velocity it jectile Type 8 at an angle of departure of 45middot also lists the angle of departure for maximum The range which is nearly the maximum raace ~ A table f- the maximum ranee is included is tabclated here (Table III)

1

----- -

------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

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1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

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49

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 16: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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------I

TABLE III MAXIMUM RANGE FOR PROJECTILE TYPE 8

ELEVATION 45deg

Range in Units of 10 Yards

Los c MuuJe Velocity Jpe

00 02 04-02 06 08 10

815I 1200 621 961 1091 1201 12886amp 2000 680 1223 151U923 1934 2403 2826 2800 R22 1650 22871168 3124 4231 5251

2145 31623900 9lW 1432 8740169364865 4-400 44701108 1720 2726 7492 1366110884

660(5200 342412li8 11693~ 16582 20319

When bombs were dropped at low speeds trashy m-the mass of the bomb in pounds jectory data based on the Gavre drag function GJ The tables give the horizontal range from release were accurate enough for calibrating the sights to impact (feet) the time from release to impact In fact the descending branches of the trajectories (seconds) the striking velocity (ftsec) and the in Volume I of the Exterior Ballistic Tables striking angle (degrees) The dng coefficients could be used for this purpose Actually some are tabulated as functions of the Mach number in Bomb Ballistic Reduction Tables were pubshy the appendix they are graphed in the introshylished which were more convenient for this purshy duction pose However at transonic speeds the drag (2) Gahs Figures 3 4 and 5 are graphs of functions of modem bombs differ considerably the total time of Right for an elevatioTl of 45deg The ftom G1bull Drag coefficients have been detennined time of flight is useful in estimating wind effects for several shapes but three of them have been For antiaircraft firing and for firing to the selected as bases of Bomb Ballistic Tables (Refshy ground at different altitudes points along the trashyerence 10) drag coefficient A was detennined jectory are needed Figures 6 and 7 show the from wind tunnel tests of a shape designed by the trajectories ComPl~ted with G2 and G at angles of -ational Advisory Committee for Aeronautics and is probably the lowest drag coefficient that any

departute of 45deg and 60deg (there is a different graph for each muzzle velocity each elevation - shy

oomb will have drag coefficient B was determined and each Projectile Type) Trajectories based from range bombing of the 3000-pound Demolishy on G1 are not included because no antiaircraft proshytion Bomb M119 and is suitable for other memshy jectiles have a blunt head The TI08 HEAT hers of the series including the 75O-pound Bomb Shell is usually used only in direct fire at short MilS and the IOOOO-pound Bomb M121 drag ranges Trajectoy data for other elevations can coefficient C was determined from resistance firshy he estimated from those at 45 deg or 60deg by assuming ings of the 75-mm Slug Mark I and is probably that the slant range is the same for a given time of the highest coefficient that any bomb will have flight

The arguments of the Bomb Ballistic Tables Unlike the vacuum trajectories in air the are release altitude (1000 to 80000 feet above sea horizontal range to the summit is more than half level) true air speed of release in level flight (250 to 2(XX) knots) and perfonnance parameter (0 to 15) The performance parameter P is inverseshyly proportional to the ballistic coefficient it is deshyfined by the fonnula

the total range and the time to the summit is 1e4s than half the total time however the maximlJ4l ordinate is approximately (g8)Tt In air the tenninal velocity is less than the initial velocity and the angle of fall is greater than the angle of

P = lOOdJm (27) departure At a given elevation the total flIlgt where d is the maximum diameter of the bomb in increases less rapidly than the square of tilt feet muzzle velocity at a given muzzle velocity the

8

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

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1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 17: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

range is a maximum at an angle somewhat differshy _ (U QlduAltitudemiddot (31)ent from 45deg lower for small ballistic coefficients q- J G(u)

uhigher for large ones However the range at 45deg is nearly as much as the maximum

Velocity increment l1u =KD8 G(u) (32)6 SIACCI TABLES ZG Spirt-stabilized Projecliles (KDS = 164 per rad)

(1) Tabllw Fllftctiofts In 18M the Italian Damping coefficient c = G(u)2u 03Col Siacci introduced the Space Time Altitude

tnd Inclination Functions (Reference 29) which Tht upper limit of integration U is A) iI torsimplify the calculation of trajectory data under Projectile Type 1 and 7000 fps for Tyres l andcertain restrictions In particular their use will 8 KDS is the yaw-drag coefficient defined by be explained for three conditions ground fire at

the formula low superelevations antiaircraft fire (where the superelevation is small) and aircraft fire These KD = Kn (1 + KD 32

) (34) and some auxiliary functions based on Glo Gu

where KDo is the drag coefficient for 0 yaw(the second revision of G2 ) and Gu (the first revision of G) have been tabulated for the Air a-is the yaw in radians Force (References 30 31 and 32) Since these

(2) Grmd Fie Gl Low Eln1GlionsSiacci tables were arranged primarily for use in computing aircraft firing tables they were called (a) FoJMlI1as Although the Aircraft Tables Aircraft Tables however they can be used for are not accurate in computing complete trajectories other purposes as explained below in lieu of other at high elevations they can be used to obtain trashyforms In these Aircraft Tables the argument is jectory data at superelevations below 15middot (for the the component u along the line of departure of the derivation and application of the following forshyvelocity relative to the air which is assumed moshy mulas see Reference 33) Here we shall taketionless The following functions and some of their derivatives with respect to u are tabulated p P~s the ratio of air density to normal asshy

sumed constant for each problem Space du

(28) aa-the ration of the velocity of sound toG(u) normal assumed constant for each

du problemTime (29)uG(u) If F is the temperature in degrees Fahrenheit

ru gduInclinationmiddot (30) aa =(459 + F)518 (35)ql = J u2G(u)

u Then the horizontal range is

x =(Cpp) cos 8 fp(uaa) - p(uaoaraquo) (36)

the time of flight is

tr = (Cpapa) [t(uaa) - t(uaoaraquo) (37)

the altitude is

y =x tan -80 - (Cpapa) [q(uaa) - q(uaaraquo) + x(Cpapa) sec -8 [Ql(uaaraquo) (38)

and the siope of the trajectory is

tan 8 = tan 80 - (Cppa) sec 80 [ql (uaa) - q (uaa)] (39)

The angle of departure for y = 0 may be found by formula

sin 8 = Cpa [q(uaa) - q(uaa ) _ ( fa)] (40)a p(uaoa) - p(uaoa ) ql ua

If pip ~ I and aoa = I let p = p(u) p = p (Uo) etc

bull Ia most places the altitude and incliDatiOll fuDctiom arc dcfioed a twice tbac iDteraJbullbull

9

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

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1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 18: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

--

Then these formulas can be expressed more NOTpound Since u is the component of the velocity simply

x =C cos 8 (p - Po) (36a)

tr =C(t - to) (37a)

y = x tan s - CS(q - q) + C sec s x QIO) (3amp)

tan ~ =tan -80 -- C sec~ (ql - qJ) (39a)

ind fo~ y ~ 0

sin -9 =- C [~- qlO ]P-PO

(h) Exam~l

nata Tank Gun 76-mm MIA2 M339

(4Oa)

Shot AP

Caliber 3000 in Mass 1458 lb Muzzle Velocity 3200 ips Form Factor 1164 on G~l

Air Density Ratio 1000 Sound Velocity Ratio 1000

Problem To find the range time of fti(ht angle of departure and angle of fall where the velocity is 2000 fps

Solution From the Aircraft Table Based on GI1 u p tq

2000 230793 65132 4890 3200 154251 34997 1616

Dift 76542 30135 3274

ql

06523

02637

03886

Ca1 = 14581164 (3000) = 1392 (Eq 22)

sin -8 = 1392 (327476542 - 02637) = 02283 (Eq 4Oa)

so =2326 mils cos so = 99974 secbullbull = HXXgt27

tan ~ = 02284

1392 ( UXXl27)( 03886) = 05411

tan ~ = -03127 (Eq 39a)

s =- 3184 mils

x = 1392 (99974 )(76542) = 10652 h (Eq 36a)

t= 1392 (30]35) = 419 sec (Eq37a)

Check x tan 8 =10652 (02284) = - C1 (q - q) = (1392)1 (3274) =

-

)

Ce1 sec -80 X q1 = 1392 (Ul0027) (10652) (02637)

y = 10

along the line of fire the tangential velocity is v =u cos scos

In this example v =2000 (99974)99951 = 2(XX)5 fps

lt3) Antiaircraft Fir

lta) FOrMvlos These tables can also be used for the flat part of antiaircrah trajectories where the superelevation is less than ISmiddot (for the derivation and application of the followi fonnushylas see Reference 33) Let pP and possibly C be known variable functions of x but assume a constant value of aa (either 1 or an average) Since PP is a function of y denoted by H its relation to x can be found by the approximate subshystitution

y - x tanmiddot-8 (41)

Let m =tan ~ m =tan bullbull

Then the following trajectory data can be found by Simpsons rule or some other method of nushymerical integration

x

p (uaa) =p(uaa) + sec -8 [~ dx (42)

o

f x

dx t = sec5o - (43)

u o

x

m =m - fgSU~middot dx (44)

o

x

v =[mdx (45)

o

2432

- 63440

= 39111

000 (Eq 3amp)

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

I~f f(26~31rol(2611) u

fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

-

y

112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 19: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

--

(b) Ex

Dta Auto_do (AA) 01lD 4O-mm M2Alj SIlo AP 1481 YuuIe V_ClUy 2870 fpl lWIillde eo~ 0574 OIl 0 up 01 Dnun 12lO Air o-a 8amp B- Ilow1d V~ Rado 1000

Problem To ftDd lhe 11_ of elcb~ loAd aldWde for bori_tal ranI flOln 0 to 2400 n Solution (See _u below 1oAd_ tbe AinnI~ Table B-d on 0 bull)

-p(u)[BAh

- shyu 26131It I Mh B m

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fpafamp shy lee I f~

1 4 1 6 7 82 a 9 10 11I0 000 17431te 28700 0910500lm 10000 0000 08290 0 241420 am bull 0 bullbullbullbullbull 00908 9T14

01 188bullbull 3gt1091 2~4 10681 0694eoo 9M3 1ld 591 I 21il52 1+13 900 02lI80 9337 bullbull 0 bullbullbull igt_iIDraquo ila8 ii4li7e 228601 DIO603UT3 1295 11Ol1 1416

04geII 891i 0 bullbullbullbullbull 1~ 0 bullbull bull bullbullbull I~~1 Q5GllO 8718 1111196 17163 15225 21322501186 231~ 231)82593

8621 0llG63 0 bullbullbullbullbull

8328 219826 274242 14137 18484 31432400 07MS 34166 43lt 22765j

Remarks

Col 1 The interval of x should be chosen small enourh so that the integrations may be performed accurately by Simpsons rule not more than 600 feet

Col 2 M =loglO e =043429 h =0000031shy58 ft_a The estimate of y = x tan ~o A slirhtly smaller factor would be better at the 10nrer ranges

Col J For convenience the formula H =antimiddot colorlo Mhy was used The density function H(y) has been tabulated (Reference 11) it gives the same values The ICAO Standard Atmosshyphere-Tables and Datal gives slightly different values

Col 4 Simpsons rule was used but the trapshyezoid rule gives 219330 for the last value

Col 5 The first value was found in the Aircraft Table for Uo = 2870 fps The other values were computed by Eq (42) with

sec ~OC bull l =261310574 =45524

Col 6 The values of u after the first were found in the Aircraft Table by inverse interpolation usinr the first two terms of Taylors series

Col 7 sec9 =26131 This is multiplied by 1000 to avoid writing zeros

11

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112

~ 4282

6664 ---J

Col 8 Eq (43) Simpsons rule gives 3131 for the last value but the trapezoid rule was used in order to obtain intermediate values

Col 9 The square of Col 7

Col 10 Note the factor 1()1 in these values Simpsons rule gives 4259 for the last value but the trapezoid rule was used so as to obtain more values

Col 11 Computed by Eq (44) with I1lo = tan ~o g = 32152 ft secJ

Col 12 Computed by Eq (45) Simpsons rule gives 5666 ft for the final value

(4) Aircraft Fire

(CJ) F orulas These tables are especially useful for aircraft fire (for th~ derivation and atgt plication of the follo ng formuas see References 34 and 35) Before using them the initial conshyditions must be determined Let

A-be the 4Zimuth measured from the direcshytion of motion of the airplane

Z-the zenith angle measured from the upward vertical

vo-the muzzle velocity (relative to the gun) w-the true air speed Uo-the initial velocity relative to the air 3-the initial yaw relative to the motion of the

air

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 20: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

The initial velocity and yaw may be found by the If h 15 rhe yawing tMmmt damping factorbull formuJu -the claquo) wind fora damping factor

u1 =v1 +wi + 2wv sin Z COl A (46) c= (h+ )2u (51)

a1 = (1 - sinl Z co A) wiu1 (rad)l (47) the )()sS in velocity due to yaw is

~u- ola (s-I12) Au (ua) (52)In jDrfl1tlld 6riag A = 0 Z = 1600 mil - a (s - 1) Cc + c (uaa)

u = v + w (4lla) Then the effective initial velocity i

(47a) u = u - Au (5t)

A = 3~ mil Z= 1600 Now we can find the distance measured aloni the line of departure to bull point directly above the

u=v- w (4amp) projecti1e

P = (CH) [p(uaa) - p (uaa) 1 (54)B=O (4ib) the drop of the projectl1e

The ail density ratio H and the sound velocity Q = (CaeHa) [q(uaa) - q(uaaraquo)ratio aa may be taken u coastanta Approxishy

mately if Y is the altitude of the airplane above - (CaeH) Pql (uaa) (55) lea left and the time of Sight is

H =e-u h = Oltxxgt031S8 ft-I (48) t = (CaeHa) [t(uaa) - t (uaaraquo) (56)

aa = e-Ilrbull k =OltXXgt00301 ft-I (49) The horizontal and vertica1 compoaenta if deshysired may be found by the fonaulu

If is the standard stability factor which cor- x = P cos ie (57)respoads to the muzzle velocity muzzle spin and standard sune air deDIity the initial stability y =P sini- Q (58) factor is with the angle of departure detenniDed by the

=bullbulla H (SO) formula

coal Z tanS = (aiDZainA)2+ (aiDZcosA+wv) (59) - 01

eDt = (tan Z sin A)I + (taD Z COl A + wIT cos Z)I (59amp)

~

~ -

12

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

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1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 21: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

(b) EIGllltI 2e = 34093 - 3)65 = 32028 fpe (Eq 53) c1H = 023503871 = 06061Data claHa = 0606109137 = 06633Azimuth lZO mila (c1aHa)1 = (06633)1 =04400Zenith Angle S)() mila

Muzzle VeJocity JOOO Epa PH~1=IZOO~I=I~9ft

Air Speed lcm fp uIIa = 33)2809137 = 35053 fIN Altitude 30000 It Find p(uaa) in Table tbeIl p(a) by Eq

54Stuldard Stability FlIdor 366 Dunpiar Factors h + a 106 aec-1 uaa p t q h

at JOO) fpa 31743 1S~5 3548 1657 L~ti

BaDiatic Coefficient 0235 on Ga1 35053 136006 29~5 1184 C~l1 19799 0593 473 057Problem To 6Dd the time of 8icbt aDd drop for

a SilIcci (P) at lZO it t = 06633 x 0593 = 0393 sec (Eq 56)

Solutioa (Ule the Aircraft Table Baled on 04400 x 473 = 208 06633 x 1~ x 002114 = 168Ga1) Q = 40ft (Eq 55)COl A = 038268

sin Z = 070711 (c) lero~ The derivatives listed in the Aircraft Tables should be used for iDtershy

SiD Z COl A = 027060 polating backward or forward from the nearest

2wv = 2 x 1000 x 3000 = 6000cm tabular value of the argument For instance in v1 = (JOOOI = 9000000 the last ~ple it is desired to find p for u =

35053 and then to find u for p =1S~5 Fantwi = (1000)1 = 1000000 the table gives

2wv sin Z cos A = 1623600 at u = 3510 P = 1357281uS =11623600 (Eq lt46)

u --= - 5923= 34093 fIN I = 072940 x 100000011623600 = Hence ~u = - 4j ~ = + 2784_ 006275 (Eq 47) aad at u = 35053 P =1360065 Ie = 02505 rae (2552 mils) (1 rad = Thea we have P = 1S~5 10186 mils) aad the table gives bY =000003158 x 30000 = 09474

p = 1S6062 ~ = - 6044 at u = 3170 H = 03871 (Eq 48)

Heace ~p = - 2Sj 60= +43kY = 000000301 x 30000 = 00903 aacI u =31743 aa = 09137 (Eq 49)

Ie = 366 oX 900000011623600 x 03871 = 731 (Eq 50)

c = 1062 x 3000 = 000177 ft-1

~a = 3409309137 =37313 fIN ~u(uaa = 14003 sec-1

(from Aircraft Table)

c(uaa) =2288 x 10-1 ft- 1

(from Aircraft Table)

~a = 006275 x 09137 631 x 0235 x ~1~~00002288 = 005733 oOO2d~~ooo023 3)65 fps (Eq 52)

13

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

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tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 22: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

b F-stabilued Projectile (I) Tabtdor FllfletWtS R~erence 6 (ontains

a tahl~ of modified Siacci functions baaed on the Cirag coefficient for the S()mm High Explosive Antitank Shell T1OB which has rigid fins These tables can be used for other similar projectiles although they are not suitable for all fin-stabilized projectiles The following functions and their derivatives are tabulated as functions of Mach rumber M

27

Space S= [ dM

MKraquo(M) (60)

M

27

Time T= [ dM

MlIKraquo(M) (61)

M

(62)Inclination 1=

27 I(M)dM

Altitude A= (63)[ MKraquo(M) M

The factor in the inclination function is ga =321S4112n27 = 00287 sec-i

loPI seclI shyy = x tan a - 2 ~i [A(M) - A(M)]ap

tan a= tan a - loPee a I(M) - HM)] a Pl

( 2 ) AIplkGliofi (a) Foulas The following formulas are

applicable for computing trajectory data at supershyelevations below 15middot

ut m be the mass of the projectile in pounds i-the fonn factor of the projectile d-the maximum diameter of the projectile in

feet v-the velocity of the projectile in feet per

second

v-the muzzle velocity in feet per IIeCOIld a-the velocity of sound in air in feet per second p-the density of air in pounds per cubic foot a-the angle of inclination of the trajectory a-the angle of departure

Abo let lo = 112027 ips p = 007513 Ibft

M = va

M= v cos aa cos a 1 = pidlm

Then the horizontal range in feet is

x = (pn) (S(M) - S(M)] the ti~ of flight in seconda i

(64)

(6S)

(66)

(67)

t = (P sec aapl) (T(M) shythe altitude in feet is

T(M)] (68)

ampoP secl a+ xmiddotJ bull I(M)a Pl (69)

(10)

The angle of departure for y = 0 may be found by the fonnula

sin 2a = 3oP [ A(M) - A(M) _ I(M)] (71)allpl S(M) - S(M)

Ifp=p and a=a let S=S(M) S= tan a= tan a - seeI a (I - Ie) (tIa)S(Mo) etc Then these formulas can be exshy pressed more simply and for y = 0

x = (ll)(S - 5) (67a) bullj2 2[A-A]

~ t = (sec aal)(T - T) (6amp) sm a = 80l S_ S Ie bull (11a)

middoty=xtana- secJ~ (A-A) +x seela Ie a1 l

(69a)

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

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1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 23: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

(b) E~~

Data Gun 9O-mm SbcIl HEAT TI08E1D

Caliber 029525 It

Ma 142

Maule Velocity 2400 fpe

Form FKtor 100 on Gn Air Dmaity 007513 Ibamp-SoaDd Velocity 113)27 fpe

Problem To fiDei the ftIocity time of flicbt angle of cIeputure aad ucte of faD at a ranee of 3000 feet

Solutioa From the Table of the Siaai F hued 011 SbeIl 9O-mm HEAT TJOJ

II 5 T A I Ij3650 3orJ196 1427502 02537 01923 214234shy 1-0836 0109983 Q067O Q0851 ---Dif 1J836OM Oj11519 01867 01072

- Me =2laquo)()113)27 =214234 (Eq 64)

T =007513(100) (029525)142 = Oooo-t612 ft- I (Eq66)

T = U3)27(Oooo-t612) =051667 1Ilamp-1

y =051667(Oooo-t612) = 000023829 ft-1 1Ilamp-1

-S - S =TX =0CXXgt-t612(3(00) = 138360 (Eq 67a)

2 [001867 ]l1liraquo = 051667 138360 - ()(QISl

=001928 (Eq 71amp)

21= 1964 mils =982 mila em= 099995

1Ilamp = 100005IIItJl bullbull =100010

000964 100010

- 051667 (om072) = -002015

tall=

tall = - 001111 (Eq 0amp)

bull=- 1132 mils em =09994 v = 112027 (lj36S0) (099995) (099994)

= 194537 ips (Eq 65)

te =~= (OjI7519) = 13S911lamp (Eq6amp)

aeck x taD =3000 (00964) =2892 ft ~ (A - A) 1CXXgt10(OO~867)

- y = - OCXXgt2J829-shy

= -7836ft

x sa I _ J(XX)( 1CXXgt10) (0QOSS1) T - 051667

=+ 4942 ft y=2892 + 4942 - i836 =- om ft

(Eq69amp)

7 DIFlEUNTIAL EPncn Some of the eftects on ranee and defi~ltm

caUled by ~ from staadard CIODditioas will be ctilCllEsed and explained Mcft detailed exp1aDatioaa are giftll in Refaences 2 22 23 and 24

CJ E8laquob 011 RtMg

(1) HgIU of Targd Two methods may be used for determining the eampct of ~ height of the target with respect to the lUll OII~ by meaoa of the trajectory chart uad another by n co~

to the aagle Of deputure (a) For ~ variatioaa in height the trashy

jectory chart should be ued The trajectory that passes throucb the point dctermiDed by the cMn horizoDtal raIJIe aad altitude can be found The total ~ of this trajectory is the ~ where it croaes the axis The diJlaeDtt bdweaa the gival ~ aad the total ranee is the eht of the height of target For greater accuncy the ashyterior ballistic tables may be used in lieu of the charta

(b) For small ~tioaa in height an ~

proximate effect may be fouacl by adding the aacIe of site

bull = taD-I (HR) (72)

to the angle of departure obtaiDiIc the corshyreeteC ancte

=+a (73)

Here H is the height of target Rr-tbe map range

--the angle of departure corTeSporuing to the map raaee in the ~or Ballistic Tables

the angle of departure conespwdiug to the COl iected nmce R

Then the effect 011 rauge due to height of target q

AR = R - R (74)

15

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

-

=Mmiddotmiddot---j ZIII-----Cl-t PROJECTILE TYPE 8

90-mm HEAT SHELL TIOS

ALL DIllE IN CAL_

Figure 1 Projectile Shapes

--

05

middot15

N

N

10

KD

15

bull10

-1

~(

tT

l

---r~

--1

-I

I I

i 1

-

_~

1-

---+p~~-~r+1

i-H

i -

~

bull

tf-1t

iMtH

-++J

=

-~

rr~

---

+T~

i~~

TTT

shy

1-1-

1-++

-

-shy

-~

00

0

5 LO

15

2

0 u

10

1

5

40

4

5 aD

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ure

l

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M

ach

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~

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i ~50 ~ III

~

40

30

20

10

2 8 8 LO r2

t 1-1-

-1 -i T l I 7 -~J- i-

I

LOG Cg

Figure 3 Time of Flight for Projectile Type 1

--~ i

110

140

120

--- --

80

40

20

o -04 -02 o 2 A 8 10

LOG C

Figure 4 Time of Flight for Projectile Type Z

Z4

I

i 100 o

10

-l-+--

H

eo

- shy

40

20

I

o -002 o 02 4 oS 08 10

180

120 ampl

~ -+~ t-+-middot looK

~ 04

-I bull i

t

LOG C

Figure 5 Time of Flight i)r Ptojectile Typa 8

zs

-- en

c gt

0 0 0 shy -IV

0

-Iamp

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o

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4

i

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 24: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

(2) Eletnuiots Since the ExIJcrior Ballistic - abIes give the range as a faoctioa of eJevation for

ntant values of muzzle Ydocity aod baDistic cocfficient the effect of aD incrcax in elevation may be found from the diftOelaces At short ran~es tht effect may be COdlpIftild -IDOre acshycurately by using tht Siaoci tables as aplaincd bove Th~ vacuum mnula (Eq6) may be uscshyful in estimating the effect rspeciaDy for ~

balhgttic ccxfficients It shoukl br DOftd that the effect is srlall in the -icinity of the maximum range and of course is oegatift at elevations above that corresponding to the olhiodlol rauge

( 3) MtlZzle VeJocity SiDce the Exterior Balshylistic Tables give the range as a f1IIXtioa of DnJZZIe velocity for constant faIacs of cIentioo and ballistic coefficient the effect of an increase in muzzle velocity may be found ampom the diflCICIICa At short ranges the effect may be computed by using the Siacci tables In YaCUdID the range is proportional to the square of the ftIocity as shown in Equation 6 in air this is a good approximation if the ballistic coefficient is large

(4) Ballistic CQefinewt Siner the Exterior Ballitlc Tables give the ~ as a faoction of ballistic coefficient for coostant values of muzzle velocity and elevation the effect of an increase in log C may be found from the c1iBtabkb At short ranges the effect may br computed by using the Siacci tables It is customary to find the efffCt of a I increase in C whidl is eqainImt to an increase of 000432 in log C

(5) Weight oj pojcIile An iucrase in weight of projectile dcercases the muzzle Ydocity and increases the ballistic codIie ient

The effect on muu1c vdocity may be expesaed

Apvo = nvo(Ap)p (75)

where Vo is the muu1c velocity

p is the projectile Jteicbt n the logarithmic diftaeutial meffmiddot imL

The value of n may be oIIqjnrd ampom iatelior ballitic tables It is appiocincdrly - 03 for a rifled gun with multiperfonkd propellant grains - 04 for a rifltd guu with siacJe-pofuaabd grains - ()47 for a smooth bore mortar with flake propellant and - 065 for a JIlOiI1rss ri8e with multiperforated gnUm

Since the ballistic roefficirnt is pruportioaaI to the projectile weight by defirritim EqaatDa (22)

the effect 01 C nay be expressed

~C =C(Ap)araquo (76)

If ~R is the effect 011 nncc of 1 unit incnue in muzzle velocity tJ tbr effect 011 ~ of IS incnue in ballisti cocfticicnt the died OIl raace afan illCfQSe in projectile weight is

6pR = I1R(~) +6oR(100 ~C)C (77)

(6) Air DnuUJ The retardation doe to air rcsistantt is propJrtioaal to the air deasity and inversely proportiw to the baJlistic uwftgtc ieat as indicated in Eq (25) Theiefo~ to a first approximation the effect on ~ of aD iacrase in air density is equal to the effat of the 8IIIIl

percelltage decrase in C (7) Air TerapertJltr An increase iD the

temperatun of the atlnosphcn affects the in two ways it iocrcascs the density of the air aad the velocity af sound TIle temperaton of die air may affect the taupeiature of the propcIIdt which affects the muzzle Ydocity bat ttt is aD

interior ballistic problem

For a givm pressure and humidity the deusity is proportional to the absolute temperature The eifect of density on range has been treated aIJoft

For a given humidity the velocity of IOIIDd is proportional to the square root of the aheolute temperature For a given projectile ftIocity the Mach number is inva-sely proportional to die acoustic velocity A change in M prodnas a change in the drag fuDction A leW trajeclory could be computed with the varied fuDction howshyever it is simpler to use an approximate fonnuJa deduced from a semi-anpirical formula daiftd by Dr Gronwall ~

~R = 01929 [OOIR - OOOSvAR - (I -OOOOOlSy)4oR]A-r (78)

where R is the

~R -the incrase in nDge due to wease m tonperatare

v-----tbe mazzle veIocifJ in fed per

~R-the effect OIl R of 1 fps iDcreue ill v

yr-tbe maximum ordinate in feet AcR-the effect 011 R of 1~ inaeue ill Co Af-the i~ in tonperatare in ees

Fanrenheit

16

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

---1----132-----oIl-c

PROJECTILE TYPE I

-1------shy --5J-----------shy

1--LI---FA -

1 ----270-------l~

PRO-ECTILE TYPE 2

------3bull---------4-1 067 Ri

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 25: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

(8) WiU A rear wiad baa tbfte dfccts it aea the ~ SJID aJDac with it rcJashy1M to the eutb it iDcraIa tbe qIe of ckshymare rdabYe to tbe air it decreucs the ftIocity mtive to the air The total OIl JUIIe may be expRMed folio

sin ~R ~R]AJl=W T+----coa-[ y 4t poundAV

(79)

wIae W is be JUIIe ~ of the wind (a rear wiad is positive bull wad wiad is aqatiYe)

T time of 8ipt

aacIe of deputure Y-dIe muzzle velocity

AR dfect oa ranee due to a cbange of ~ ndiaas in

u eftect 011 raaee due to a cbaaee ~v in Y

f) Eedl _ D~dWa

(1) WiU A crosswiDd has two effects it moves tbe coorctinate system with it aud it changes the directioa of motioa relative to the air The IlDtaI effect 011 IiDear deampdioa may be expressed

AZ =W (T - Rycos ) (80)

where W is the douwiDcl The qaIar deSectioa dae to wiDd in radians

ia

0= W (TR -lycos) (81)

(2) Drill After the yaw due to ioitia1 disshyt1Ubaaca has damped oat a spUming sheil has a yaw of repose due to the ClllYat1lre of the trashyjectory This yaw is mainly to the right of the trajerlory if the sbeIl has rigbt-baDded spin to the left if it bas left-handed spin Itmiddotmay be deshytermined at short ~ by 6riag alternately frau bands with right aud left hand twists of riftmc or at Ioac ruga by COl letting the ~

served de6ectioo for the effeds of wind CUlt of tnmnions aDd rocatioa of earth

The difleseutial equation of motion ir the drift l iaII

_ 2qAyLN Gpi (82) Z =ampJJdnaIMN It - Ie

when C is the eravibtional accelerationbull

A-the axial iIICJPleOf of inertia

v-lthc azzlc yclocity

L-tbe crouwind bu (lift)

N-thc spiu

N--thc iaitial spin

m-tbe mass of the projectile

d----laquobe caliberbull u--tbe ftIocity of the projectile rehtiv ~ 0 the

air M-tbc overturniDg moment about the ccoter of

graYity

x-tbe ~l ranee Cr-tbc drag fuoctioo p-1he air ckasity

p-the staDdanI air density (007513 IbftI)

e-tbe baDictic ~

Dots dade time daiwatives and the initial conshyditioas are

z= OZe =O

c BoIJisIie DnuitJ reralflre tuJd Wind Iu tJatiag the effects of variations in the

atmospbrre it has hem assumed that the percentshyage Yariatioos from stmdard density and temperashytuft aDd the wind are coastaat all along the trashyjedOry AdaaDy they vary with altitude so that weigbtal mcaa nlucs must be used The wcigbtiag fadon are cktamiaed by the proporshytioa of the toQI effect that a variation occurring iu each alritade mae woaJd have Instead of computiac a set of weiamphtiag factors for each trashyjectory a few npiuentative curves are used The sum of the prodacts of the zonal variations by their weightiug fietors is called the ballistic deasity taDperatiIJe or wiud The results are thea ~ as coastaDts in computing the effects aD nmampe aad defkdion

17

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 26: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

REFltIlENCPs

InlunailtJlla Cvil Avial(ft1 OrKaniulion Standard 17 lalurw Ilteport Nobull 11 and 1429 of the Gavre Atmlgth~r~ Tal and )a~ lor Altltud~ to comoinioll (AUI 1897 and July 1898) TheK were 15IlOO lerl 1~Kley Aeronautical Lab NACA the origin I sources of information contained in ref Hmiddot J235 (I~S51 I bull

2 D-silln for Control of Flight Characteristics III Garnier Calcul des trajectoires par arca Giwe ODP ~1-246 (Art Am Series Ord Eog Des Comm (I~17)

Handbook I (1957) 19 EXlerior Iallisti Tables based 011 Numerical Inshy 3 Dng COtffic~nl HI Aberdccn Proving Ground tegratior Vol 1 Ord Dept of U S Army (1924)

BkL Fil~ oj 1middot50 (1942) Table la Log G(V) Table Ib d log G(V dV)

~ Orag ComiddotfIi(l~nl B2 Aberdeen Proving Ground BRL File -middot-5l il942) Drag Coefficient Bu File 1-1-86 (1945) Drag Coefficient Bu File N-I-IOS

20 Herrmann E E Ran~ and Ballistic Tables I S Naval Academy (1926 19JO 1935) Table I Thl Gavre Reardaticn Function Gv

ll946) 21 Woulton F R New Wethods in Exterior BaJJistics

5 iarringtol M E Drag Coefficient BI Aberdeen Pmiddotoving Ground BRL File N-I-69 (1943) Drag -)efficien B ) File N-I-89 (1945)

G Odom C T Drag Coefficient KI)f and Siacci Funcshylions for a Rigid-fin Shell Based on the Shell9Omm HEAT TUll Aberdccn Proving Groand BRL MR-882 (Rev 1956)

70rd Dept li S Army Exterior Bamstic Tables bHed on Numerical Integration Vol 1 WashingshyIm War 1Jept Document 1107 Om) G-Table A~rdeen Proving Ground BRL File NmiddotI-40 (1945)

Univ of Chicago Press (1926)

zz Hitchcock H P Computation of Firing Tables for the U S Army Aberdeen Proving Ground BRL X-IOZ (9z4)

23 Hayes T J Elements of Ordnauce New York John Wiley aDd Sons (1938)

24 Bliss G A Wlthematics for Exterior Bllistics New Yorl John Wiley and Sons (1944)

25 Ord Dept U S Army Exterior Ballistic Tables based on Numerical Integratio Vol II Washingshyton (1931)

Table of G BRL Fik N-I-92 (1945) (These tables 260rd Drraquot U S Anny Exterior Bamstic Tables pertain to Projectile Type 1 Doc 1107 has log G1 baed on Numerical Inteeration Vol III Aberdeen with V in ms N-I-lttO has G1 with V in ms PraYing Ground BRL (1940) N -1-92 has GI with V in yds) D Brief Exterior BaJJistic Tables for Projectile TFPe

8 (2-Table Aberdeen Proving Ground BRL File N middot1-20 (1944) Table of Gr File N-I-93 (1945)

9 Harrington M E Table of G Aberdeen ProYine Ground BRL File N-I-68 (1943) Table of Gu

I Aberdtfn Proyi Ground BRL File N-I90 (1945)

2amp Exterior 3aJJistic Tble for Projectile Type 2 Aberdeen PlOviDg Ground BRL WR 1096 (Rev 1957)

File N-I-96 (1945) 29 Siacei F Corso di balistica ht ed Romc (1870 10 Martin E S Bomb Ballistic Tables Aberdeen to 1884) 2d ed Turin (1888) Frenth trans

Proving Ground BRLM 662 (1953) P Laurent Balistique extuieure Paris (1892) II 1 H-Table Aberdccn Proving Ground BRL File 30 Aircraft Table Based -on G Aberdeen Provin

N-II (1942) H-Table File N-I-1I4 (1950) Altishy Ground BRL File N-I-Ill (1955) tude is in meters in N-II yard in N-I-114) 31 Aircraft Table Based OIl G 2 Aberdeen ProYing

12 Charbonnier and GOlly-Ache Wesure des Yitesse de Ground BRL File N-I-I21 (i9S5) projectiles Part 2 Book III Wan de Iart de la 32 Aircraft 7able Based on Gu Aberdeen Proviac marine JO I (1902) Ground BRL File N-J-I26 (1955)

13 Jacob Une solution de problme balistique Chap II 1 Wen de Iart de Ia marine 27 481 (1899)

1bull Note sur la ddermination expbimentale do coshyefficient de 1a risistalltt de Iair dapra les clemiera etudes de Ill commission dexpa-iences de GiYft Mem de rart de Ill marine 27 521 (1899)

IS Charbonnier Note sur Ill resistance de rair au mouvement de projectiles Men de fart de la marine J3 829 (1895)

16 Ingalls ] M Ballistic Tables Art Circular 1l (Rev 1917) Scc p III af Introduetioa

33 Hitchcock H P and Kent R H Applicatiou of Siaccis Methad to Flat Trajectories Aberdeea Proving GrOUDJl BRL R-1l4 (1938)

34 Sterne T E The ESect of Vaw Upon Aircraft Gunfire Trajectories Aberdeen Proving Ground BRL R-J45 (1943)

35 Hatch G and Gru R W ANew Form of BIshylistic Data for Airborne Gunnery Mus lnlt Tech Instnuncntation Lab R-tO (1953) (Coaf)

36 r~()n_lI T H An Approximate Formula for the l~ Variation due to a Chance in Temperature ~a5hingto OrcL Office TS-161 (1921)

bull r-middot

18

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

r------smiddot28-----

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 27: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

GLOSSlRY of cIepattan (elnatiaa) A ued in this

pamphlet tIwR terms mean -gil 01d which is defined ampI the angle between the horizontal and the line along which the proshyjectile leava the projector ODe of the two initial conditions 01 a trajectory the other conshydibOll beinc iwiIidI wllaquoil

For a roeIaet-fired projectile in wbicb the pr0shy

pellant bunUac CClIltmua after the rocket leaves the launcher it is CSuy to make ~

middottiona relative to the point at which the rocket becomes a missile in free yent aod the velocity attained at that point

1JIC1e f ilaclillau The angle between the horishyzontaJ and the tangalt to the trajectory at any point At the origin of the trajectoly this is the same as the tJ1IIfIlI 01 dHJrl1W

apical lt_I-apkal) aqIe In general the angle formed at the apex or tip of anything As apshyplied to projectiles the angle between the ~shygelts to the Olrft oudining the contour of the projectile at its tip or for semi-apical angle the angle between the axis and one of the tanshy- gents For a projectile haYing a conical tip the cone apex angle

wtica Branch of applied mechanics which deals with the motion and behavior chancteristics of missiles that is projectiles bombs rockets guided missiles etc and of accompanying pheshynomena It can be conveniendy divided into three branches -ildnior ballistics which d2ls with the motion of the projectile in the bore of the weapon utnior ballisIics which deals with the motion of the projectile while in flight and tifQl ballistics which is concerned with the efflaquot and action of the projectile when it imshypacts or bursts

crosswind force The component of the force of air resistance acting in a direction perpendicular to the direction of motion and in the plane deshytennined by the tangent to the trajectory formed by the center of gravity of a missile and the axis of the missile (This plane is calkd the plane of yaw)

drag The component of the force of air resistanCe acting in a direction opposite to the motion of the center of gravity of a missile

)natiaL See lIfIgu 0 dIJrlwbull

exterior Wsdca See bGllistics

blirizollta1 rage 11le horizontal UlmflODcn middotf the ltiistanee from the beginning of the tTdjatut (poiat of origin) to auy other pomt 00 tlc trashyjectory

iJaitia ftlodty (muzzle velocity) 1Dc projccti1e velocity at the moment that the proj~t ~ e1ses to be acted upon by propellingfones

For a gun-fired projectile the initial velocity expressed in feet or meter$ per second is called ffampauzle velociy or ifliti4l vloci It is obtained by measuring the velocity over a distance forshyward of the gun and comcting bade to the muule for the retardation in Bight

For a rocket-fired projectile the velocity atshytain~ at the moment w11m roclcet burnout ocshycurs is the initial velocity A slightiy fictitious value is used referred to an assumed point as origin of the trajectory

The initial v~locity of a bomb dropped from an airplane is the speed of the airplane

llIapu force The component of the force of air resistance acting in a dirlaquotion perpendicular to the plane of yaw (see crossuMul force) It is caused by the action between the boundary layer of air rotating with the projectile and the air stream This force is small compared with drag and crosswifld force

muule ftlodty The velocity with which the projectile leaves the muzzle of the gun See it~ wociy

slant range The distance measured along a straight line from the beginning of the trajectory (point of origin) to a point on the trajectory

stability factor A factor which indicates the relashytive stability of a projlaquotile under given condishytions It is dependent upon the force momertts acting to align the projectile axis with the tanshygent to the trajectory and the oYertuming force moments For the projectile to be stable the stability factor must be greater b1an unity

standard atlusphere An average or representashytive structure of the air U$ed as a point of deshyparture in computing firing tabl~ for projecshy

19

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 28: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

- -

tiles The standard atn~adopted ill 1956 r the Armed Services and DOW known as the

l S Standard Atmosphere is that uaed by the i~(emational Civil AYiation Organization (ICAO) This Standard AtmoIpbn-e aaaumes a ground pressun of 7(1) mm of mercury a ~ound temperature of ISdeg C air dauity at ground level of 0076475 Ibft aDd a taDpcrashyture grallirot to the beginniIIc of the ~

phere expressed by the formula

absolute temperature T(OK = 28816-6SH

where H is height above sea level in Jn1ometas ~n the stratosphere (above II kilometers) the

temperature is assumed ttIOStaDt at 21666deg Ie For firing table purposes wiad eIOCitirI of zero are assumed

porei~_tiClll An I(~ded positive angle in aatishyaircraft gtm~r) that COR(l(nSlltes for the faD of the projectile dunng the time of Raght due to the pull of gravity the angk the gun or projector must be elevated above the gun-targd tiDe

trajecterymiddot The path followed in 5pQICe by the aDtel of gravity of a missile while ill free 8icht

yaW 1ne angle between thc direction of moboIl of a projectile and the axis of the projectile ~

ferred to either as cr more claquolIIlpIetdy tJAgk 01 yatI1 The angle of yaw incnases with time of flight in ~ UDStab1c projectile (see bilily lactor) aad dccnascs to a aJOstant nlae caI1cd the jOII1 01 nfHne or the re~ u of yorv in a stable projectile

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 29: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 31: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 33: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 35: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 36: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 37: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 38: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 39: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 40: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 41: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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49

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 42: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 43: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 46: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 49: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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49

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 50: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 51: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 52: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 53: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 54: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 55: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 56: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 57: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

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ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 58: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

)

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1
Page 59: AMCP 706-140 Trajectories, Differential Effects, And Data for Projectiles

ENGfNEERING DESIGN HANDBOOK SERIES The Engineering Detiign Handbook Series is intended to provide a compilation

of principles and fund~~ental data to supplement experience in assisting engineers 1n the evolution of new designs which will meet tactical and technical needs while also embodying satisfactory producibility and maintainability

Listed below are the Handbooks which have been published or submitted for publishycation Handbooks with publication dates prior to I August 1962 were published as 20-series Ordnance Corps pamphlets AHC Circular 310-38 19 July 1963 redesignated those publications as 70b-series AMC pamphlets (eg ORDP 20-138 was redesignated AHCP 706-138) All new reprinted or revised handbooks are being published as 706-series AHC pamphlets

Gelleral and Milee11aneous Subjects Ballbtic Mluile Series

Number Title Number Title 106 Elemenu of A~nt Engineering Part One 281 (S-RDI Weapon Syetem EUeCtivenell (U)

Soutces of Energy l82 Propuls ion and Prope llampJIti 107 Elem_s of Armament Engineering Part Two 284(C) Trajectories (U)

Ball18tics 286 Structuree 108 Elements of Armament EngIneering Part Three

Weapon Syeteme and Components Ballietic8 Serie 110 Experimental Statistics Section I Basic Conshy 140 Trajectoriee Differential Effect and Data

cepts and ~lysis of Measurement Data for PrOjectile 111 Experimental Statietics Section 2 Analysis o IbO(51 Elements of Terminal ampllbstice Part ODe

Enumerative and Classificatory Data Introduction Kill Mechaniams and liZ Experimental Statistics Section 3 Planning and Vulnerability (U)

AnaJysis of Comparative Experiments 161 (S) Elementa of Terminal Ballistice Part Two 113 Expe rimental Statistic s Section 4 Special Collection and Analyis of Data Concernshy

Topics ing Targets (U) 114 Experimental Statistic s Section 5 Tables 162IS-RD Elements of Terminal Ballistics Part 134 Maintenance Engineering Guide for Ordnance Application to Millile and Space Targets

Design 135 Inventions Patents and Related Matter Carriages and Mounts Series 136 ServomechaDiems Section I Theory 34i Cradles 137 Servomechaniems Section 2 Measurement 342 Recoil Systems

aDd Sigw Converters 34 3 Top Carriages U8 Servomechaniems Section 3 Amplification 344 Bottom Carriages 139 Servomechanisms Section 4 Power Element 345 Equilibrators

and Syetem Deeign 346 Elevating Mechaniams lTO(C) Armor and Itl Application to Vehicles (U) 347 Travering Mechal1iem Z70 Propellant Actuated Devices Z90(C) Warheads--General (U) Materials Handbooks 331 Compensating Elements (Fire Control Series) 30 I AlumInum and Aluminum Alloys 355 The Automotive Assembly (Automotive Series) 302 Ccvper and Copper Alloya

303 Magnesium and Magneelum Alloys AmmW1ition and Explosives Series 305 Titanium and Titallium Alloya

175 Solid Propellants Part One 306 Adhesive 176(C) SoUd Propellants Part Two (UI 307 Gasket Materials (Nonmetallic) 177 Properties of Explosives of Military Interest 308 Glass

Section 1 309 Plastic s 178(CI Properties of Explosives of Military Interet 310 Rubber and Rubber-Like Materials

Section Z (U) 311 Corrosion and Corrosion Protection of ZIO Fuzes General and ~echanical

Z11(C) Fuzee Proximity Electrical Part One (UI Surface-to-Air Missile Series ZlZ(5) Fuzee Proximity Electrical Part Two (UI 291 Part One System Integration 213(5) Fuzee Proximity Electrical Part Three (U) 292 Part Two Weapon Control Zl4 (5) Fuzee Proximity Electrical Part Four (U) 293 Part 1hre Computers Zl5(C) Fuzes Proximity Electrical Part Five (UI 294(S) Part Four Millile Armament (UI U4 Section 1 Artillery Ammunition--General 295(S) Part Five Countermeaeuree (U)

with Table of Contents Glossary and 296 Part Six StlUctures and Power Sources Index for Series 291 (S) Part Seven Sample Problem (U)

U5(CI Section 2 Design for Terminal Effects (U) U6 Section 3 Design for Control of Flight Charshy

acteristics U7(C) Section 4 Design for Pro)ection (U) U8 Section 5 Inspection Aspects of Artillery

AnunW1ition DeSign U9(C) Section 6 Manufacture of Metallic Components

of Artillery Ammunition (U)

  • AMCP 706-140
    • AMCP 706-140
      • AMCP 706-140-1
        • AMCP 706-140-1
          • AMCP 706-140-1