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REPORT No. 236

TESTS ON AIRPLANE FUSELAGES, FLOATS AND HULLSBy WALTER S . D IEKL

B urea u of Aer on aut ics, Na ~ D epa rt men t

129

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REPORT NO. 236TESTS ON AIRP LANE FU SE LAG ES , FLOATS AND II I ILLS

By WALTER S. DIEHL

SUMMARYTh is r epor t is a com pila t ion of t est da t a on a ir pla ne fusela ges, n aceI Ies , a ir sh ip ca rs, sea pla ne

floa ts, a nd sea pIa ne huk, prepa red by the B urea u of Aerona ut ics, a ti t he request of the hTa tiona lAd vis or y C om mit t ee for Aer on a ut ics . The discussion of the da ta jneIudes the deriva tion of asca Ie correct icm curve to be used in obt a ining the full sca le dra g. Composit e cur~ es of dra ga nd L I D for floa ts a nd hulls a re a ko gi~ en.

INTRODUCTIONIn order t o ma ke a n a ccura te est ima te of the proba ble performa nce of a n a irpla ne, the pa ra -

sit e dra g must be know n. When w ind tunnel t est da ta a re not a va ila ble, this pa ra sit e dra g mustbe obta ined by some process of summa tion, a nd in such a process one of the la rgest a nd mostuncert a in it ems is the dra g of t he fuseI a ge, or simiIa r pa rt s, such a s the na celles, hull, or ffoa ts.The usua l pra ct ice is t o compa re t he desired design w ith other a nd simila r designs for w hich testda ta a re a va ila ble.

k 1922 t he B urea u of Aerona ut ics compiled a ll of t he w ind t unneI t est da ta then a va ila bleon fusela ges, hulls, na celles, a nd floa ts, into a form w hich w as convenient for rea dy reference.This compjI at ion w as of such va Iue t b at t he l44a tiona IAdvisory C ommit tee for Aerona ut ics ha sseen fit t o request it s relea se for publica tion a s the first of a ser ies of report s, giving w ind tunneltest da ta of t his t ype in condensed form.

For convenience in referen ce t he models ha ve been divided int o seven groups, ea ch desig-n at ed by a let ter ris f ollow s:A.Ai rp lane fuselages .B .Air pI a ne fu sela ges w it h a ppen da g es .C.Nacelles. ,.D. Fjns.E .Air sh ip ca r s.F .---Seap lane f loa t s .G .-S ea pI ane hulls.

E a ch modeI is designa ted by a group let t er a nd a number , t hus AL, i. e., a irpla ne fusela geNo. 1, or F+ floa t No. 4 TEST DATA

For ea ch modeI the source of the t est da ta , the sjze of the model, a nd the test speed a re givenin a ddit ion to the t est da t a . Whenever pra ct ica l, the dra g is given in pounds a nd pounds persqua re foot a t some specified w ind speed.

The da ta from B rit ish t est s a re frequent ly in t he form of ~ orma I force Z a nd longitudina lforce X. When necessa ry t hese can be convert ed to lift a nd dra g by t he usua I formula s:

L=.Z COSf?-.~ SiI16 (1)D =XCOS $+23 sin o

Vlhere o is the a ngle of pit ch. 131

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132 REPOR.T NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSCorrect ions for pressure drop a long t he w ind t unnel a xis ha ve not been a pplied t o a ny of t he

t est da ta in this report . S ince it w ould ra rely be more t ha n t he experimenta l error , t he omissionof this correct ion is a ppa rent ly just ified for a Il models w hich devia te a pprecia bly from t he con-ven tion a l st ream lin e forms . For exa mple, on t he floa t F1 t he ma ximum possible correct ion forpressure dr op a t 58.7 f. p.s. is a bout 0.0007 pound, w biI e t he a ct ua l correct ion is somew ha t less,due t o loca tion of m odel during t est s. S ince the mea sured dra g of I?l a t 58.7 f. p, s. w as 0.0627pound, t he correct ion w ould be of t he order of 1 per cen t .

SCALE EFFECTTa king the product of t he velocity V by some cha ra cterist ic length 1 a s the sca le t he

lift ma y be a ssumed to va ry a s the squa re of t he sca le. Tha t is:L = & , (VZ)2 (3)

where K~ is a const a nt for ea ch model.The dra g does not va ry a s the squa re, but a s some lesser power of the sca le. Figure 1 is

a loga rithmic plot or dra g a ga inst speed for a ll models t est ed a t more tha n one speed. Theslopes of the lines w it h t he corresponding exponent s a re given in t he follow ing t able:

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TESTS ON AIRPLANE FUSELAGES, FLOATS AND HULLSVELOCITY EXPOh-Eh-TINTEE DRAG EQliATI03i

D-KY.I~MOdeIdesignatiOn

A7..-.__..-.--_AID_________A12---------------A13..............Be---------------cl----------------C4----------------EL.--------------IN....-----------E6----------------E7..------------_-E8................Em----------------EIO__---_-----_--EII---------------F1................F2----------------F3..-....--------G1.--............Go......-.....-_.Go...............G1l.......-..-.-.lG12.....-...--.

133

:Avenge........!62.2 I.90The a vera ge va lue of the exponent so found is n= 1.90. V7hile th is st r ict ly a pplies t o the

velocit y only , it ma y be a ssumed for va ria tion in length a lso. The dra g equa tion ma y there-fore be w rit t en a s D= K. (V7) (4) where K= is a const a nt for ea ch model.

I t w ill proba bly be found more convenient t o use inst ea d of equa tion (4):

()D= K 8Dm # 2mm (5)w here K, is t he sca le correct ion fa ctor given on Figure 2, L?~ the observed model dra g a t. v~ 7~a nd D t he full sca le dra g a t V7.

Lao Ill II ~~\ I Ill I 1 IIL*+,0.90 !11 111 111111)~080 ~y+ Itltll t II 1.%9. I 1 -p/4Jc)al~a70 tminw+- --L ~te Ill I Ill IIII I NH Ill 1111 It Ill Ill~501111 I 111111105[0 [52025 3(?.?54045

Scuierufio,@~&FIG.?.Drag correction factors forfwelages, hulk, floats, etc. Bssed on the assumption that D ccVJ.~

ih=KDz (~) TJ31reDL=Drag at t% and D:=Drag at Y*?sb convert i~ ~ model da ta to full sca le va lues,, a ny lenggth on the model such a s ma tiurn

diameter, overa ll lengt h, et c., ma y be used to determine the sca le, provided tha t the samegeomet r ica l lengt h is used for modeI a nd full sca le. Th e u se of over all len gt h is r ecom men ded,however.

The squa re of a le~ ~ th ha s the dirnensiom of a rea so that the m&muIu cr os s-s ect ion a la rea ma y be used inst ea d of 1= if desired.

.

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134 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSCOMPOSITE CURVES FOR FLOATS AND HULLS

The dra g curves for different floa ts a nd hulIs dii?ier so lit tle, one from a not her, tha t a cum-posit e curve ma y be draw n to represent w ithin compa ra t ively na rrow limit s the dra g for a ll

FIG. 3.C.ompositeresistance curve forseaplane floats tmd hulIssuch models. This curve is given on Figure 3. Know ing the dra g for 0 piline, the drag for any normaI pitch angle is rea dily obt ained fr om t his curve.

The I ift curves a re a lso simiIa r , so tha t a composite curve for L ,/ DmayFigL1re ~.3

2Q!: ~~Qf6 20

FIG.4.C!ompositeL/Dcurveor floats and hulls

.tch of the dc!ckbe drawn a s in

The curves of Figures 3 a nd 4 apply to any form }vhich approximates to a streamline andwhich does not ha~e too many appendages. From the limited data, available there is reasonto believe that the same, or a t a ny ra te simiIa r, curres w ill a pply t o a lI body lines of the a-rerageor better types.

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TESTS ON- AIRPQ!JTE FUSELAGES, FLOATS AND HULLS 135A/ ;f67:@&!_ ..

, F71Assumede.g.o s,,!! 1 r ~1 2 7.+83+b

Ii$l7.083:11;.-, - ..-__.Opitiandyaw 5=..455.s+7f

{y fp.s.f D, [b. .(%4 1!

~ fp.s.2 D, lb. .07; 7B/S,lb./sq.ff2505 D[S,/b./.sffff4330

4 Angte ofp[fchFor%- and moments in pitch onan airplane fuseIage. 7=$0 f.p.s.(Ref. R. and M. No. 112)

Assumedc.g.O@fchandyaw v= 40 rlp.s.a,h.@eeli f f r ou t w i n d sh i el d or pi f of - - - - - - - - .;~!b~b, ,, w i i h p i l ot n o w i n d sh i ef d - - - - - - - - - .0/97,. I I /OR$?w i n d sh i el d of f - - - - ---- - .025+; a f sh or f ---- ------ _-.o257., ~r a + cufbackfi~ .&?~~?: ::::.,. .Drag on an airplane fuselage. T=

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136 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS . - - . ../?7 (---J:*>

.5 i -~%~,0, 3.89t J

~ f+>

Op;fchndJQW ~,~p..s.Originalode/H

I

44.o s8,7 73.3 88.0.2850.4750 .7280f.0150S =.6750Sq. I?, _ D)S,;i+q.ft..4222.7037/.0785L5037FoiringBadded B,lb. .2150.3630 .5460.7830S =.6750sq.ff _ D/S,[b.}sq.i .3f85.5378 .8089L/600Foi-ingCremoved D,lb. .2000.3420 .5250.7450S =,6620sq.ff._ D/S,[b.[sq.i .302[,5[66 ,793f1.254Drag on a Navy speed scout seaplane fuseIage. (Ref. W. T. R.No. 20)

A9e ,51,1,1 ! I 1 I

-E3-,,: i,:,,.::

L.343AIOptfchndyow .S=.087~;q.t~ i?p..D>Jb. .0443D/S,Ib./sq.ff.5[00 .

gn.n? 1

I I m I I I I I I i

4 Ob otrc $E$A D FF D&7?-f

Opifchndyaw 8=.0780s~;i~ Ep.s. 40 ~ )cp.s.Foiring2 Fairing6D,[b. .033/ D,lb. .0340D/S lb./sq.ff.4250 D/S,lb./.sftft-?3600.04(7 / 0.08

@ tIx -7f-----*. y 0.030 t -. .. . -0.06~:$ z *L *. /1 bJ-r- -- _--?-- [)0.04$\

3E00/0 0.02k?-%. .%0 00 4 8 /2 [6Angleofpitch

Forces and moments in pitch on airplane fusekge F-E-7 modelR. and ?vf,No. 644) with fairing lA]. V=40f. p. s. (Ref. R. and M. No. 163)

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.

.TESTS ON AIRPLANE FUSELAGES, FLOATS ANTD HULLS 137

o .5.r I I 2.667 jaba bc a .

OOQ i f Chand YOW v= 40 fp.s. D =.0384t!.1,8ady wifboufeng.,pihfr wi&shie@allAo/esbkea- - - -z,(I)ifhpi[ofin~oce - - - - - - - - - - - - - D=.04841b.3,(2) ,,wins.sh[e[dinploce- - - - - - - - - D =.0609lb.-4ComplefeasSI+On, w i f b en g i n e - - - - - - - D =. ~540 [ b .* ~ j $p .S. - - - 44.0 .58.7 73.3 88.0 f0~7Combination D,lb.- - - - .136 .237 .365 .500 .680. 2 D/S,lb./sq.ff442 -783 1.200L7[8 2.235Drsg on Wexsl airpkme fuselage. (Ref. R. snd M. Xo. $65),.,:q@&Q-

Secfi~nA-A .282 +

i)=-2 pi+ch s=.0506sq. ff.

v Ep.s. 58.7 88.0D,l b. .0f23 .0330Df5,b./sq.ti2m .6522

s il;i~I ,P i ich i n a m om en z+.~i-8 I I ii-ii , t I -l--i 1,(-4 0 4 8 L, 112 , 16 20.& g[ e of p i +ch u n d yaw

Moments shout r. g. of Kirkham triplam+speed-scout fuselage.V=5&i f. p.s. (Ref. W. T. R. ho. i3)

1A)Originalode[.4f[p en i n g s cl osed , ~h[efopening dosed:4

D=.f/57/b.shutter,2tD =.[3[6/b.Sideporfs[on&)/osed2=. [226/b. ZI -25D=./6981b.(;~~odi~.dm~del~quure nose)D= [50t7R~r%$te.sD;/bV41b~ rem&ed, D=. [630lb;D =KSV+ K=.00074S=sq .f t, V = l f p.S..Dmg on fusslage of RE-7 akphme with shutters. F= 40f. p.s. (Ref. R.and M. N-o.221)

4/3 f+T=.275 ~_.a86.J c-g-,?663 J1.[.,,, ., . .. ;J-

0 ,, .5, .Opifchand yaw s=.Iol:;q.f%E fp.s.D /b. .0%6 .0$5 .0482D/S,[b.[sq.k .2727 .3113 .4763

AngleofyawYawingmoment about c. f. ofsirpkme fusslageof BristoI Pullman(A). F=50 f. p.s. (Ref. R. and M. ii.. 644)

0

OOR&h andyaw

{S=._f280sq.;f.~ fp.s.A D, [ b. .O:Q {

v, Ep.s.~ 1?, t !b .D /$ Ib./sq.ft2313 .0343D/S,Ib.[sq.ff2680

AngleofyawForms and moment in Ya~ on fusslage of SE-4 airplane. F= 40f. p. s.(Ref. R. snd 31.o. HZ)

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128 REPORT NATIONAL ADVISORY COMMITTEE FOR. AERONAUTICSC93 -en%--==-

LLJ-J L z.17 d.483~ Area of f i ns =.08!8Sq.ff4

.-4 ,,rudder=.0721 a .3 .5t--~ v+

6;.. i ~1 T ~- 8/7i345678O p i fch O h@yo w v= 40 Ep.s. S= .1032sq.ff.Body;~~ r% ond rudder Body olone.04[7 D,fb. .0378D)S,)b.~sq.t.404[ D~S,lb.jsq.ft3663

I I I I I I I I I I I0 5 100 /5 20 25AngleofyawForces@dmomentson fuselageof SEQairplane. V=40f . p,s. (Ref. R.and hf. No. 153)

.,,.g.,B6 ~ !++ .,:,,,,, L 5, . Y axis v.08/,&&

./ 2 3 f ,32< .( +.+.L + 4

Sf.1/0sq.ff.fin]~.=;;,;q. fi(rudder) S =.0928.sqft.Opifchndyow Mfh brakes,.S=..[78 sq.fitRudder~eufrak Wdhouffin&rudder:fAirbrokesc[ased. AirbrOkesopen) ,4irbrokeslosed.D, l b. .0753 D,{b. .1882D,lb. .0697D/LS,b.,lsq.ff81~+ D/S,[b.lsq,t /.93 D~S,lb.~sq.f..751/

Angleofyow

!- 1 2.125~SectionX-X I lx*OpitchndYOW v= 40 Ep.s. s =.0510Sq.ft.Airbrakesc[osed Airbrokesopen 90D,lb. .0696 D,lb. ./550D#7,Ib.lsqff.3647 DJS,lb.[sq.fk.0392

An gfe of r ud d er +0 f i nEffect of ai rbrakes on rudder of RE-1 af rplane 0 pi tch and YswV=40 f. p .s, (Ref. R. and M. 112)!C.g,-L?7 f==+-w&==TJ.Luii5 L I 2.508I 4

Opit&OOQyOW. Body w;thoufifl;oS=.;;3Sq. ffv,Ep,s.D,lb. .0?85 .1%0 .[540 .2/50D#s,b.~sq.ff.7503./16O /.68673549

AngleofyowFowesand moments in yaw OnRE-7 airplane fuselage fit ted with !air- ~Forces and moments in yaw on RE-8 airplane fuselagewith fkMSilOWII.brakes. V=40 f. p. s. (Ref. R. and M. No. 153) 7=40 f. p.s. (Ref. R. and M. No. 2011

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TESTS ON AIRPLANE FUSELAGES, FLOA~ AKD HULLS 13908 -=0 .5.!,,

~;[[JWifhfui-ingCW----- >=:Z?263>Z;3[3=Z4,([) man inopencackpifD =.03% lb.,?[S=.7

O&ch andyow v= -40r!p..s. S=.0560Sq.{f.Afodelashown Y ----- --D =.0730lb.,jS=[3036[b.jsq.%.[,Body wifhouffubifizers-.0..0294lb.,[S =.5250[b.lsq.fi.z Wijhcod~jfBtc------- B= .0.?!4h ~f~= .5W7[b./sq.fk9s[Q&@.56[b./sq.ff.5;fo 3L$ cockpita[FedoverD =.029S[b~li]S=.4304Ib.[sq.,i.6,(1)ithfakingDadded--D= .0265fb.,/S =.4732Ib./sq.ft.Areooffi~edin=.0667q.ftAreaofcenfrofudder=.O.35sq.i,, ouferrudders=.0425s.7.ff.afal75area =./442sq-*.Drag on fmelage ofFE-4 airplane. 0 p itch and yaw ~=40 f. p .s. (Ref.R. and M. h-o. 221)

Ho m$kJ=---@-/ f ~--. ..2 -Complefemode[ v= 40 fip.s. S=.C?52Uq.*.,4-@ ofpi+ch 2 +3 +8 +13D,lb. .0850.0850.0710.[120MS, lb.~sq.ff.6346L2500 L3654 2[538

Lift and drag onfussk+geo!iy ofBE-2c airpIane. (Ref. R. and M.No. 2.54)

q

1k

.Sectiin-8 BOpifchndyaw V=40 Ep.s. S=.R935sq.fk

{~ifhOut~or D,lb. L,Zlb./s#f %%.0275 wifh~arD,lb.D/S,[h/sq.k .294/

1 L.483L& .fspiti[eArea ~flo;:;rudder=.0598sq.fi.,, ,, =.0458 * .0p3chanoymv Is=.?390sq.fkiii%[agerudder Body oloneE Ep.s. 40 K fp.s.D,lb. .0332 D,lb. .0%7D/S,[b.#q.f%85/3 DE, J+q.fh .7358

Forces and moments i~ yaw on fussIage of Avro sespIane. V=40 f. p. s.(Ref. R. and M. No. 155)

SectionA-B E b47J

Opitchnd yaw v=40 fp.s. s =.0935Sq.fk~~+ f or wod COT W)fhforwuticar.0275 D,lb.-0]S,b./sq.ff.294/ D/S,Ib./sq.ff.%0.06:.0.04

2$.f 0.04$0.03q hx- $$0.02$0.02c:g.?< 080.0/+Ci$-0.02.$ 0p

2 -4 0 4 8 f2 mAngleofpifch -Dregwith faired IX onbcdy ofBE-9 airplane. (Ref. R. and M. No. 202) Forms and moments in pi tch ti th unfa ired car on fuselage of BE-9airpkme. [=40 [. p.s (Ref. R. and M. h-o.X0)

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140 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSc/ -a -+s---21o]:7 .. . . ..o \s.so p i fch O n cf ya wE f I f p . s . .9=2.60 sq . f f.587 8@ 1[ .73 [ 46.6I I , l b, 37800 8.3500 14.7000 22.7000D /S, /b ./.sf tf t /.4538 3.2115 .56538 8.7308Drag on nacelle of Davis-gun seaplane. (Ref. R. T. R.No. 67) (l

C3 +El@$@----ti5 hf-

t 2833 !

~o~v $=ezaP-----@a[anae Opifchndyaw S=.09[O sq.fi!(approx.)v= 40 f p.s. D .=. 0848 l b D@=.93i 9 l b./s q .f i !

4 Ang/eofyowForces and moments of m and rudder. FE-g airplane nacelie.V=40 f. p . s. (Ref. R. and M. No. 156)

Opitcbnoyow S=.2S8sq.ffV= 58.7f,O..S. D=. 1883lb D/S=.7298Ib.jsq.ff.

Angfeofpi+chLift and drag on nacelle o f Richardson seaplane. V=M.7 f. P.s.(Ref. IV. T. R. No. 54)

C5i.u..d,/hh:x

Drag on nacelle o fFE-2b ai rplane. (Ref. R. and M. No. 305)

@~6-- ... -..4, Oppx.LL.-J.+ TaifNo.I

L

1 OpifchndyawOpifchndyoW S=.go Sqbg v= 4U.OEp.s.IYO.[ foilwifh,adiafors,=. I/20fb.,wdhou+, D=.08651b.~ Lp.s . N o. 2 ,! I .[%0 .27$0 .3410 .4900 , D=./15/ib., ,$ D =.0874lb.WifhoufailII ,,~l$b.fsq.ff.2990 .5220 .8[501.700 D=./210lb., D=,/088lb,Dro9 due fo,side/afes, B =.O/031b.,gos;onk,D=.0072lb.

Drag on nacelle ofFE-8 airphme. (Ref. R. and LI. ho.305) Drag on nacelle ofHandley Page airplane. (Ref. R. and M. ho.251)

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TESTS ON AIRPLANE Fuselages FLOATS AND HULLS

D/ \ @G=+ =.=..----~.=.-..=T32f,, . ,,-FA

9,,.,~,.,,;/,.d-% 6I.i..?,,~,/,Q eJ.&o,$~(l bi.Q~5 SQ. O&o4 2.00 5 [00 /5 20 25AngleofyawLateraf force on Sn only of RE or Be type fuee[age. (Ref.R. and M. NTO.Xl)

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142 REPOItT N.4TION.4L ADVISORY COMMITTEE FOR AERON.4UTICS

3. 4 /VO.2, +/* 2 5 , 11 ~r-q -; ,.. . .. .i : 6 ,, -.~...m !7 [234 5 67

M od el N o. 1 M od el N o. 2~ fp.s. 40 K fp . s.D , l b. .0395 D , /b .0?7[D~S,/b.[sq.t .2582 D[S,b. sq.fit.3078

0Tos.1and 2

25r],,3 234s/j;,;, ~f ,,.!~:....:, ..=--:: -...................f Ik .3225 JO,oltchA yaw v 40 f ,os. s=.f5Q.sqffOpening None A Ba /b. .0424,0446 .L?46)05%8 .04%1BIS,lb./sq.t..2827 .2973.3037 .3520 .3073,/0.08 0.07/f

A / 0.06$~

$ 640 o.05g

-0b./sq . f t . f /82 .420! .9453

Forces and moments in pitch on airship car A. (Ref. R. an d M.hTo.151)

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TESTS ON AIRPLANE FUSELAGES, FLOATS LID HULLS 143--- 7,-____ q f

LLZ?3AI ---% f

E5

B~ -5, J h L JB-58?Op%chnd yaw s=.o#ii7sq.%~ fps.D,lb, >2%0 .0?:0 .%B /z /b ./.sf tf t ./0.% .4[58 .S190Opifd Ondyaw S=.0480sq.ffK Ep..sD,/b. .C%2 .0:$7 .2?7D}Z /b.@q.%.[292 .4[04 .8688

4 AngleofpifchForces and moments in pitch ORairship u B. (Ref. R. and M.No. 151) Forces and moments in pitch on airship w C. (Ref. R. and M.No. 151)

oO,off&ndyaw ;;047yoq. ft~ fp.s. 20D , [ b. .0046 .0180 .039.3D/S,/h/.sq.fl.0970 .3797 .829f00 ;i fch a nd yO W S=.2895sq . f i~ fp .s. 4+?0D , l b. 58.7 73.3 88.0 [02..0895 .f520 .2330 .32.54-4305D/S,b.jsq.ff.30S2 .5250 .8050 L/240 I!487(7

+++++0-02120, --lTp;tch-8&[.5--40 o -4 80 /2 }6

.Ang[e ofpifchand yu w

Dmg on:t%aed airship car, model A-o.326. (Ref. II_.T. R. A-o.145}orces and moments in pitch on airssp w D. Ref. R. ad M.N-o.151)

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144 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS.. -

0 ,51 I 1 L 2.27[ J

- @-~~ - . -7 JOOpifchndyaw S=.303+Sq.fitv fp.s. 440 58.7 73.3 88-O {02.7D,[b. .07%3 .[3!4 .2325.28/6-3705D/S,lb./sq.ff2580.4330.66/0 .92301.22/O

Ang/e ofpifchand yawDrag on closedairship car, model No. 323. (Ref.W. T. R. No. 14:)

AISecf/~nA-A

Opifchndyaw s =.;3:$/Sq.fifq Kp , s. 440 58.7 88.0D , .f b. .0366 .0627 .0963 .1390D /S, l b./sq .f t .4874 .8349 .t 2t 723 1.8509

o , .s( I +& IL /.667 JW -+> ~., .Opifchndyowv fp.s. s =.ob;.3;q.},29.3 44.0 587 73.3D,lb. .0468 .[040 .[835 .2834 .3996D/S,/bJsq.fk74291,8508.(912744984 63429blues formodelm shown wifhbombsond oppendogesDrag on C cIass c ar. (Ref. W. T. R. No. 140)

cE// C :..-- .....-...---..L~.2.... ----------------7=:,------::....I

y.,~~;,:::LJJ_.Ld B /,f28 1

-0.2 I I I I I I I ( ! I-4 O 4 8 f20 {6

A . .......... .

Amgk ofpifch(deckI/ne)Lift and drag on Speed Scout seaplane float . V=58.7 f. p. s. (Ref.V?.T . R. No. 18)

Drag on G class car. (Ref. W. T. R. No. 140)

F2 :5;4.sq . f i~ f p .s.D , l b. 88.0.075: .::87 .1063 .!495D/S,/b./sq.fi!7/10 /!227019/80 2.6986

0.80.6

g:0.4c16 0;2

-040 0 4 8 /2 /6Angfeof@fc6 (deckh%)Drag on Speed Scout seaplane float. V-88 f. P. S. (Ref. ~. TR. No. 147)

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TESTS OX .LIRFLANE FtJSEL.kGESj FLOATS AND HULLS 145F3 . .. .

Opifchandyaw S=.0751sq.ff.w fp.s. 44.0 58.7 73.3 88.0D,lb. .0423 .0720 .1129 ..f6f3i?~~lh~sq.fi5632 .9587L50332./478

0.8 I 1;0.6

Q II A Iq@4 /IQ II %/1 I40.2 ,, ,/- /

I I~4 111111 10Angleo?~;fch,d~cklin$ 16Drag onN-9 seaplane ffori t- Y-f% Lp.s. (Ref. TV.T. R. No. 147)

~ ,G/ ?C/ %7C7::,G W V= ZO f i p.SB S=. O ;56sq . f iD , l b . .0443 .0458 .0-406D /S, [ b ./sq . f t .97f 5 L O044 .8904

F4 P-- 1,

0pifci7nd yaw S =.0729sq.ff.44.0 58.7 733 88.0,{Es. .0.?39.0596 .0923 .13/8l?l~lb.,lsq.ff.4650 .8176/266! L808ff

0.8#,

0.6 /@ I ,~1q.~04 It& 5 /1 1 I0.2 At Io0 4 /6Angleo?~ifc~(;~e[.hej 20Drsg on Soptith seaplane fleat. V-2$ f. P. s. (Ref.

fl.4w2/ CJK. T. R. ho. 147)

~1,

If 2 34

Opifchawya w S=;$$26sg.ff.y fp.s.3/$Msq.ff. .:.:O

I- - ~ -!# I [o Ap iii ,4/ I -f.Qo Ill II0 .+ 8 /2 /6 0

I

Ang[eofpitchLift snd drag on sespIsne float. V=58.7 f. p. s. (R. and M. N-o. 1 93) Lift enddrag on CWlingen N-o. 1 float. V=98.6 f. P. s. (Ref.CIWtingen1921)

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146 REPORT NATIONAL ADVISORY COMMKMEE FORF7 - - . -0 .5 F --3.937

OpifchfldyUW s=.2/60sq.ftv fp.s. 98.6D,lb. 0.456D/iSt/b./sq.ff..1//4.0 2.0

3.0 [.6

72.0& /.2Q$J $$< /.0 ?.8Q

o 0.4

-/.0-4 o [20Ar?:l;fpl% [6 0Lift and dragon G6ttingen No. 2 float, V=W.6 f. p. s. (Ref.CMttingerr1921)

F9 -f+-->0 .5, L 3.937 J

0p;fchndyaw s=. [940sq.fi!v,fp,s. 98.6D,lb. 0.366D/S,lb.@.ff.1.8874.0 {.6

3.0 /.2

742.0 0.83L~ Q*.%. $;/.0 Q4&

o 0

-/.0-4 o 4 8 /2 /6AngleofpifchLif t anddrag on Gott ingen iVo,4 float. V=98.Gf. p.s. (Ref.Clottingen 1921)

-F8o .5) 4

4$.& ~3

AERONAUTICS

.. --F. 3.937 7

1II II/ 23 4

0p;fchndyaw S=. /525Sq.fi!~ fp,s. 98,6D,/b. 0.330D/S,/b./sqf.2.164

Lift and drag on Gott.ingen NO, 3 float. v=9s,6 f. p, s.G6ttingen 192.1)

~w~\, ,46$., I.. IJ21 {3 i 1/ 2 34O p t i ch on d ya w s =g$555sq??~ ,fp,.D,k. .5520D/S, lb.q.ff.2.45

(Ref.

Lift and drag on C+dttingenho. 5 J@.t, F=9;.5 f. p , S, (R~f.Giittingen 19zI)

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TESTS ON AIRPLANE FUSELAGES, FLOATS AND HULLS 147,,,F// -++-+++-+-++ , FL? : ---++++i,, ,L.li

4yS:_~ qs.> U.,,e j ,0 .;, !! thner h u l ! o .4.,, ,,S ca leo.- .5td e fw

~~~~ O p i f ch a n+ ya w s =& a Sq . f i ena-pdv l $p .s. em we.sD , l b. .0588D /s [ b ./sq .f f . .[849

t; i ic.gj i i [

L ---- .H : + !s,?;6;,~~ t i ; n@o f }om 0 t -I h n e r huffopi f& or7aow S:;780 Sq . i ?w f p.s.Z ) , l b . . & f 4 fD /S, @sq f i t .24780.5/.01, ,,, (, l~o.5

!lUsol---kw+Lf4ifw

AngleofpifchForm and moments in pitch OKIan A. D. resin fbt for short sw.-planes. T=40 f. p.s. (Ref. R. and M. ho. 285)

,F/3 ;--~L5 ,lf ,, ,\3.5 mheifi$$++2E&~o .C,., I ts..!, fore..bcq.d Op;fdandyaw S =&780 Sq ff.emw~e ~ ,fp.s.D, lb. .0441D[S,t!jsq.t 2478

Fomes &d moments in pitch on a Blaekburu seaplane main fhth-o. L T=40 f. p .s. (Ref. R. and M. No. 2$.5)

Qc.

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148 REPORT NATIONAL ADVISORY COMMITTEE FOR

Op i fch a nd ya w S =

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TESTS ON AIRPLANE FUSELAGES, FLOATS AND HULLS

L I0 .& 29/7 ~.~,, ,,,

OOpifchndyaw s=.f7oosq%gv:Ep.s.i?,lb. .0?73.05;5.Oz:k .0:77 .f[30D/S,lb.jsq.fk[606 .2618 .37% ..5153.66470.5- II II IIILJ -20II IHIV 0,8-4 I II I 11A ~Ill$03 I Illllxm 5

~. I t I I/xDl I 202 I Ilwflll o&Fa[ HY/1/l//~ +=J --J I 11 0.04

11 [lo/0 /5 20Angle ofp i t c h

Lift and drag on R. A. E. seaplane hull. V-M f. p . s. (Ref. R. and hf.No. 461)

Op i ?ch or d ya w S=.2760Sq.fkv I@.D,lb. .&:4 .0$7f .[7Z8 ./$;2 .2%0 .2:;52?1S,b.~sq.ff.15ffL72576.4014 .5559 .7717 .9764Drsg on F-3 s=plsne hrdl. (Ref. R. snd M. No. 461)

G//u

OO p i fc h O & yUW S=.;Z J Sq . f iT $ t p . s. 50. 80D,lb. .0~85 .0%8 .0750 .% .[44.9.IB80D/s,&./sq.f -1203 .2059 .3[ 65 .45f 9 .6/ /4 .7932

50.[264.49/8.0775.4212

Drag OQNT-2B waplane half. (Ref. R. snd M. N-o .461)

O ep i fch a nd yow S=7~86sq>$K .fp..s.D,lb. .0~?9 .~?5 .0;?5 .1~~[ .[38/ .18/0D/S,[b.q.fi.[500 .2554.3844 .5435 .7425 .9731- Drag on W-fed A. D. seaplsne huIL (ReL R. snd M. No. 461)

OpifdC?ndyow S=.2520sq.fkw fip.s.D,[b. .0%?3 .0:s2 .05:7 .1771 ./::! :2:2[D/S,fb.~sq.ft.[242 ..2/[ .3258,4647 .6313 .8139Drag on N4A .=plane hti. (Ref. R. snd K No. 461)

,!!, ! ED

oPi+ch c md yO W X=$;07 Sqh : .y f p .s. 30 40 50. 60hhe AB por ul lel f o w [h dD , l b. .0329 .0588 .0903 . /284 .1733 .2253D /S, f b./%q .f t .1589 .284/ .4362 .6203 .8372 [0884L i n e CB p om ll el t o w th di ?, l b . .0367 .0635 .0978 . /397 . [853 .2420D /S, i b .[ sq .f f .1773 .3068 .4725 .6749 .8952 1. /69[Drsg on N-4 seaplsne hull. (Ref. R. snd M. Lo.461) Drag on P-5A seaplsne hulI . (Ref. R. and M. No. 46I )

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REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

~55 L 3.833 JA?od;ficofionanglesledh)

Drag on P-5 and P-5 (modified) seaplane bulls,Iio. 461)

G/5Lf_L.Q?

(Ref. R, and M

.J-.-.__._ ._. _ ,_.I

0oj+ch and yo w s=. /44 Sq . ff . O p i f ch andyuw S=;;39Sq.f%v,fp,s. v fp,s.D,k, ,2:?0 .0%2 .0%/ .0%4 ,[% .1%8 D , l b.D/S, [b.jsq.t.,/743 .3069 .4799.6903 ,9583 1.2278 q .0:?8 .0:+2 .0%3 .0%4 . /07(7 . /%0D [S, I b./sq f +. . /588 .2676 .3978 .57/2 .7698 /.0072Drag on NT-T seaplane huR. (Ref. R. & M. No. 461) Drag on Supermwine N-lB hull. (Ref. R. aud M, No, 461)