Dane Batema Benoit Blier

Drew Capps Patricia Roman

Kyle Ryan Audrey Serra

John Tapee Carlos Vergara

Team 1:

Aerodynamics 2 PDRTeam “Canard”

September 19th, 2006

AAE 451 Team 1 2

OverviewAircraft Geometry:

- Airfoil selection for wing and tail

- Wing and tail configuration

- Aspect ratio and wetted area

- 3-View drawing

Aerodynamic Mathematical Model:

- CL

- CD

- CM

AAE 451 Team 1 3

Wing and Tail Geometry

  Wing Horizontal tail

Airfoil MH 43 NACA 0006

Aspect ratio 8.65 6

Taper ratio 0.45 0.6

Sweep angle 9.95° 9.46°

Dihedral angle 0.85° 0°

Span 6 ft 1.79 ft

Area 4.16 ft2 0.54 ft2

Reynolds number 511 463 220 472

Maximum velocity : 115 ft/sAircraft wetted area : 12.21 ft2

AAE 451 Team 1 4

3-View Drawing

AAE 451 Team 1 5

Mathematical ModelLift Coefficient 3D:

eCCS

SCCC eLttL

twwLLoL ,,, )(

(From Flight Stability and Automatic Control, Robert C. Nelson)

CL: Total Lift Coefficient

CLo: CL at α = 0

CL,αw: Lift coeff. slope for wing

CL,αt: Lift coeff. slope for tail

CL,δe: Lift coeff. slope due to δe

η: Dynamic pressure ratio

αw: Angle of attack for the wing

αt: Angle of attack for the tail

St/S: Horizontal Tail area/Wing area ratio

δe: Elevator deflection angle

AAE 451 Team 1 6

Wing Lift Coefficient

11.0LoC radC wL /03.5,

lowl

wlLo

AR

CC

C

,

,

1

AR

CC

Cwl

wlwL

,

,,

1

Less than 2π

eCCS

SCCC eLttL

twwLLoL ,,, )(

AAE 451 Team 1 7

CL Plot for WingCL vs Alpha

-0.6

-0.4

-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

-10 -5 0 5 10 15

Alpha (deg)

CL

, C

l

radC wl /18.6,

Blue Line: XFOIL

Red Line: 3D

radlo 0218.0

AAE 451 Team 1 8

Tail Lift Coefficient

Qw

Qt

Vw

Vt

2

2

5.

5.

1 13.0

S

St

)(,, twwtLttL iiCC

0 4ti

t

tl

tltL

AR

CC

C

,

,,

1

radC tL /64.4,

w

wL

AR

C

,2

rad/37.0

eCCS

SCCC eLttL

twwLLoL ,,, )(

AAE 451 Team 1 9

CL Plot for TailCL vs Alpha for Tail

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

0 2 4 6 8 10 12

Alpha (deg)

Cl ,

CL

Blue Line: XFOIL

Red Line: 3D

radC tl /15.6,

AAE 451 Team 1 10

Elevator Effect on CL

S

SCC t

tLeL ,,

6.0

radC eL /362.0,

eCCS

SCCC eLttL

twwLLoL ,,, )(

Plot of TAU vs Area ratio (Control Surface/Lifting Surface)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8

Control Surface area/lifting surface area

TA

U

(From Flight Stability and Automatic Control, Robert C. Nelson)

AAE 451 Team 1 11

Maximum Lift Coefficient

LMaxstall SCVWL 25.

SV

WC

stall

LMax 25.

13.1LMaxC

Needed CLMax CLMax from Lift Curve

81.0LMaxC

Needed ΔCLMax: 0.32

)(9.0 maxref

flappedlLMax S

SCC

9.0max lC

264.1 ftS flapped

AAE 451 Team 1 12

Mathematical Model

2LDoD kCCC

ref

wetfDo S

SCC

64.0)045.01(78.1 68.0 Ae

Drag Coefficient

793.0e

Aek

1

0464.0k

006.0fC

018.0DoC

Small due to Swet

AAE 451 Team 1 13

Drag PolarDrag Polar

0

0.02

0.04

0.06

0.08

0.1

0.12

0.14

0.16

-0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2 1.4

CL , Cl

CD

, C

d

Blue Line: XFOIL

Red Line: 3D

AAE 451 Team 1 14

Mathematical ModelMoment Coefficient 3D:

eCCCC emwwmmom ,,

(From Flight Stability and Automatic Control, Robert C. Nelson)

Cm : Total Moment Coefficient

Cmo : Cm at α = 0

Cm,αw : Change of Cm due to αw

Cm,δe : Change of Cm due to δe

αw: Angle of attack for the wing

δe: Elevator deflection angle

AAE 451 Team 1 15

Zero Moment Coefficient

12.0moC

1

eCCCC emwwmmom ,,

)( 0, twtLHmomo iiCVCCw

AR

CL

00

2

cS

lSV ttH

ac cg ac

25%

33%

lt

t

tl

tltL

AR

CC

C

,

,,

1 4ti

0

0256.00 wmC

AAE 451 Team 1 16

Moment Coefficient

75.1, wmC

eCCCC emwwmmom ,,

AR

CC

Cwl

wlwL

,

,,

1

)1()( ,,, d

dCV

c

x

c

xCC tLH

accg

wLwm

w

wL

AR

C

d

d

,2

tLHem CVC ,,

t

tl

tltL

AR

CC

C

,

,,

1

114.1, emC

AAE 451 Team 1 17

Moment Coefficient

AAE 451 Team 1 18

Questions

Any Questions?