1. Team “Canard” September 19th, 2006
Aerodynamics 1 QDR
Team “Canard”
September 19th, 2006

2. Overview Aircraft Geometry: Aerodynamic Mathematical Model: Summary
- Airfoil selection for wing and tail
- Wing and tail configuration
- Aspect ratio and wetted area
- 3-View drawing
Aerodynamic Mathematical Model:
- CL
- CD
- CLMax
Summary
AAE 451 Team 1

3. Preliminary Airfoil Selection
Wing Airfoil:
- Looked at pylon racers
- MH 43 common airfoil
- Low Reynolds number airfoil
Tail Airfoil:
- NACA 0009 common in tail surfaces
- Thin, lower induced and parasite drag
MH 43
NACA 0009
AAE 451 Team 1

4. Wing Geometry METHOD Fixed thanks to historical data:
Aspect ratio = 10
Taper ratio = 0.45
To be determined:
Sweep angle
Dihedral angle
Wing span
AAE 451 Team 1

5. Wing Geometry Top View s a b Wing span = 6.45 ftC a b s
Swing = 4.16 ft2
Wing span = 6.45 ft
Too much for structure
Wing span = 6 ft
Aspect ratio = 8.65
Sweep angle =
= 9.3 degrees
AAE 451 Team 1

6. Same airfoil all along the wing
Wing Geometry
Front View d
troot
ttip
Chordtip = 0.4 Chordroot
ttip = 0.4 troot
Same airfoil all along the wing
From the airfoil section, we know :
troot = Chordroot
troot = ft
ttip = Chordtip
ttip = ft
Dihedral angle =
= 0.73 degrees
AAE 451 Team 1

7. Tail Geometry Top View Horizontal tail : Vertical tail :
11.4 deg
Taper ratio : 0.6
Aspect ratio : 10
Sweep angle : 11.4 deg
No dihedral
0.47 ft
Shtail = 0.36 ft2
0.28 ft
1.88 ft
Swing = 4.16 ft2
AAC = 0.65 ft
D = 2.25 ft
with
Vertical tail :
0.7 ft
0.65 ft
Degrees of freedom on the size for control and stability
AAE 451 Team 1

8. Wing and Tail Geometry Wing Horizontal Tail Span 6 ft 1.88 ft
Sweep Angle
9.3°
11.4°
Taper Ratio
0.45
0.6
Dihedral Angle
0.73° 0°
AAE 451 Team 1

9. Aircraft Wetted Area
(Historical data)
AAE 451 Team 1

10. Aircraft Wetted Area Fuselage wetted area estimate :
Wing/tail wetted area estimate :
Fuselage : Swet-fuselage = 2.88 ft2
Wing : Sexposed-wing = 3.92 ft2
Swet-wing = 7.92 ft2
Horizontal tail : Sexposed-htail = 0.33 ft2
Swet-htail = 0.67 ft2
Vertical tail : Sexposed-vtail = ft2
Swet-vtail = 0.39 ft2
AAE 451 Team 1

11. 3-View Drawing
AAE 451 Team 1

12. Mathematical Model
CL: -
CD:
CLMax:
- CL at αstall
AAE 451 Team 1

13. Mathematical Model 2D Estimation from XFOIL 2D Coefficients
Clo = 0.151
Clα = 0.104/°
Clmax = 1.082
AAE 451 Team 1

14. Mathematical Model 2D Estimation Cont… 2D Drag Coefficients
Cdo =
AAE 451 Team 1

15. 2D to 3D Calculations Find CL from lifting line : Find e : Find k :
Find CD for 3D :
Find CDo :
AAE 451 Team 1

16. 2D/3D Comparison
2D plotted in blue
3D plotted in red
AAE 451 Team 1

17. Summery Aircraft Geometry: Aerodynamic Mathematical Model:
- Airfoil selection for wing and tail
- Wing and tail configuration
- Aspect ratio and wetted area
- 3-View drawing
Aerodynamic Mathematical Model:
- CL
- CD
- CLMax
AAE 451 Team 1

18. Questions
Any Questions?
AAE 451 Team 1