1. Aether Aerospace AAE 451 September 27, 2006
Aerodynamics 1 QDR
Aether Aerospace
AAE 451
September 27, 2006
Mark Davis Ashley Gordon
Hank Kneitz Ryan Mulligan
Joshua Rodewald Brandon Wampler
Mathieu Hautier Samantha Pearcy

2. Overview Aircraft Geometry Airfoil Selection Aerodynamic Trade Study
Wing
Tail
Aerodynamic Trade Study
Aspect Ratio
Wing and tail geometry
Aircraft wetted area
Aerodynamic Mathematical Model
Lift Coefficient
Drag Polar
Moment Coefficient
Aircraft Trim Diagram
Future Work
November 28, 2018
AAE 451, Aether Aerospace

3. Aircraft Geometry The Angry Mosquito 5.26 ft 1.59 ft 4.0 ft
November 28, 2018
AAE 451, Aether Aerospace

4. Aerodynamic Design Point
Max speed at steady, level flight
α = 0º
V = 125 ft/s (~85 mph)
Sea level
From vehicle sizing
W = 5.5 ft
S = 3.25 ft2
(W/S) = 1.7 lb/ft2
November 28, 2018
AAE 451, Aether Aerospace

5. Wing Airfoil Selection
MH-24 Characteristics
Requires very precise manufacturing
Designed for Re ~ 800k
Used on piston-engine pylon racer
MH-32 Characteristics
Higher CLmax
Designed for Re < 500k
Wind tunnel data for Re = 300k
Used on electric powered pylon racers
Selecting the MH-32 airfoil for the wing
November 28, 2018
AAE 451, Aether Aerospace

6. Wing Airfoil Section – MH 32
November 28, 2018
AAE 451, Aether Aerospace

7. Tail Airfoil Section NACA 0009 Symmetric Low t/c November 28, 2018
AAE 451, Aether Aerospace

8. Aspect Ratio Trade Study
Optimize AR for minimum total drag (Cd0 + Cdi = Cd)
Assumes turbulent flow
Increasing Cdo
November 28, 2018
AAE 451, Aether Aerospace

9. Aspect Ratio Trade Study
Optimize AR for minimum total drag (Cd0 + Cdi = Cd)
Decreasing Cdi
November 28, 2018
AAE 451, Aether Aerospace

10. Aspect Ratio Trade Study
Results
ARopt = 8.5
Cd,min =
(Cf ~ .0057)
Solution depends on:
Velocity
Inversely proportional
Weight
Directly proportional
Optimum AR = 8.5
November 28, 2018
AAE 451, Aether Aerospace

11. Wing Geometry Wing Airfoil MH 32 S 3.25 ft2 Aspect Ratio 8.5 Span
Taper Ratio
0.45
Leading Edge Sweep 0°
Quarter Chord Sweep
-2.56°
Trailing Edge Sweep
-10.12°
Dihedral
yes
Quarter chord line
2.56°
Leading Edge
0.38 ft
0.85 ft
10.12°
2.63 ft
November 28, 2018
AAE 451, Aether Aerospace

12. Fuselage Design Ongoing Fuselage Trade Study Future Considerations:
Minimize Weight
Sufficient Tail size
Sufficient Control Surface Size
Future Considerations:
Minimum build-able fuselage length
Weight and size for control surfaces at each fuselage length
November 28, 2018
AAE 451, Aether Aerospace

13. Tail Geometry Design Process
Calculate required tail areas
Tail size coefficients for proper control size
cHT = 0.5
cVT = 0.04
SVT = ft2
SHT = 0.49 ft2
November 28, 2018
AAE 451, Aether Aerospace

14. Tail Geometry Design Process
V-Tail consideration
V-tail requires same total tail area as conventional configuration
Stails = 0.78 ft2 (total - conventional)
Sv-tail = 0.39 ft2 per tail
Dihedral angle
37.3º
November 28, 2018
AAE 451, Aether Aerospace

15. Tail Geometry V-Tail Airfoil NACA 0009 S 0.39 ft2 - each Aspect Ratio
3.25
Span
1.59 ft
Taper Ratio
0.45
Leading Edge Sweep
25°
Quarter Chord Sweep
12.7°
Trailing Edge Sweep 0°
Dihedral
-35°
Quarter chord line
25°
Leading Edge
0.67 ft
0.3 ft
12.7°
0.795 ft
November 28, 2018
AAE 451, Aether Aerospace

16. Aircraft Wetted Area
Use CATIA function to find an accurate wetted area
November 28, 2018
AAE 451, Aether Aerospace

17. Aircraft Drag Polar Cfe = 0.005 e = 0.797 CDo = 0.032 k = 0.047
Historical data from Raymer
CDo = 0.032
e = 0.797
k = 0.047
November 28, 2018
AAE 451, Aether Aerospace

18. Aircraft Drag Polar
Note a marked reduction in CD0. Changes in wing and tail geometry were contributing factors, however the streamlining of the fuselage accounts for the greatest drag reduction.
November 28, 2018
AAE 451, Aether Aerospace

19. Moment Coefficient CMo = -0.068 CMa = 0.1432 From XFOIL From XFOIL
November 28, 2018
AAE 451, Aether Aerospace

20. Aircraft Lift Curve Cla = 5.6936 Clo = 0.293 (2-D) Raymer “90% est”
From wind tunnel data & XFOIL
Clo = (2-D)
From wind tunnel data & XFOIL
Raymer “90% est”
2-D to 3-D
CLo = 0.9 Clo
CLo = (3-D)
CLa = 5.575
November 28, 2018
AAE 451, Aether Aerospace

21. Lift Coefficient Curve
*a in radians
November 28, 2018
AAE 451, Aether Aerospace

22. Drag Polar and Lift Curve with Flaps
Near 1.6 design point
November 28, 2018
AAE 451, Aether Aerospace

23. Maximum Lift Coefficient, MH-24
Clmax = 1.12
2-D from online data
CLmax = 1.08
CLmax,flaps = 1.5
XFOIL data:
November 28, 2018
AAE 451, Aether Aerospace

24. Future Work Fluent CFD Model Purpose Status Entire aircraft
Separate tail/wing models
Purpose
Better structural loading analysis
Better aerodynamic model for D&C
Identify/correct areas of high drag
Status
Mesh complete but needs refinement
Will be able to run solution
Can be modified for flaps
November 28, 2018
AAE 451, Aether Aerospace

25. Future Work Continue Integrating code
Ensures global usage of parameters
Integrates aerodynamics, controls, propulsions and structures
Integrates trade study codes
Sample Output
November 28, 2018
AAE 451, Aether Aerospace

26. The Angry Mosquito
November 28, 2018
AAE 451, Aether Aerospace

27. Wing/Tail Geometry Equations
Span
Root chord
Tip chord
TE sweep
c/4 sweep
November 28, 2018
AAE 451, Aether Aerospace