1. Aether Aerospace AAE 451 September 19, 2006
Aerodynamics 1 QDR
Aether Aerospace
AAE 451
September 19, 2006
Mark Davis Ashley Gordon
Hank Kneitz Ryan Mulligan
Joshua Rodewald Brandon Wampler
Mathieu Hautier Samantha Pearcy

2. Aircraft Geometry The Angry Mosquito 4.4 ft 0.285 ft 3.54 ft 0.75 ft
Quarter chord to quarter chord
0.75 ft
The Angry Mosquito
May 24, 2019
AAE 451, Aether Aerospace

3. Aerodynamic Design Point
Max speed at steady, level flight
α = 0º
V = 175 ft/s (~120 mph)
Sea level
From vehicle sizing
W = 5.5 lb
S = 3.25 ft2
(W/S) = 1.7 lb/ft2
May 24, 2019
AAE 451, Aether Aerospace

4. Wing Airfoil Selection Process
Airfoil Criterion
“Low” Reynolds number, Re = 808,000
High lift to drag ratio
Machinable geometry
Research
RC pylon racers
Agricultural crop dusters
Single engine, homebuilt
May 24, 2019
AAE 451, Aether Aerospace

5. Wing Geometry Design Process
Set Parameters:
Aspect ratio, AR = 6
Initial value based on team experience
Will be optimized for minimum induced and parasite drag taking structural considerations into account
Taper ratio, l = 0.45
Best approximation for elliptical loading
Calculate based on the above:
Span, b
Root/tip chords, Croot Ctip
TE sweep, LTE
TBD
May 24, 2019
AAE 451, Aether Aerospace

6. Wing Geometry Wing Airfoil MH 24 S 3.25 ft2 Aspect Ratio 6 Taper Ratio
0.45
Leading Edge Sweep 0°
Quarter Chord Sweep
-3.6°
Trailing Edge Sweep
-24.5°
Dihedral
yes
Quarter chord line
3.6°
.45 ft
1 ft
24.5°
2.2 ft
May 24, 2019
AAE 451, Aether Aerospace

7. Wing Airfoil Section MH-24 Used on pylon racers Optimized for “low” Re
May 24, 2019
AAE 451, Aether Aerospace

8. Fuselage Design Based on Raymer historical data From Raymer, Table 6.3
Agricultural aircraft
Homebuilt – metal/wood
From Raymer, Table 6.3
a = 4
C = .23
Wo = 5.5 lbs
Length = 5.9 ft
May 24, 2019
AAE 451, Aether Aerospace

9. Tail Geometry Design Process
Calculate required tail areas
Historical data from Raymer
cHT = 0.5
cVT = 0.04
SVT = ft2
SHT = ft2
May 24, 2019
AAE 451, Aether Aerospace

10. Tail Geometry Design Process
V-Tail consideration
V-tail requires same total tail area as conventional configuration
Stails = 0.5 ft2 (total - conventional)
Sv-tail = 0.25 ft2 per tail
Dihedral angle
35º
May 24, 2019
AAE 451, Aether Aerospace

11. Tail Geometry V-Tail Airfoil NACA 0009 S 0.25 ft2 - each Aspect Ratio
3.25
Taper Ratio
0.45
Leading Edge Sweep 0°
Quarter Chord Sweep
-6.66°
Trailing Edge Sweep
-29°
Dihedral
-35°
Quarter chord line
6.66°
.17 ft
0.38 ft
29°
0.9 ft
May 24, 2019
AAE 451, Aether Aerospace

12. Tail Airfoil Section NACA 0009 Symmetric Low t/c May 24, 2019
AAE 451, Aether Aerospace

13. Aircraft Wetted Area Calculations May 24, 2019
AAE 451, Aether Aerospace

14. Fuselage Wetted Area Estimation
Use scaled grid to estimate top and side fuselage areas
Top Area ~ 3 ft2
Side Area ~ 2.8 ft2
1 sq box = 0.25 sq ft
May 24, 2019
AAE 451, Aether Aerospace

15. Aircraft Drag Polar e = 0.75 Cfe = 0.006 k = 0.0707 CDo = 0.032
Historical data from Raymer
CDo = 0.032
e = 0.75
Historical data from Raymer
k =
May 24, 2019
AAE 451, Aether Aerospace

16. Aircraft Drag Polar
May 24, 2019
AAE 451, Aether Aerospace

17. Aircraft Lift Polar Cla = 8.3/rad Clo = 0.139 Raymer “90% est”
From XFOIL & online data
Clo = 0.139
From XFOIL & online data
Raymer “90% est”
2-D to 3-D
CLo = 0.9 Clo
CLo = 0.125
CLa = 7.95
/rad
May 24, 2019
AAE 451, Aether Aerospace

18. Lift Coefficient Curve
*a in radians
/rad
May 24, 2019
AAE 451, Aether Aerospace

19. Maximum Lift Coefficient Justification
Wind Tunnel Data: NACA 0009
Wind Tunnel Data: NACA
MH 24
Clmax = 1.0
2-D
CLmax = 0.9
3-D
CLmax,flaps = 1.6
Approximate a 0.7 increase to allow room for controllability
May 24, 2019
AAE 451, Aether Aerospace

20. The Angry Mosquito

21. Wing/Tail Geometry Equations
Span
Root chord
Tip chord
TE sweep
c/4 sweep
May 24, 2019
AAE 451, Aether Aerospace

22. Overview Aircraft Geometry Airfoil Selection Wing and tail geometry
Aspect Ratio
Taper Ratio
Sweep angle
Dihedral Angle
Aircraft wetted area
Key Coefficients
Lift coefficient
Drag Polar
Maximum lift coefficient
May 24, 2019
AAE 451, Aether Aerospace