1. AAE 451 Aircraft Design First Flight Boiler Xpress November 21, 2000
Team Members
Oneeb Bhutta, Matthew Basiletti , Ryan Beech, Mike Van Meter
Professor Dominick Andrisani

2. 3-D Views
11ft
6ft

3. Aerodynamic Design Issues
Lift
Low Reynolds Number Regime
Slow Flight Requirements
Drag
Power Requirements
Accurate Performance Predications
Stability and Control
Trimmability
Roll Rate Derivatives

4. Low Reynolds Number Challenges
Separation Bubble-to be avoided!
Laminar Flow -more Prone to Separation
Airfoil Sections designed for Full-sized Aircraft
don’t work well for below Rn=800,000
Our Aircraft Rn=100, ,000

5. Airfoil Selection Wing: Tail sections: Selig S1210 CLmax = 1.53
Incidence= 3 deg
Tail sections:
flat plate for Low Re
Incidence = -5 deg

6. Drag Prediction Assume Parabolic Drag Polar Based on Empirical
Fit of Existing Aircraft

7. Parasite Drag Drag Build-up Method of Raymer
(Ref. Raymer eq & eq.12.30)
Blasius’ Turbulent Flat Plate-
Adjusted for Assumed
Surface Roughness

8. Drag Polar Aircraft Drag Polar CL 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8
0.02
0.04
0.06
0.08
0.1
0.12
0.14
0.16
Aircraft Drag Polar CL CD
CDi
CDo

9. Power Required Predict: Power required for cruise Battery energy for15 20 25 30 35 40 16 18 22 24 26 28 32
Velocity [ft/s]
Power Required [ft-lb/s]
Predict:
Power required for
cruise
Battery energy for

10. Aerodynamic Properties
Wetted area = sq.ft.
Span Efficiency Factor = 0.75
CLa = / rad
CL de = /rad
L/Dmax =
Vloiter = ft/s
CLmax =
CLcruise =
Xcg = (% MAC)
Static Margin = at Xcg = 0.35

11. Stability Diagram Cmcg CL elev deflect=-8 deg -4 4 8 0.2 0.4 0.6 0.8 14 8
0.2
0.4
0.6
0.8 1
1.2
1.4
1.6
1.8
-0.4
-0.3
-0.2
-0.1
0.1
0.3 CL
Cmcg

12. Flow Simulation

13. Parasite Drag CDo for Wing and Tail surfaces
For Fuselage, booms & pods
(Ref. Raymer eq & eq.12.33)

14. Tail Geometry Horizontal Tail: Area = 2.2 Span = 3.0ft Chord = 0.73ft
Vh = 0.50
Vertical Tail- 25% added
Area = 1.75 sq.ft
Span = 1.63 ft
Chord = 0.60 ft
Vv =

15. Control Surface Sizing:
Elevator
Area Ratio = 0.30
Chord = 2.7 in.
Rudder
Area Ratio = 0.40
Single rudder of chord = 7.5 in.
Ailerons
Area Ratio = 0.10
Aileron chord = 3 in.

16. Equipment Layout & CG. Controls equipment Propulsion component
Rotation angle = 10deg
Tip Back angle= 15deg
Controls equipment
Propulsion component
Airframe component
17.54 in.
Miscellaneous Weight

17. Equipment Layout (3-D)

18. Landing Loads Vland=1.3Vstall=25ft/s
g = -5 deg
Vvert=2.2ft/s
Vland=1.3Vstall=25ft/s
For d = 1 in., k = 15.2 lb/in
For 1 inch strut travel, peak load = 15.2 lb
sspar = 240 psi on landing

19. Static Margin, Aerodynamic Center, and c.g.
Xac = 0.46
Xcg = 0.35
SM = 0.11

20. Horizontal and Vertical Tail Sizing
Vh - Horizontal tail volume coefficient = 0.50
Vv - Vertical tail volume coefficient = 0.044

21. Control Surface Sizing
Based on historical data from Roskam Part II Tables 8.1 and 8.2.
Homebuilts
Single Engine

22. Control Surface Sizing (cont.)
Sa = 1.35ft2
Sr = 0.80ft2
Se = 1.00ft2
Max. surface deflection is 15 deg.

23. Climb Performance
Max. Climb Angle, G
G = 7.3 deg.

24. Turning Performance Maximum turn rate r = 50ft Vmax = 28ft/s
Y= 0.28 rad/s

25. Propulsion Design Issues
Power
Power required
Power available
Endurance
Can we complete the mission
Verification
Motor test to take place this week

26. Power Power required is determined by aircraft
Power available comes from the motor

27. System Efficiencies Propeller Gearbox Motor Speed Controller 60-65%
95%
Motor
90%
Speed Controller
Total System Efficiency
50.7%

28. System Components Propeller Gearbox Motor Speed Controller
Freudenthaler 16x15 and 14x8 folding
Gearbox
“MonsterBox” (6:1,7:1,9.6:1)
Motor
Turbo 10 GT (10 cells)
Speed Controller
MX-50

29. Economics Preliminary Design Testing 525 man-hours @ $75 = $39,375
$81.70 in materials

30. Economics Prototype Manufacturing Flight Testing
300 $75 = $22,500
$ in materials
Flight Testing
$900
Prototype manufacturing budget
$200 max

31. The Budget

32. Total Project Cost
The Bottom Line
$67,024.05

33. Questions?