1. Bridget Fitzpatrick Patrick Dempsey Heather Garber Keith Hout Jong Soo Mok Aerodynamics Preliminary Design Review #2 October 23, 2000

2. Objectives -Three View Drawing Update -Coefficient of Lift -Methods Update: Warner and Roskam -Drag Polar -Lift to Drag Curve -Endurance Parameter -CMARC Update -Aerodynamic Effectiveness of the Control Surfaces -Stability Derivatives

3. Aircraft Geometry – 3-View SID5

4. MethodClmax Warner1.25 Roskam1.48 Average1.37 2-D1.53 Coefficient of Lift

5. Aerodynamic Mathematical Model WARNER

6. Aerodynamic mathematical model Roskam 3-D Coefficient of Lift

7. Aerodynamic mathematical model Roskam 3-D Coefficient of Lift

8. Aerodynamic mathematical model Roskam 3-D Coefficient of Lift Slope

9. Aerodynamic mathematical model Roskam 3-D Coefficient of Drag

10. 3-D Drag Polar Optimum CL~1

11. Lift to Drag Ratio

12. Endurance Parameter:

13. Endurance:

14. Flight Conditions for maximum endurance L/D max:7.2 Velocity: 20.52ft/s Angle of Attack: 8.37 degrees CL: 1.03 CD: 0.16

15. Coefficient of Moment

16. Coefficient of Moment Calculations Equations taken from Mark Peters thesis

17. Coefficient of Moment Calculations Equations taken from Mark Peters thesis

18. Aircraft Geometry -SM: the static margin was set at 0.18

19. Aircraft Geometry Aircraft wetted Area59.5 ft 2 Wing38.7 ft 2 Struts0.83 ft 2 Tails9.01 ft 2 Landing gear-0.003 ft 2 Aspect ratio of wing4.4

21. Control Surfaces Raymer’s Suggestions Orion Aerospace Ailerons15-25% chord15% chord full span Elevator25-50% chord40% chord full span Rudder25-50% chord40% chord full span

22. Aerodynamic Effectiveness of the control surfaces Rudder Effectiveness: 60% Elevator Effectiveness: 60% Aileron Effectiveness: 30% Effectiveness determined from Roskam’s Flight Dynamics and Controls

23. Stability Derivatives -Theoretical Method: This was presented on Tuesday. -Will be compared to CMARC CMARC needs: -working wake -will use to verify theoretical derivatives

24. Aerodynamic coefficients CL  3.938 CL  wing 3.7914 CLo.5242 Cm  -.4428 Cmo.5503-.5992 Cm-.8667 CDo.0427

25. Questions?