1. November 6, 2003QDR1 Team 5 Aerodynamics QDR #2 Scott Bird Mike Downes Kelby Haase Grant Hile Cyrus Sigari Sarah Umberger Jen Watson

2. November 6, 2003QDR2 Presentation Outline Updated Airfoil Lift Coefficient Pitching Moment

3. November 6, 2003QDR3 Airfoil Re-Selection NACA 2412 Selig 1223 24 inch chord

4. November 6, 2003QDR4 Method Used to Calculate Lift Coefficient 1.Ran XFOIL for NACA 2412 to get 2-D Data 2.Converted to 3-D 3.Ran XFOIL again for NACA 0012 horizontal tail 4.Converted to 3-D 5.Used method described in Roskam Part VI, CH8

5. November 6, 2003QDR5 Lift Coefficient C L = C Lo + C Lα * α + C Lδe * δe C L = 0.1764 + 0.1386* α + 0.0336* δe (note α and δe in degrees)

6. November 6, 2003QDR6 Effects of Elevator Deflection on Lift Coefficient

7. November 6, 2003QDR7 Method used for calculating Pitching Moment Coeff. Utilized Lift Coefficient data and calculations described earlier in accordance with method described in Roskam, Chapter 3 of AAE 421 Book.

8. November 6, 2003QDR8 Pitching Moment Coefficient about Quarter Chord C m = C mo + C mα * α + C mδe * δe C m = - 0.0280 - 0.1562* α - 0.0898* δe (note α and δe in degrees)

9. November 6, 2003QDR9 Pitching Moment “Believability” Check C m0 Range +.15 to -.15 C mα Range +1 to -4 [deg -1 ] C mδe Range 0 to -4 [deg -1 ] (note: not necessarily correct, just in a “believable” range of typical values) (Roskam p.87,88 Airplane Flight Dynamics and Automatic Flight Controls)

10. November 6, 2003QDR10 Pitching Moment Coefficient

11. November 6, 2003QDR11 Questions? Questions?

12. November 6, 2003QDR12 Calculations  Re = 432,0000; M = 0.029 (Takeoff Conditions) 2-D to 3-D Conversion  C Lα = C l α /(1 + (57.3*C l α /(π*e*A))) [deg -1 ]  [57.3 deg/rad conversion] (from AAE 251 book)  C L = C l *(C Lα /C l α )  [calculated for C L0 using C l0 ] (Hepperle)