1. Team 5 Aerodynamics QDR 2 Presented By: Christian Naylor Charles Reyzer

2. 2 AAE 451 – Team 5 February 8, 2005 Outline Aerodynamic Model Trimability Considerations Stability Considerations

3. 3 AAE 451 – Team 5 February 8, 2005 Mathematical Model – Lift C L vs α Lift vs. α α (deg) Lift (lbs) CLCL

4. 4 AAE 451 – Team 5 February 8, 2005 Mathematical Model – Drag Drag Polar CLCL Drag (Lift) CDCD Lift (lbs)

5. 5 AAE 451 – Team 5 February 8, 2005 Mathematical Model – L/D L/D max =13.21 Loiter at α=.71°,4.46° Loiter at 0.866*L/D max 1 α (deg) L/D L/D vs. α 1 Raymer, D.P., Aircraft Design: A Conceptual Approach, Virginia, 1999, pp 27

6. 6 AAE 451 – Team 5 February 8, 2005 Trim Diagram Negative C Mα for stability Find C M0 Find C Mα Intro to Aeronautics: A Design Perspective, Steven A. Brandt et al

7. 7 AAE 451 – Team 5 February 8, 2005 Find C M0 C Mac = Pitching Moment Coefficient about Wing AC (0.05) ε o = Downwash at zero AOA (0) i to = Tail angle of incidence (0)

8. 8 AAE 451 – Team 5 February 8, 2005 Determine C Mα C Lα = Change in wing C L vs AOA (0.075 /deg) C Lαt =Change in tail C L vs AOA (0.066 /deg) X cg =Normalized center of gravity (0.89) X ac =Normalized center of gravity (1.00) C mac = 0.717 ft V H = “Volume” of horizontal tail (0.11 cubic ft) dε/dα=Change in Downwash vs AOA (.7153)

9. 9 AAE 451 – Team 5 February 8, 2005 Trim Diagram Trim Point: 3.18 degrees

10. 10 AAE 451 – Team 5 February 8, 2005 Future Work Class 2 Sizing of Control Surfaces Adjust tail angle of incidence Add elevator deflections to trim diagram Ensure that the aircraft is stable in all directions Verification of C M0