1. AAE 451 Aircraft Design Aerodynamic Preliminary Design Review #1
Team Members
Oneeb Bhutta, Matthew Basiletti , Ryan Beech, Mike Van Meter

2. Airfoil Selection FX-63–137 Selig 1210 Selig 1223 CLmax = 1.36

3. Drag Polar

4. Drag Polar

5. Drag Polar

6. Tail Geometry
Horizontal Tail
Span = 3.0ft ; Chord = 0.71ft
Vh = 0.45

7. Tail Geometry
Vertical Tail
Span = 1.63ft ; Chord = 0.60ft
Vv = 0.005

8. Tail Geometry Sweep Angle = 0 Dihedral Angle = 0
Taper = 0.6; Ctip = 0.78ft , Croot = 1.31ft
Recritical_tip = 100e3

9. Wetted Area Reference Area = 14.50 sq-ft
Total Wetted Area = sq-ft
AR = 8.50
Span = ft

10. Aerodynamic Model
Lift Coefficient CL
Drag Polar

11. Parasite Drag CDo for Wing and Tail surfaces
(Ref. Raymer eq & eq.12.30)

12. Parasite Drag For Fuselage, booms & pods
(Ref. Raymer eq & eq.12.33)

13. Drag Polar Graph

14. Drag Graph

15. Endurance