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

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

Drag Polar

Drag Polar

Drag Polar

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

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

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

Wetted Area Reference Area = 14.50 sq-ft Total Wetted Area = 45.72 sq-ft AR = 8.50 Span = 13.168 ft

Aerodynamic Model Lift Coefficient CL Drag Polar

Parasite Drag CDo for Wing and Tail surfaces (Ref. Raymer eq.12.27 & eq.12.30)

Parasite Drag For Fuselage, booms & pods (Ref. Raymer eq.12.31 & eq.12.33)

Drag Polar Graph

Drag Graph

Endurance