Team 5 Aerodynamics QDR #1 Scott Bird Mike Downes Kelby Haase Grant Hile Cyrus Sigari Sarah Umberger Jen Watson October 9, 2003 QDR

Preview Airfoil Sections and Geometry 3-view of aircraft Aerodynamic mathematical model October 9, 2003 QDR

Aerodynamic Known Values Recruise = 700000 At 1000 ft, Vcruise = 55 ft/s Restall = 380000 At Sea Level, Vstall = 30 ft/s S = 28 ft2 b = 14 ft c = 2 ft October 9, 2003 QDR

Airfoil Sections Wing Horizontal tail Vertical tail S1223 Airfoil High lift, Low Reynolds number Used extensively in RC aircraft Horizontal tail NACA 0012 Symmetrical 5 degrees Sweep To prevent tail stalling before wing Taper Ratio = .803 Vertical tail symmetrical 10 degrees Sweep Tail sweep > 20 degrees not practical for slow flight Taper Ratio = .73 October 9, 2003 QDR

Aircraft 3-view October 9, 2003 QDR

Aerodynamic Mathematical Model CL = 1.056 + .0804 * α CLmax = 2.13 CD = .0638 + .0518 * (1.056 + .0804 * α)2 Swet = 119 ft2 AR = 7 October 9, 2003 QDR

Questions? Questions?? October 9, 2003 QDR

Aerodynamic Mathematical Model CL= CLo + CLα * α CLα = Clα / (1 + 57.3 * Clα / (pi * AR * e)) CLo = -CLα * α when CL = 0 CD=CDo + k * CL * CL CDo = f / S f was interpolated using Figure 5.39 (Raymer) k = 1 / (pi * AR * e) e = 2 / (2 – AR + √ (4 + AR^2 * cosΛLE)) e = .877 Swet = Σ Swet_surfaces October 9, 2003 QDR

Airfoil Section October 9, 2003 QDR

Airfoil Section Data CL Alpha October 9, 2003 QDR

Airfoil Section Data CD CD CL CL October 9, 2003 QDR