Comparing Airfoils

NACA 65(2)-415 a=0.5

AH 82-150 A

NACA 65(2)-415 a=0.5 AH 82-150 A
Thickness (%) 14.975 14.995
Camber (%) 2.990 3.278
Trailing Edge Angle (%) 9.766 10.121
Lower Surface Flatness 8.165 7.777
Leading Edge Radius (%) 2.634 2.244
Maximum Lift (CL) 1.217 1.265
Maximum Lift Angle-of-Attack (deg) 15.000 12.000
Maximum Lift-to-drag (L/D) 37.694 45.550
Lift at Maximum Lift-to-drag 1.035 0.929
Angle-of-Attack for Maximum Lift-to-drag (L/D) 7.500 4.500