naca-4408

Generated NACA airfoil. See also http://www.aerospaceweb.org/question/airfoils/q0041.shtml

Thickness: 8.0%
Camber: 4.0%
Trailing edge angle: 9.6o
Lower flatness: 91.2%
Leading edge radius: 0.8%
Max CL: 1.198
Max CL angle: 6.0
Max L/D: 59.958
Max L/D angle: 5.0
Max L/D CL: 1.09
Stall angle: 6.0
Zero-lift angle: -4.0