naca-4508

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: 86.2%
Leading edge radius: 0.8%
Max CL: 1.142
Max CL angle: 10.5
Max L/D: 62.803
Max L/D angle: 3.5
Max L/D CL: 0.97
Stall angle: 5.0
Zero-lift angle: -4.5