naca-2208

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

Thickness: 8.0%
Camber: 2.0%
Trailing edge angle: 9.7o
Lower flatness: 85.0%
Leading edge radius: 0.8%
Max CL: 0.974
Max CL angle: 6.5
Max L/D: 46.339
Max L/D angle: 5.5
Max L/D CL: 0.864
Stall angle: 6.5
Zero-lift angle: -1.5