naca-2508

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: 76.9%
Leading edge radius: 0.8%
Max CL: 0.911
Max CL angle: 11.5
Max L/D: 46.984
Max L/D angle: 3.5
Max L/D CL: 0.692
Stall angle: 5.0
Zero-lift angle: -2.0