naca-8410

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

Thickness: 10.0%
Camber: 8.0%
Trailing edge angle: 11.6o
Lower flatness: 42.3%
Leading edge radius: 1.2%
Max CL: 1.876
Max CL angle: 9.0
Max L/D: 64.975
Max L/D angle: 2.5
Max L/D CL: 1.323
Stall angle: 3.5
Zero-lift angle: -8.5