naca-2410

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

Thickness: 10.0%
Camber: 2.0%
Trailing edge angle: 12.1o
Lower flatness: 63.6%
Leading edge radius: 1.2%
Max CL: 1.13
Max CL angle: 7.5
Max L/D: 49.279
Max L/D angle: 5.0
Max L/D CL: 0.854
Stall angle: 7.5
Zero-lift angle: -2.0