naca-8610

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

Thickness: 10.0%
Camber: 8.0%
Trailing edge angle: 11.1o
Lower flatness: 42.2%
Leading edge radius: 1.2%
Max CL: 2.025
Max CL angle: 7.0
Max L/D: 64.178
Max L/D angle: -0.5
Max L/D CL: 1.202
Stall angle: -0.5
Zero-lift angle: -10.0