naca-4608

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

Thickness: 8.0%
Camber: 4.0%
Trailing edge angle: 9.5o
Lower flatness: 80.9%
Leading edge radius: 0.8%
Max CL: 1.166
Max CL angle: 10.0
Max L/D: 67.118
Max L/D angle: 3.0
Max L/D CL: 0.983
Stall angle: 4.5
Zero-lift angle: -5.0