naca-4514

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

Thickness: 14.0%
Camber: 4.0%
Trailing edge angle: 16.7o
Lower flatness: 50.8%
Leading edge radius: 2.2%
Max CL: 1.656
Max CL angle: 12.0
Max L/D: 59.546
Max L/D angle: 4.5
Max L/D CL: 1.137
Stall angle: 5.5
Zero-lift angle: -4.5