naca-4314

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

Thickness: 14.0%
Camber: 4.0%
Trailing edge angle: 16.8o
Lower flatness: 67.8%
Leading edge radius: 2.2%
Max CL: 1.581
Max CL angle: 15.0
Max L/D: 52.965
Max L/D angle: 4.0
Max L/D CL: 0.986
Stall angle: 4.5
Zero-lift angle: -3.5