naca-4614

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

Thickness: 14.0%
Camber: 4.0%
Trailing edge angle: 16.6o
Lower flatness: 41.9%
Leading edge radius: 2.2%
Max CL: 1.713
Max CL angle: 11.0
Max L/D: 59.669
Max L/D angle: 6.0
Max L/D CL: 1.385
Stall angle: 6.5
Zero-lift angle: -5.0