naca-2414

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

Thickness: 14.0%
Camber: 2.0%
Trailing edge angle: 16.9o
Lower flatness: 29.2%
Leading edge radius: 2.2%
Max CL: 1.276
Max CL angle: 15.0
Max L/D: 48.157
Max L/D angle: 6.5
Max L/D CL: 1.061
Stall angle: 6.5
Zero-lift angle: -2.0