naca-6416

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

Thickness: 16.0%
Camber: 6.0%
Trailing edge angle: 18.8o
Lower flatness: 68.3%
Leading edge radius: 2.9%
Max CL: 2.004
Max CL angle: 15.0
Max L/D: 50.966
Max L/D angle: 1.5
Max L/D CL: 0.996
Stall angle: 1.5
Zero-lift angle: -6.0