naca-4410

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

Thickness: 10.0%
Camber: 4.0%
Trailing edge angle: 12.0o
Lower flatness: 87.5%
Leading edge radius: 1.2%
Max CL: 1.386
Max CL angle: 8.5
Max L/D: 60.764
Max L/D angle: 6.5
Max L/D CL: 1.279
Stall angle: 7.0
Zero-lift angle: -4.0