naca-6608

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

Thickness: 8.0%
Camber: 6.0%
Trailing edge angle: 9.3o
Lower flatness: 63.1%
Leading edge radius: 0.8%
Max CL: 1.451
Max CL angle: 4.5
Max L/D: 65.443
Max L/D angle: 3.5
Max L/D CL: 1.251
Stall angle: 4.5
Zero-lift angle: -7.5