naca-8518

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

Thickness: 18.0%
Camber: 8.0%
Trailing edge angle: 20.4o
Lower flatness: 49.6%
Leading edge radius: 3.6%
Max CL: 2.448
Max CL angle: 15.0
Max L/D: 52.786
Max L/D angle: 5.0
Max L/D CL: 1.625
Stall angle: -0.5
Zero-lift angle: -9.0