naca-2218

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

Thickness: 18.0%
Camber: 2.0%
Trailing edge angle: 21.7o
Lower flatness: 10.4%
Leading edge radius: 3.6%
Max CL: 1.433
Max CL angle: 15.0
Max L/D: 36.502
Max L/D angle: 6.0
Max L/D CL: 0.891
Stall angle: 4.0
Zero-lift angle: -1.5