naca-9212

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

Thickness: 12.0%
Camber: 9.0%
Trailing edge angle: 14.0o
Lower flatness: 41.1%
Leading edge radius: 1.6%
Max CL: 2.013
Max CL angle: 12.5
Max L/D: 35.308
Max L/D angle: -0.5
Max L/D CL: 0.96
Stall angle: -0.5
Zero-lift angle: -8.0