naca-6612

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

Thickness: 12.0%
Camber: 6.0%
Trailing edge angle: 13.9o
Lower flatness: 62.0%
Leading edge radius: 1.7%
Max CL: 1.883
Max CL angle: 9.5
Max L/D: 71.716
Max L/D angle: 5.0
Max L/D CL: 1.562
Stall angle: -0.5
Zero-lift angle: -7.5