naca-2310

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

Thickness: 10.0%
Camber: 2.0%
Trailing edge angle: 12.1o
Lower flatness: 66.8%
Leading edge radius: 1.2%
Max CL: 1.115
Max CL angle: 7.5
Max L/D: 50.244
Max L/D angle: 5.5
Max L/D CL: 0.893
Stall angle: 7.5
Zero-lift angle: -1.5