NACA M22 AIRFOIL

Thickness: 6.2%
Camber: 6.3%
Trailing edge angle: 19.3o
Lower flatness: 10.3%
Leading edge radius: 1.8%
Efficiency: 28.7
Max CL: 1.068
Max CL angle: 13.5
Max L/D: 31.376
Max L/D angle: 5.0
Max L/D CL: 0.703
Stall angle: -0.5
Zero-lift angle: -2.0