NACA-M1 AIRFOIL

Thickness: 6.2%
Camber: 0.0%
Trailing edge angle: 17.4o
Lower flatness: 13.0%
Leading edge radius: 1.9%
Efficiency: 28.3
Max CL: 0.644
Max CL angle: 12.5
Max L/D: 12.363
Max L/D angle: 1.5
Max L/D CL: 0.165
Stall angle: 1.5
Zero-lift angle: 0.0