NACA-M1 AIRFOIL

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Thickness: 6.2%
Camber: 0.0%
Trailing edge angle: 10.4o
Lower flatness: 86.0%
Leading edge radius: 2.3%
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