NACA 63-210 AIRFOIL

Thickness: 10.0%
Camber: 1.1%
Trailing edge angle: 4.7o
Lower flatness: 9.6%
Leading edge radius: 2.0%
Efficiency: 32.3
Max CL: 0.899
Max CL angle: 12.5
Max L/D: 23.699
Max L/D angle: 1.0
Max L/D CL: 0.318
Stall angle: 1.0
Zero-lift angle: -1.5