NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT AIRFOIL

Thickness: 15.5%
Camber: 1.3%
Trailing edge angle: 9.6o
Lower flatness: 5.1%
Leading edge radius: 2.4%
Efficiency: 34.9
Max CL: 1.049
Max CL angle: 15.0
Max L/D: 18.407
Max L/D angle: 4.5
Max L/D CL: 0.478
Stall angle: -0.803
Zero-lift angle: -1.0