NACA 66,2-(1.8)12 A=.6 P-51 TIP AIRFOIL

Thickness: 12.0%
Camber: 1.3%
Trailing edge angle: 7.9o
Lower flatness: 7.0%
Leading edge radius: 2.0%
Efficiency: 32.5
Max CL: 0.897
Max CL angle: 14.0
Max L/D: 30.545
Max L/D angle: 3.5
Max L/D CL: 0.517
Stall angle: -0.5
Zero-lift angle: -1.0