NACA67-120 a=0.6

NACA67120a=0.6

Lift curve slopes of basic Javafoil data for NACA67-120 a=0.6, smooth airfoil:

Re: 500k | 1M | 3M | 6M | 12M

Re = 500k | 1M | 3M | 6M | 12M

Re = 1M | 500k | 3M | 6M | 12M

Re = 3M | 500k | 1M | 6M | 12M

Re = 6M | 500k | 1M | 3M | 12M

Re = 12M | 500k | 1M | 3M | 6M