NACA67-116 a=0.6

NACA67116a=0.6

Curve fits of basic Javafoil data for NACA67-116 a=0.6, smooth airfoils, Mach 0:

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

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

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

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

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