NACA67-214 a=0.2

NACA67214a=0.2

Curve fits of basic Javafoil data for NACA67-214 a=0.2, 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