NACA airfoil

I can help with the first four numbers, but I'm unsure about the others.

The general 4-digit NACA airfoil is defined as follows:

First digit = Maximum camber as a percent of chord length
Second digit = Position along chord where maximum camber occurs
Third and Fourth digits = Maximum thickness, in percent of chord length.

For example, a NACA 2412 has a maximum camber of 2% of the chord length. The maximum camber occurs at a position .4 chord from the leading edge, and the maximum thickness is 12%.

The two leading zeros would be indicative of a symmetric airfoil.

SuperStress