Option for Alpha 2 POLAR - Can we use NACA airfoil instead?

[ggunners]

Roman,

I've not yet figured out how to create a POLAR file from scratch but think they may be related to actual airfoil performance.

Could we possibly use NACA 4-digit airfoils and calculate the POLAR table at model load time?

NACA 4-Digit Series:
1st digit = max camber in % chord
2nd digit = position of max camber in 1/10 of c
3rd & 4th digit = max thickness in % of chord

Typical slowflyer would be like 6301
Flat bottom airfoil would be 2306
Symettric would be 0306

See for the airfoil geometry calculator.

NACA 5 or NACA 6 would also work OK.

Or instead could be have airfoil designations like:

UNDERCAMBER // wing camber = UNDERCAMBER, FLATBOTTOM or SYMETTRIC

THIN // wing thickness = THIN, NORMAL, THICK

3.0 // wing tip washout 1-10

You might even be able to substitute the NACA number for the POLAR number in the surface section and drop the POLAR sections entirely.

Just an idea. Do you think it has merit?

If not, please help me figure out how to generate POLAR files for various NACA airfoils.

Thanks!

-- ggunners