"naca5gen.m" Generates the NACA 5 digit airfoil coordinates with desired no. of panels (line elements) on it.
*Accurate coordinate generation with the required precision
*Option to generate closed or open Trailing Edge
*Additional separate outputs for camber line, upper surface and lower surface
*A tst (test) file included
 NACA 5 digit designation (eg. '23012')
 No of panels (line elements) PER SIDE (upper/lower)
 Type of chord station spacing (Half cosine spacing / Uniform spacing)
 One can plot the generated airfoil, camber line and the leading edge circle by setting an option input wantPlot=1
 A data file can be generated by setting the option input wantFile=1
Being a function, the airfoil generator can be called several times from a loop to generate any number of airfoil data files.
This program works well for the example given but when I plot a NACA 65016 their is an obvious discontinuity at the point of max camber. I believe the equations used are correct, but I'm not exactly sure how the k1 constant is obtained. Either way I believe the z-values at the point of max camber are wrong.