NACA 5 digit Airfoil Generator

Generates the NACA 5 digit airfoil coordinates

Description

"naca5gen.m" Generates the NACA 5 digit airfoil coordinates with desired no. of panels (line elements) on it.
 
FEATURES:
 *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
 
INPUTS:
[1] NACA 5 digit designation (eg. '23012')
[2] No of panels (line elements) PER SIDE (upper/lower)
[3] Type of chord station spacing (Half cosine spacing / Uniform spacing)
 
OUTPUTS:
[1] One can plot the generated airfoil, camber line and the leading edge circle by setting an option input wantPlot=1
[2] A data file can be generated by setting the option input wantFile=1
 
EXTENSION:
Being a function, the airfoil generator can be called several times from a loop to generate any number of airfoil data files.

Acknowledgements

This file inspired Xfoil Matlab Interface.

• MATLAB release: MATLAB 7.4 (R2007a)

[Dirk]

FYI python port here: https://github.com/dgorissen/naca

[Austin Bond]

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.