"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.
J. Divahar (2021). NACA 5 digit Airfoil Generator (https://www.mathworks.com/matlabcentral/fileexchange/23241-naca-5-digit-airfoil-generator), MATLAB Central File Exchange. Retrieved .
For anyone finding errors in the airfoil generation, here are the code modifications to apply in order to generate correct airfoils (using Airfoiltools.com definitions):
 P=[0.05 0.1 0.15 0.2 0.25];
 M=[0.0580 0.1260 0.2025 0.2900 0.3910];
 K=[361.4 51.64 15.957 6.643 3.230];
P=[ 0.1 0.15 0.2 0.25 ];
M=[ 0.13 0.2170 0.318 0.441 ];
K=[ 51.99 15.793 6.520 3.191 ];
P=[0.05 0.1 0.15 0.2 0.25];
M=[0.0580 0.1260 0.2025 0.2900 0.3910];
K=[361.4 51.64 15.957 6.643 3.230];
I know that I'm 7 years late but I see people are still downloading this file nowadays.
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.
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