Generate airfoil data for NACA4415

The NACA 4415 was removed from the top of the file to make reading easier. This can be used for any airfoil that is input as columns of x and y points. The points must start and end with x = 1.0.

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%   Reference: https://m-selig.ae.illinois.edu/ads/coord_database.html
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%   Copyright (c) 2023 Princeton Satellite Systems, Inc.
%   All rights reserved.
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%   Since v2024.1
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% Number of points
n     = 100;

% Angles of attack
alpha = linspace(0,2*pi,n);

%  List of x and y points
z     = load('naca4415.txt')';

% Call once to get the plots
ComputeCoeffFromShape( z(1,:), z(2,:), n, alpha );

% Get the outputs
[cL, cD, cM] = ComputeCoeffFromShape( z(1,:), z(2,:), n, alpha );

save('NACA4415.mat',"cL","cD","cM");


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