January 2019 – Josh The Engineer

Below are the two Python codes used to download all the airfoils from the UIUC Airfoil Database, found here:

https://m-selig.ae.illinois.edu/ads/coord_database.html

For some reason, I can’t load .py files onto my website, so I’ve saved them as .txt files. You can press the download button, copy the text into a new file, and save it as a .py file.

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Get_Save_Airfoils.py

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Get_Save_Airfoils_Selig.py

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Below you can download the MATLAB script from my YouTube video about how to run XFoil from MATLAB. The .m file will open in a separate window.

MATLAB_XFOIL.m

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The code can also be seen below (without line-by-line comments)

clear;
clc;

NACA       = '2412';
AoA        = '0';
numNodes   = '35';
saveFlnmAF = 'Save_Airfoil.txt';
saveFlnmCp = 'Save_Cp.txt';

% Delete files if they exist
if (exist(saveFlnmAF,'file'))
    delete(saveFlnmAF);
end
if (exist(saveFlnmCp,'file'))
    delete(saveFlnmCp);
end

% Create the airfoil
fid = fopen('xfoil_input.txt','w');
fprintf(fid,['NACA ' NACA '\n']);
fprintf(fid,'PPAR\n');
fprintf(fid,['N ' numNodes '\n']);
fprintf(fid,'\n\n');

% Save the airfoil data points
fprintf(fid,['PSAV ' saveFlnmAF '\n']);

% Find the Cp vs. X plot
fprintf(fid,'OPER\n');
fprintf(fid,['Alfa ' AoA '\n']);
fprintf(fid,['CPWR ' saveFlnmCp]);

% Close file
fclose(fid);

% Run XFoil using input file
cmd = 'xfoil.exe < xfoil_input.txt';
[status,result] = system(cmd);

%% READ DATA FILE: AIRFOIL

saveFlnmAF = 'Save_Airfoil.txt';
fidAirfoil = fopen(saveFlnmAF);  

dataBuffer = textscan(fidAirfoil,'%f %f','CollectOutput',1,...
                                 'Delimiter','','HeaderLines',0);
fclose(fidAirfoil);
delete(saveFlnmAF);

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XB = dataBuffer{1}(:,1);
YB = dataBuffer{1}(:,2);   

%% READ DATA FILE: PRESSURE COEFFICIENT
saveFlnmCp = 'Save_Cp.txt';
fidCP = fopen(saveFlnmCp);
dataBuffer = textscan(fidCP,'%f %f %f','HeaderLines',3,...
                            'CollectOutput',1,...
                            'Delimiter','');
fclose(fidCP);
delete(saveFlnmCp);

% Separate Cp data
X_0  = dataBuffer{1,1}(:,1);
Y_0  = dataBuffer{1,1}(:,2);
Cp_0 = dataBuffer{1,1}(:,3);

%% PLOT DATA

% Split airfoil into (U)pper and (L)ower
XB_U = XB(YB >= 0);
XB_L = XB(YB < 0);
YB_U = YB(YB >= 0);
YB_L = YB(YB < 0);

% Split Xfoil results into (U)pper and (L)ower
Cp_U = Cp_0(YB >= 0);
Cp_L = Cp_0(YB < 0);
X_U  = X_0(YB >= 0);
X_L  = X_0(YB < 0);

% Plot: Airfoil
figure(1);
cla; hold on; grid off;
set(gcf,'Color','White');
set(gca,'FontSize',12);
plot(XB_U,YB_U,'b.-');
plot(XB_L,YB_L,'r.-');
xlabel('X Coordinate');
ylabel('Y Coordinate');
axis equal;

% Plot: Pressure coefficient
figure(2);
cla; hold on; grid on;
set(gcf,'Color','White');
set(gca,'FontSize',12);
plot(X_U,Cp_U,'bo-','LineWidth',2);
plot(X_L,Cp_L,'ro-','LineWidth',2);
xlabel('X Coordinate');
ylabel('Cp');
ylim('auto');
set(gca,'Ydir','reverse')

Month: January 2019

UIUC Airfoil Database File Download

Running XFoil from MATLAB