This page contains my library of MATLAB function m-files for aerodynamics problem solver. All m-files listed here are my m-files. All of these m-files are free and you may use or modify them as you like. To download the m-files, simply click the link on each m-file name and a pop-up window will appear, allowing you to download the m-files from my dropbox.
GenerateBezierCurve.m – generates Bezier curve from the specified control points.
GenerateCSpline.m – generates cubic Hermite curve from the specified control points and the tangent of each control point.
GenerateAirfoil.m – generates vertexes of an airfoil from the specified camber line and thickness distribution.
GenerateNACACamberLine.m – generates vertexes of the specified NACA camber line.
GenerateNACASeries4Airfoil.m – generates vertexes of the specified NACA series 4 airfoil’s surface and camber line.
GenerateNACASeries5Airfoil.m – generates vertexes of the specified NACA series 5 airfoil’s surface and camber line.
GenerateNACASeries16Airfoil.m – generates vertexes of the specified NACA series 16 airfoil’s surface and camber line.
GenerateNACASeries6Airfoil.m – generates vertexes of the specified NACA series 6 airfoil’s surface and camber line.
CalculateVelocityFromSource2D.m – calculates a velocity at a certain location that caused by a source at a certain location.
CalculateVelocityFromSourcePanel2D.m – calculates a velocity at a certain location that caused by a uniformly distributed source panel at a certain location (requires CalculateVelocityFromSource2D.m).
CalculateVelocityFromDoublet2D.m – calculates a velocity at a certain location that caused by a doublet at a certain location.
CalculateVelocityFromVortex2D.m – calculates a velocity at a certain location that caused by a doublet at a certain location.
PotentialFlow2DSim.m – generates 2D potential flow field from given combination of elementary flow such as uniform flow, source, sink, doublet, and vortex (requires CalculateVelocityFromSource2D.m, CalculateVelocityFromDoublet2D.m, and CalculateVelocityFromVortex2D.m).
PotentialFlow2DSim_GUI.m – starts GUI version of PotentialFlow2DSim.m to generate and plot 2D potential flow from given combination of elementary flow such as uniform flow, source, sink, doublet, and vortex (requires PotentialFlow2DSim.m). This code were also available in Mathworks File Exchange Center.
SourcePanelMethod2D.m – analyzes an object’s aerodynamic characteristic by using source panel method (requires CalculateVelocityFromSourcePanel2D.m and CalculateVelocityFromSource2D.m).
ClassicThinAirfoilAnalysis.m – calculates an airfoil’s aerodynamics characteristic in a potential flow with thin airfoil assumption (Classical Thin Airfoil Theory).
CalculateMAC.m – calculates MAC of a wing and its spanwise location based on given halfspan chord length distribution.
If you have any comments, critics, and suggestion for my m-files, please feel free to message me at zerocross_raptor@yahoo.com or leave a comment.
please tell me how can I download the m-file to generate NACA Series 4 Airfoil?
Dear Mr Abdullah,
Simply click the link at GenerateNACASeries4Airfoil.m text and you’ll be directed to megaupload.com. Enter the validation code at the upper right screen, and wait for 45 seconds, a download link will appear and you can download the m-file.
Regards,
0X_R
Are they made by yourself?
wow.. produktif bener lu pen..
Dear Hicha,
Yes, until now, they are all mine. Hoever, if you would like to contribute to MATLAB Aerodynamics Toolbox, you can send my te e-mail and your MATLAB code to my e-mail and I’ll add it to th list above.
Regards, 0X_R
Dear Hicha,
Yes, until now, they are all mine. Hoever, if you would like to contribute to MATLAB Aerodynamics Toolbox, you can send my te e-mail and your MATLAB code to my e-mail and I’ll add it to th list above.
Regards,
0X_R
Good work , keep going
regarding the thin airfoil theory program , use cm_leading_edge = -(pi/2) * ( A0 + A1- A 2/2 )
also the zerolift_angle = – (A0 +A1/2) * 180/pi