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

hi im a uni student doing aerodynamics i really wanna thank you for your files 🙂

Thanks a ton !!

CalculateVelocityFromSource2D.m is showing there is a problem with the code..not able to get the output. I do not know what the problem is. Please help me.

Can you show me the complete error message displayed in the Matlab’s command window so I can trace the error?

Hi.. Thanks for these code.

Do you think is possible to develop panel method to analyze two airfoil in one column (2D blade to blade analysis). I am a student and my supervisor want me to search how to solve this.

Thanks in advance for your attention.

Abdul

Do you have a program to calculate C_l and C_d using the vortex method?

Thank you for your work, I am currently writing a MACRO set for CATIA using python. Thinking that I am going to have a long rode ahead of me, your work provides a strong basis (pretty much just porting the code).As an offer, I have an ‘old’ MATLAB interface I made for 2D Vortex Panel Method, It was a project for MATLAB. The purpose of the course was Coding in Matlab..so the program just needed to function, it didn’t necessarily need to be accurate. but I would be happy to provide the scripts that I made and the open sources scripts involved (documented in their respective files). I only ask that you provide credit where it is due. Feel free to email me if you interested, gondekm@my.erau.edu. PS..Im a matlab fanatic but python is increadibly portable and very similar

Hello, thank you for sharing the codes. However,I failed to learn from you because of failure in downloading. Would you please send them to me through email?

pls tell how to design a new airfoil using the matlab & simulink

Do you have a code for vortex panel method?

Do you have a code for pressure coefficient with panel method(2D cyllinder)

Hi thank you for your help. ..can I contact you I will need some help

Yes, sure… Find my email at the about page.

how to do optimization of airfoil by varying the length of the wing or thickness..??