Panel Method Based 2-D Potential Flow Simulator

This potential flow simulator simulates the flow past bodies of arbitrary shape including airfoils.

Description

This potential flow simulator simulates the flow past bodies of arbitrary shape including airfoils. With this simulator, we can do the following tasks,

► Compute and plot the Velocity Vector Plot of the flow past the selected body.
► Compute and plot the Pressure Distribution in terms of both Cp ( pressure coefficient ) and 1-Cp.
► Compute and plot the cL Vs alpha Curve of the selected body.
► Export the pressure distribution and the cL-Alpha data at various angles of attack as Ms.Excel file.
► Capture the images that are generated in the simulator (Profile and mesh details of the body, Vector plot, Cp distribution and cL - alpha Curve ) as .jpg files.

Salient Features

● Automatic name generation for exporting the data and capturing the images to avoid the confusions that are very common in any Scientific Computing.
● Total of 9 Arbitrary bodies coordinates files are included in the simulator as default. You can also generate your own coordinates file of any shape and associate with the simulator.
● Total of 1550 Airfoils coordinates files are provided with the simulator ( All are checked for compatibility so that the simulator can read without any problem ).
● One can view the pressure distribution for range of angles attack dynamically and interactively
● The Menu lists the available data files very dynamically. Even if the data files are added, removed or renamed when the simulator is open ( before running the simulation ), the simulator detects it and updates the list.
● Well Customization is made possible through the Options menu
● Extensive Help is also included for better utilization.
● All of these are kept in a attractive and user friendly Graphical User Interface.

• MATLAB release: MATLAB 7.0.1 (R14SP1)
• Other requirements: Screen Resolution of 1024 x 768

[Zygmunt Wysocki]

 

[kp singh]

 

[Diogo Zuluaga]

 

[Derek Jones]

Didn't work at first but author responded with a quick fix. Good basic tool but could use Cd and L/D plots vs. alpha to be more useful to me.

[Theodore Van Rooy]

This toolbox is pretty cool. First of all the strengths are that it is GUI, and the GUI works well and is intuitive for the most part. Secondly, for the novice wing designer it allows you to visualize your wing and the laminar flow around it.

On the con side, this toolbox will not be good for batch processing or full fledged scientific research. It also lacks the ability to modify your wing shape within the GUI...a feature that would be very nice. It could also be nice to have the ability to plot the wing shape and the corresponding pressure gradients (not jsut potential flows) on the wing.

Overall, this is a good place to start in CFD for airfoil design.

[tom Mueller]

 

[falcon1.44 falcon1.44]

 

[Robson Feijó]

 

[Erik Tylczak]

Code does not function properly with some earlier versions of MATLAB (around 7.0.1). This is due to the use of [panzoom], which was not yet a defined function. This error can be circumvented with at least some earlier versions of MATLAB by commenting out or deleting the following lines:

852
922
1071
1195
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1944
1953
1963

Author is very helpful in support of the code.

[Irvan Afiat]

I want to know as well as design of airfoil

[Eric D. Laird]

This program is exactly what I've been looking for. A few superficial modifications to get it to work on my linux machine, and I was up and running. Thanks!

[hossein saiedi]

 

[hamid moaiieri]

 

[Bey Mohammed]

C'esi un bon travail. je travail sur la modélisation des éoliennes et j'ai développé un programme en MATLAB version 6.5 qui calcule la distribution de préssion autour de profil basant sur la méthode des singularités et il calcule aussi la vitesse de rotation de la turbine.

[Omar Bizri]

Good content

[Benjamin Sanderse]

under linux i had to change all backward slashes to forward slashes... otherwise it does not recognize the folders

[mohammed mahdi]

gooooooood

[Roger Martinez]

excellent!
But only limited for degree [-16,16] an arbitrarial form [-45,45].
solo esta para trabajar con angulos de [-16,16] y para arbitrarias formas unos angulos de [-45,45] seria bueno que lo habilitaras.

[Matt Stevenson]

 

[Remux Wu]

Thank you so much

[cotan elena]

n/a

[chris johnson]

much useful

[try ono]

thank you

[terry Haung]

Thank you for providing it. May i ask you some question about mesh and signal.

[naing lwin]

 

[ucho ucho]

 

[Xu Sam]

 

[ZerO]

please please please always check Ira.H.Abbott and the others,
aerodynamics for engineering students is nice ,but will always give u this cp error and as a result ,wrong aero forces .

[ZerO]

 

[ZerO]

been many years giving ppl wrong results ,its ur time to check now ,isnt it !!!

[ZerO]

comparing the results with :(Theory of wing section-Ira.H.Abbott)(naca report no.411/452-Theodore theodorsen1931/1940)(nasa.tm.no4741)(professor Richard.L.Fearn code)(Rhinoceros-design foil code),man can find that u have to check again please.

[Divahar Jayaraman]

The Hess-Smith panel method is implimented in this code, It has been validated with Hess code.

Every theory has its own limitation, thus the results of this code (Hess-Smith's algorithm) will not perfectly match with experimental or other results.

[ZerO]

Exactly True , this code will not perfectly match with experimental or other results,thank you for your comment.

[jay willis]

Thanks - this simple model is exactly what I needed, but I had to get rid of panzoom - thanks Erik Tylczak for posting the line numbers.

[Yi]

Thanks for your code. From the introduction I know it is a very nice code. But why I cannot run it? I downloaded and extracted get same files as shown in the web. Then I ran matlab code: Potential_Flow_Simulator, chose the airfoil and simulation. But matlab gave me warnning. What's wrong with my step? Could you please tell me? Thanks

[Marc Grossman]

I was unable to get this to work. None of the airfoil data files seemed to load when the gui opened although they were in the proper folders. When I clicked on File>Choose Airfoil Coordinate File, there were no available files to choose, however if I browse to the folder where the function is supposed to load from there are plenty of airfoil files. Any suggestions?

[Deka]

Although need some addressing adjustment to run on unix, it is good :D
Thanks

[kitesurfercharlie Seviour]

Does anyone know how to reverse engineer this code to include mutliple blades i.e. for biplanes?

[Deka]

hi, do you know which parts need to be edited when i need to simulate an immersed finite pipe-like object? is it doable?

[Willie Anderson]

Your package computes pressure and cL for arbitrary alpha and Re. Will it compute cD and the coefficient of pitching moment? If so, it could be used to very easily generate airfoil data for X-Plane, which is the most popular flight simulator (and more importantly, aircraft modeling platform) on the planet.