CFD Online Logo CFD Online URL
Home > Forums > General Forums > Main CFD Forum

Debugging Unsteady 2-D Panel Method Code: Wake Modeling

Register Blogs Members List Search Today's Posts Mark Forums Read

Like Tree1Likes
  • 1 Post By sbaffini

LinkBack Thread Tools Search this Thread Display Modes
Old   May 3, 2009, 07:07
Default Debugging Unsteady 2-D Panel Method Code: Wake Modeling
New Member
T.Rajesh Senthil Kumar
Join Date: May 2009
Location: India, Tamil Nadu, Coimbatore
Posts: 3
Rep Power: 17
RajeshAero is on a distinguished road
am doing my Master's Project on Flapping foil aerodynamics.. Have written unsteady vortex panel code in matlab.. but its not converging after three time steps.. I feel the problem is in wake modeling, especially in measuring the angle between wake and body panels, though I'm not entirely sure... Can anyone help me with this?

Also, if any one wishes to debug my code.. i will send the code.. i need help in debugging my code... if anyone has code in fortran or Matlab or C, kindly send it to me.. it will be helpful to rectify my errors.. Thanks!

Last edited by RajeshAero; May 3, 2009 at 07:11. Reason: Update on the problem
RajeshAero is offline   Reply With Quote

Old   May 9, 2009, 16:23
New Member
yasir abas
Join Date: Mar 2009
Posts: 11
Rep Power: 17
yasir is on a distinguished road
Perhaps this due to wrong calculations of influence coefficients of trial wake,,,,if you send the code i will check it,,,,,,,,,,,,,,,,,,,,
yasir is offline   Reply With Quote

Old   May 9, 2009, 20:45
Senior Member
sbaffini's Avatar
Paolo Lampitella
Join Date: Mar 2009
Location: Italy
Posts: 2,163
Blog Entries: 29
Rep Power: 39
sbaffini will become famous soon enoughsbaffini will become famous soon enough
Send a message via Skype™ to sbaffini
I made this code for my Aero course. It is based on lumped vortex and mean lines only. Moreover the motion is imposed and not calculated.

As i remember the code worked fine but i also remember of some problem
in the convergence of the itereations for the wake points positions at each time step.

Unfortunately i wrote it in italian and i have no time to translate it, but i think it will not be so hard to follow it if you have written your own code...

Hope this helps
Attached Files
File Type: zip (8.5 KB, 174 views)
vahid69 likes this.
sbaffini is offline   Reply With Quote

Old   March 4, 2010, 09:17
Question 2D Unsteady Panel Method
New Member
Join Date: Mar 2010
Posts: 5
Rep Power: 16
rezvan6587 is on a distinguished road
Hi all

I am working on experimental measurement on an airfoil in unsteady motion and I am looking for 2D or 3D panel method Code for comparion my data with some standard cases. Is here any one can help me?

Thank you all

rezvan6587 is offline   Reply With Quote

Old   January 20, 2011, 12:50
Unhappy 2D unsteady panel method kutta condition
New Member
Amit Singh
Join Date: Jan 2011
Posts: 3
Rep Power: 15
amitsingh178 is on a distinguished road
I'm working on a 2D unsteady panel method for harmonic oscillations of a NACA 0012 airfoil. I've been trying to debug the code for ages. I'm getting a nice sinosoidal variation for the lift force but the value of amplitudes are not satisfactory. Does anyone have any source to verify the values I'm getting. Also, while implementing the kutta condition(Basu and Hancock), I'm getting a quadratic equation. So, to choose the correct root, the one closest to the last time step values is chosen. But at even slightly higher frequencies, the two roots are very close and the code doesn't converge anymore. So, I want to know whether there is a better way to choose the correct root so that I can reach higher frequencies.

Thank You.
amitsingh178 is offline   Reply With Quote

Old   November 10, 2011, 05:48
Default Help please !!!!
New Member
Mohamed Mehdi
Join Date: Dec 2009
Posts: 2
Rep Power: 0
Mehdi.numérique is on a distinguished road
I was developped the unsteady panel method using the Hess and Smith method. two types of singularities are used : source and vortex. An additionnal vortex shedding panel have been injected related to the trailing eadge. the problem is that the wake géométrie is not conform whith the bibliography. Can some one help me to detect the wrong part of the code . ( The code is written in Fortran language).
Mehdi.numérique is offline   Reply With Quote


Thread Tools Search this Thread
Search this Thread:

Advanced Search
Display Modes

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

BB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Trackbacks are Off
Pingbacks are On
Refbacks are On

Similar Threads
Thread Thread Starter Forum Replies Last Post
2D Field Panel Method Source Code Shukla Main CFD Forum 3 January 20, 2011 12:51
3D Panel Method Daniel_Cro Main CFD Forum 0 September 19, 2008 03:44
Panel Method Doublet Derivatives Gerrit Groot Main CFD Forum 17 September 17, 2007 09:13
Why use a panel method? gocarts Main CFD Forum 2 April 22, 2007 22:50
panel method Waleed Mohamed Main CFD Forum 2 March 30, 1999 21:26

All times are GMT -4. The time now is 07:38.