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Old   October 10, 2014, 14:41
Default New to OpenFOAM? - so am I
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Umran Abdul Rahman
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Dear All,
First of all i would like to thanks everyone here in OpenFOAM threads who have been continuously helping fellow forumers in the tactics and techniques in using this great tool.

https://www.dropbox.com/s/x6c317d932...roach.pdf?dl=0

Attached is a simple usage guides I came out with after studying this forum, reading the usage manuals and off course browsing the technical papers on it.

And if God willing i'll be sharing more test cases to this forum.

Once again thanks.
Umran Abdul Rahman
B.Eng (UKM) MSc (ITB) D.Eng (Student - UPM)
A380 Fleet Duty Engineer
Malaysia Airlines
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Old   October 10, 2014, 14:52
Default the files
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Umran Abdul Rahman
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As the title suggest, the actual files...
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File Type: zip FX63137.zip (14.2 KB, 30 views)
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Old   October 18, 2014, 11:38
Default Onera M6 rhoSimpleFoam
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Umran Abdul Rahman
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As the tittle suggest, i managed to mesh the Onera M6 wing using blockmesh alone to make it a fully structured mesh and successfully run a steady state simulation using rhoSimplefoam.

http://youtu.be/fNKUrZnH3So?list=UUe...ve5H3uKJ5mbf7g

Kindly refer to the above youtube video. This will be my publication work in establishing rhoSimplefoam validity in solving a steady state transonic flow.

Once my paper being accepted, i'll share the whole working file with the rest of the forumers here. Mind you, i spend almost 8 months to get a proper mesh with zero warning or cautions from checkMesh -allGeometry -allTopology and i guessed that is the whole trick in getting it to run smoothly and converge. Hopefully this test case can be use as a tutorial case for compressible solver in the next release of openFOAM.

As it is, the attachment shows the residuals for all the parameter.
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File Type: jpg residuals.jpg (32.8 KB, 23 views)
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Old   December 11, 2014, 02:57
Default Onera M6 rhoSimpleFoam
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Umran Abdul Rahman
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Dear Ladies & Gents,
My paper "Validation of OpenFOAM® steady state compressible solver rhoSimpleFoam" has been reviewed and will be published soon after "International Conference on Mechanical And Industrial Engineering (ICMAIE’2015) Feb. 8-9, 2015 Kuala Lumpur, Malaysia.", the ref is IAE0215214.

Since it has been accepted for publication, as previously promised i will share the working folder of this simulation.

https://www.dropbox.com/s/79nmfx9y5dahaic/OneraM6.zip?dl=0

As usual kindly unzip the file into your run environment, point to it, and run it using ./Allrun. If you want to do manual running, please go ahead.

At this current moment, there is no fault registered for this ONERA M6 mesh, and if one is interested in developing other compressible solvers, this will be a good foundation for testing.

As for the paper itself, i given the copyright to IAIMAE, so if it can be open to public, then i'll update here.

Tq All.

p/s... openFOAM developer, just hoping that on your next release, this file can be part of your tutorial file. This is because as you all know, dropbox links are limited in time.
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Old   December 23, 2014, 12:26
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Umran Abdul Rahman
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Dear All,
I posted the comparative results here...
Attached Images
File Type: jpg 20%.jpg (25.3 KB, 17 views)
File Type: jpg 44%.jpg (25.0 KB, 12 views)
File Type: jpg 65%.jpg (24.7 KB, 14 views)
File Type: jpg 80%.jpg (24.6 KB, 13 views)
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Old   December 23, 2014, 12:28
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Umran Abdul Rahman
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a little more...
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File Type: jpg 95%.jpg (24.7 KB, 6 views)
File Type: jpg 99%.jpg (25.8 KB, 7 views)
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Old   December 23, 2014, 13:02
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Martin Beaudoin
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> p/s... openFOAM developer, just hoping that on your next release, this file can be part of your tutorial file. This is because as you all know, dropbox links are limited in time.

Would it be possible for you to publish your experimental data as well?
Then, instead of becoming yet another tutorial, this case could also be part of a V&V test loop.

Martin
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Old   December 23, 2014, 13:47
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Umran Abdul Rahman
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Dear Martin,
The experimental values were taken from "Schmitt, V. and F. Charpin, "Pressure Distributions on the ONERA-M6-Wing at Transonic Mach Numbers," Experimental Data Base for Computer Program Assessment. Report of the Fluid Dynamics Panel Working Group 04, AGARD AR 138, May 1979."

Anyway here are the obtained results by above authors. It maybe old, but it has been used as a bench mark for many transonic flow solvers. In fact when i wanted to use this rhoSimpleFoam solver in investigating my primary research which is awkward pressure distribution on thin structure surfaces due to airflow interaction of between wing and fuselage for commercial jets (mach 0.8 to 0.9), i find it very difficult to pin point the validity of this solver for my case study. This drives the publication of these results.

In case there are developers out there, provide me with an email address, i'll send him or her the excel format files.
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Old   December 23, 2014, 14:21
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Martin Beaudoin
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Hello Umran,

Thanks for the pointer to the PDF file.

I am pretty sure your test case + experimental values would be a nice and appreciated contribution to the foam-extend project.
https://sourceforge.net/projects/openfoam-extend
https://sourceforge.net/p/openfoam-e...i/master/tree/

The admins of the project are really easy to get in touch with...

And if you are interested, we can show you how to contribute your test case so it could eventually be merged to the project, and automagically integrated to the project's test harness.

Best,

Martin


Quote:
Originally Posted by umran View Post
Dear Martin,
The experimental values were taken from "Schmitt, V. and F. Charpin, "Pressure Distributions on the ONERA-M6-Wing at Transonic Mach Numbers," Experimental Data Base for Computer Program Assessment. Report of the Fluid Dynamics Panel Working Group 04, AGARD AR 138, May 1979."

Anyway here are the obtained results by above authors. It maybe old, but it has been used as a bench mark for many transonic flow solvers. In fact when i wanted to use this rhoSimpleFoam solver in investigating my primary research which is awkward pressure distribution on thin structure surfaces due to airflow interaction of between wing and fuselage for commercial jets (mach 0.8 to 0.9), i find it very difficult to pin point the validity of this solver for my case study. This drives the publication of these results.

In case there are developers out there, provide me with an email address, i'll send him or her the excel format files.
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Last edited by mbeaudoin; December 23, 2014 at 18:04.
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Old   December 25, 2014, 14:44
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Umran Abdul Rahman
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Dear Martin,
I saw the OpenFOAM extend links... honestly i wouldn't know how to go about it. Anyway as i mentioned before, I believe the most difficult part for this validation is the mesh itself (blockMeshDict file included where it is one to one ratio to the actual model) and of course the fvSchemes and fvSolution input (note the relaxations factors).

Anyway this page shows the validity of WIND solver by Prof JW. Slater where the details of the original 1979 paper can be obtained.

Rgds
Umran
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