[umran]

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

[umran]

As the title suggest, the actual files...

[umran]

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.

[umran]

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.

[umran]

Dear All,
I posted the comparative results here...

[umran]

a little more...

[mbeaudoin]

> 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

[umran]

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.

[mbeaudoin]

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

Originally Posted by umran

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.

[umran]

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

[kruljeb1]

Hello Umran,

I am currently doing my thesis in OpenFOAM, and I would very much appreciate the Onera M6 that you have created. Unfortunately the files that you have shared on the forum have expired. Can I find them somewhere else? If not, would you be so kind to share them again, or maybe send them to iborbk@yahoo.com? I have a mesh, but many problems when running in OpenFOAM.

Thank you and best regards.

[umran]

Hi Boki,
Can you try this new link?

https://www.dropbox.com/s/79nmfx9y5d...eraM6.zip?dl=0

If not so much of a problem to you, in your work, can you quote my publication with the title as the document attached here, https://www.dropbox.com/s/zpcktp1836...15214.pdf?dl=0 refer to ISBN: 978-93-84468-16-3, thanks.

rgds
Umran

[kruljeb1]

Dear Umran,

Thank you very much, I really appreciate it. Absolutely, I will reference your work, it was my intention.

All the best!

[rewol]

Dear Umran,

Should you ever find yourself in Turkey, know that you have a friend.

Thanks.

[umran]

Dear Boki,
Thanks.

Dear Refik,
Thanks for the kind invitation. We (Malaysia Airlines) do have a few of our engineers stationed in Turkey. They are looking after our cargo aircraft which is leased (A330) to your Airlines.

For the rest I hope this paper and files shared bring more light to the elusive compressible flow solver...

[wanghyun88]

Dear. Umran,

Hello, I’m Wanghyun Kim from CFD lab. of Chungnam National University, Republic of Korea.

At first, I am sorry for my poor english ability.

I saw your “Validations of Openfoam Steady State Compressible Solver Rhosimplefoam” paper.

I analyzed Onera M6 wing to increase my Openfoam analysis ability using Rhosimplefoam by reference to your paper.

But I could’t find any details about Case setting of Openfoam files(0, constant, system folder), so I performed analysis using tutorial case.

Nevertheless, My analysis have failed again and again.

Meanwhile, I saw your post at cfd-online forum page fortunately.

FX63137.zip file which you have uploaded does not seem to be Onera M6 case.
(FX63717 seems to be Case using simpleFoam, not rhoSimpleFoam.)

Perhaps Dropbox link seems to be Onera M6 case file. But, I can’t check because link has expired.

I wonder if you can share your Openfoam Case file about Onera M6 wing.

I have learned a lot of Onera M6 parameter(velocity, pressure, temperature, etc.) setting.

If you can share your Onera M6 wing Case file, I will be more helpful.

I will waiting for you reply.

Thank you.

Wanghyun Kim

[umran]

Dear Wang,
Kindly refer to below link. Somehow i did asked for openFOAM developer to include these files as a tutorial case for the next release of openFOAM since 2.2.3, but not happening yet I guessed.


https://www.dropbox.com/sh/tmfgox6os...lqukbYH2a?dl=0

And if not so much of a problem, kindly cite my papers for yours, thanks.

[umran]

And perhaps forumers may try this zip file....

[wanghyun88]

Dear. Umran,

Thank you for your reply.

I will try OpenFOAM analysis using grid which I made by reference to your Case file.

Analysis using your grid comes good result.

but, analysis using my grid has failed.

I will find Case setting for my grid and solve the problem.

Thank you for sharing Case file.

I will tell you if I get convergenced result.

Wanghyun Kim

[umran]

Dear Wang,
Looking forward to your results, thanks.