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[Other] blockMeshDict missing for airfoil2D tutorial |
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December 9, 2015, 18:45 |
blockMeshDict missing for airfoil2D tutorial
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#1 |
Senior Member
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I am new to OpenFOAM. After going through cavity and dam break tutorials, I finally moved on to airfoil2d tutorial. First thing I checked for familiar files like blockMeshDict, etc. Its missing!
After doing some reading on internet and this forum, it seems that the mesh file for this case is not created in the usual way. But, where is the simulation getting its mesh? How can I check the file used for creating the mesh for this simulation? I checked the Allrun file. It has no indication of where the mesh is coming from. Eventually, how do I run this simulation? |
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December 10, 2015, 02:00 |
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#2 |
Senior Member
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Hi,
http://www.cfd-online.com/Forums/ope...airfoil2d.html It is the first link on results page of the https://www.google.fr/search?q=openfoam+airfoil2d+mesh. And you can generate airfoil meshes with different external software, construct2d for example. Do not know what was used for the case. |
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December 10, 2015, 02:10 |
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#3 |
Senior Member
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I have already gone through that link. I understand that the mesh is already created, but then the question is still unanswered - where is the mesh file? It has to be somewhere.
I do not know what was used for the case. This is what I got with the OpenFOAM installation itself. Last edited by thunde47; December 10, 2015 at 11:47. |
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January 10, 2016, 02:36 |
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#4 |
Senior Member
Join Date: Aug 2013
Posts: 407
Rep Power: 15 |
Hi,
I have no idea what was used to create the mesh either. But to answer your question, the mesh for the case is present (as usual in OF) in constant/polyMesh. The files - faces, points, neighbours, owners and cells - pretty much convey all the information to OpenFOAM about the mesh. Cheers, Antimony |
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January 12, 2016, 03:17 |
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#5 |
Senior Member
Join Date: Aug 2013
Posts: 407
Rep Power: 15 |
Hi,
In case anyone is interested, here is my version of a working blockMeshDict for an airfoil case. It is based on the NACA0012 airfoil, with the trailing edge extrapolated to a single point and the subsequent chord length rescaled to unit length The interpolation points for the splines are the points listed for NACA0012 in the UIUC database. Cheers, Antimony |
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