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 yzf1215 November 28, 2012 21:32

Having problem in airfoil calculation

3 Attachment(s)
I'm using rhoSimpleFoam to calculate flow over airfoil. And after several iterations the Ux seem to be zero in the inlet. Also the temperature have some problems.

This is my case

And the mesh

Also, the checkMesh
Checking geometry...
Overall domain bounding box (-14.9978 -15 -0.424248) (15 15 0.424248)
Mesh (non-empty, non-wedge) directions (1 1 0)
Mesh (non-empty) directions (1 1 0)
All edges aligned with or perpendicular to non-empty directions.
Boundary openness (3.30002e-18 -1.7807e-18 -1.66129e-18) OK.
Max cell openness = 1.08077e-14 OK.
Max aspect ratio = 595.261 OK.
Minumum face area = 7.97538e-09. Maximum face area = 1.29329. Face area magnitudes OK.
Min volume = 6.76708e-09. Max volume = 0.341398. Total volume = 681.489. Cell volumes OK.
Mesh non-orthogonality Max: 80.4107 average: 22.3043
*Number of severely non-orthogonal faces: 26.
Non-orthogonality check OK.
<<Writing 26 non-orthogonal faces to set nonOrthoFaces
Face pyramids OK.
Max skewness = 0.864702 OK.

Mesh OK.

End

What fvScheme will you suggest?

 batta31 November 29, 2012 03:36

Hi!

First of all I'll try to correct the error that checkMesh gives to you
Quote:
 *Number of severely non-orthogonal faces: 26. Non-orthogonality check OK. <
I don't know if that's the problem but it will be better if you don't have that failure.

Greetings

Simone

 yzf1215 November 29, 2012 03:43

I have tried this way, eliminated the non-otrhogonal mesh, but the calculation still blows up.

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