Having problem in airfoil calculation
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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 http://pan.baidu.com/share/link?shar...&uk=2234161950 And the mesh http://pan.baidu.com/share/link?shar...&uk=2234161950 Also, the checkMesh Checking geometry... Overall domain bounding box (14.9978 15 0.424248) (15 15 0.424248) Mesh (nonempty, nonwedge) directions (1 1 0) Mesh (nonempty) directions (1 1 0) All edges aligned with or perpendicular to nonempty directions. Boundary openness (3.30002e18 1.7807e18 1.66129e18) OK. Max cell openness = 1.08077e14 OK. Max aspect ratio = 595.261 OK. Minumum face area = 7.97538e09. Maximum face area = 1.29329. Face area magnitudes OK. Min volume = 6.76708e09. Max volume = 0.341398. Total volume = 681.489. Cell volumes OK. Mesh nonorthogonality Max: 80.4107 average: 22.3043 *Number of severely nonorthogonal faces: 26. Nonorthogonality check OK. <<Writing 26 nonorthogonal faces to set nonOrthoFaces Face pyramids OK. Max skewness = 0.864702 OK. Mesh OK. End What fvScheme will you suggest? 
Hi!
First of all I'll try to correct the error that checkMesh gives to you Quote:
Greetings Simone 
I have tried this way, eliminated the nonotrhogonal mesh, but the calculation still blows up.

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