|February 21, 2008, 14:45||
Dear foamers, I have some c
Join Date: Mar 2009
Posts: 62Rep Power: 9
I have some convergence problem while running simpleFoam. Both pressure and velocity converges at the beginning to the order of 10^-3, then start to diverge until blowing out. I took a look at the pressure results before diverging and it looks reasonable and smooth. However,after that, I got huge pressure value at some locations, when simulation starts to diverge. Can someone please give me some guidance here? Thanks.
I had a hybrid mesh with fine hexahedra mesh in the wall region in order to use low Reynolds turbulence model.
Here is what I got from checkMesh,
Boundary openness in x-direction = -1.2949e-19
Boundary openness in y-direction = -2.43946e-18
Boundary openness in z-direction = 3.92812e-19
Boundary closed (OK).
Max cell openness = 1.0842e-19 Max aspect ratio = 33.7858. All cells OK.
Minumum face area = 1.85108e-08. Maximum face area = 0.00063044. Face area magnitudes OK.
Min volume = 2.9974e-11. Max volume = 5.37019e-06. Total volume = 0.36159. Cell volumes OK.
Number of non-orthogonality errors: 0. Number of severely non-orthogonal faces: 581.
Mesh non-orthogonality Max: 77.6364 average: 19.9435
Non-orthogonality check OK.
--> FOAM Warning :
From function primitiveMesh::checkFaceSkewness(const bool report, labelHashSet* setPtr) const
in file meshes/primitiveMesh/primitiveMeshCheck.C at line 838
Large face skewness detected. Max skewness = 256.281 percent.
This may impair the quality of the result.
37 highly skew faces detected.
Writing 37 skew faces to set skewFaces
Minumum edge length = 1.59999e-05. Maximum edge length = 0.0455865.
All angles in faces are convex or less than 10 degrees concave.
Face flatness (1 = flat, 0 = butterfly) : average = 0.999997 min = 0.997836
All faces are flat in that the ratio between projected and actual area is > 0.8
Geometry check done.
Number of cells by type:
tet wedges: 0
Number of regions: 1 (OK).
Here is what's inside fvSchemes and fvSolution
default Gauss upwind;
div(phi,U) Gauss upwind;
div(phi,k) Gauss upwind;
div(phi,epsilon) Gauss upwind;
div(phi,R) Gauss upwind;
div(R) Gauss linear;
div(phi,nuTilda) Gauss upwind;
div((nuEff*dev(grad(U).T()))) Gauss linear;
default Gauss linear limited 0.7;
laplacian(nuEff,U) Gauss linear limited 0.7; //Gauss linear corrected;
laplacian((1|A(U)),p) Gauss linear limited 1; //Gauss linear corrected; //Gauss linear limited 0.7;
laplacian(DkEff,k) Gauss linear limited 0.7;
laplacian(DepsilonEff,epsilon) Gauss linear limited 0.7;
laplacian(DREff,R) Gauss linear corrected;
laplacian(DnuTildaEff,nuTilda) Gauss linear limited 0.7;
p AMG 1e-08 0.01 200;
U BICCG 1e-08 0.0;
k BICCG 1e-06 0.0;
epsilon BICCG 1e-06 0.0;
R BICCG 1e-06 0.0;
nuTilda BICCG 1e-06 0.0;
|Thread||Thread Starter||Forum||Replies||Last Post|
|convergency problem at mach 3||emrah||FLUENT||0||May 21, 2008 01:39|
|I have a problem with the convergency of a case||Raul Martin||FLUENT||3||August 24, 2006 04:44|
|convergency problem||enis||Main CFD Forum||0||July 27, 2005 09:27|
|convergency||guang ai||CD-adapco||1||June 30, 2005 04:24|
|PCG convergency||Steve Song||Main CFD Forum||2||January 16, 2003 04:47|