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- - **Steady state transsonic turbulent flow **
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Hello,
I'm trying to validHello,
I'm trying to validate some experimental data for steady pressure measurements on a 3D wing with a Mach number of 0.8. I've been trying to use rhoSimpleFoam, but the pressure gets very high after just a few iterations. After reading on the forum, I understood that rhoSimpleFoam is not good for trans-sonic flows. Therefore I have an idea of trying to modify sonicTurbFoam to solve a steady state calculation, but I'm not sure how to do that. Any help or suggestions are most welcome, thank you for your interest. |

Hi again,
I have not managHi again,
I have not managed to modify sonicTurbFoam to a steady solver, so instead I'm doing a transient calculation on my case. However, it is starting to diverge after a while, and I don't understand why. I'm thinking there might be something wrong with my mesh, the result from checkMesh can be seen below. The problem is set up by a 3D wing in a half-sphere far field, the mesh is completely tetrahedal. Mesh stats points: 200098 faces: 2231127 internal faces: 2161985 cells: 1098278 boundary patches: 6 point zones: 0 face zones: 0 cell zones: 0 Number of cells of each type: hexahedra: 0 prisms: 0 wedges: 0 pyramids: 0 tet wedges: 0 tetrahedra: 1098278 polyhedra: 0 Checking topology... Boundary definition OK. Point usage OK. Upper triangular ordering OK. Face vertices OK. Number of regions: 1 (OK). Checking patch topology for multiply connected surfaces ... Patch Faces Points Surface topology far-field 1206 632 ok (non-closed singly connected) symm 5520 2885 ok (non-closed singly connected) arw_trailing 506 508 ok (non-closed singly connected) arw_tip 730 433 ok (non-closed singly connected) arw_lower 30529 15611 ok (non-closed singly connected) arw_upper 30651 15672 ok (non-closed singly connected) Checking geometry... Overall domain bounding box (-2.08446e-14 -22.5 -22.4974) (22.4989 22.5 22.4974) Mesh (non-empty) directions (1 1 1) Mesh (non-empty, non-wedge) dimensions 3 Boundary openness (1.04741e-18 7.20372e-19 2.7995e-19) OK. Max cell openness = 1.64485e-16 OK. Max aspect ratio = 8.5273 OK. Minumum face area = 3.30537e-06. Maximum face area = 5.81775. Face area magnitudes OK. Min volume = 3.02341e-09. Max volume = 3.70366. Total volume = 23746.7. Cell volumes OK. Mesh non-orthogonality Max: 74.3269 average: 19.577 *Number of severely non-orthogonal faces: 38. Non-orthogonality check OK. <<Writing 38 non-orthogonal faces to set nonOrthoFaces Face pyramids OK. Max skewness = 0.845377 OK. Mesh OK. End Please tell me what information is of interest and I will post it here. I appreciate any help I can get. |

Dear Mathias,
did you manage Dear Mathias,
did you manage to solve your convergence problems? I am facing the same difficulties as you did for a subsonic, steady state and turbolent flow around a wing (I am using simpleFoam), see the complete discussion here. Maybe you could give me some advices... Thanks, Maddalena |

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