Hello, I'm trying to valid
 

Hello,

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 manag
 

Hi 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