Issues with Low Mach Number Simulations #2476
Description
Hello,
I am doing simulation of flow around sphere at Re=1.32E5 (Near to the critical region). I tried both compressible and incompressible solvers of SU2 and both underestimate the drag by almost 100%. I am using a structured mesh with approximately 22K points on the sphere surface (The sphere is divided into 6 domains with 61x61 points). The results are consistent with both central and upwind schemes (2nd Order) for the incompressible solver while for the compressible solver L2ROE scheme diverges immediately after the solver starts. The central scheme JST works and also underestimates the drag.
The case is not a transitional case since the flow separates laminarly from the surface. The results are not affected much by the use of transition model with k-omega SST model.
The experimental drag is 0.5 whereas the RANS approximations are in the range 0.2-0.25. Interestingly, the same solver settings and mesh provide accurate results for Re=1E4. The experimental drag is 0.4 whereas the RANS approximation is 0.397.
Case Files: https://drive.google.com/drive/folders/1cEqlithNmy7no6H98wWrfpRHvL3coHKZ?usp=sharing
Bug report checklist
Please make sure that you have followed the checklist below, many common problems can be solved by:
- [-] Consulting the build instructions (https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/).
- [-] Looking for similar problems on GitHub or CFD-Online (https://www.cfd-online.com/Forums/su2/).
- [-] Updating to the newest version of SU2 (either develop, master, or the pre-built executables https://su2code.github.io/download.html).
Desktop (please complete the following information):
- OS: Linux
- C++ compiler and version: GNU 12.2.0
- MPI implementation and version: openMPI 4.1.4
- SU2 Version: v8.0.0