[cdomenig]

Hello,

I don't know much about CFD but I need to run some simulations for my bachelor thesis. I want to calculate lift coefficients of a wing for 10 different Mach numbers between Ma 0.1 and Ma 2.5 at various angles of attack. My supersonic and transsonic simulation result are very realistic but my results for low Mach numbers (0.1, 0.3) don't make much sense. I realized that the problem could be related to the fact that I am using the compressible RANS Solver and the SA_COMP turbulence model, so I changed those settings to the incompressible versions. Now, however, my initialization of the free stream conditions doesn't work anymore, unfortunately. I checked the .cfg files of the test cases on SU2's website but they didn't really help.

Could anyone tell me how I could initialize the following flow conditions so that it works with the incompressible solver INC_RANS ?

I would be very grateful for any help!

% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%

MACH_NUMBER=0.1
AOA= 5.0
SIDESLIP_ANGLE= 0.0

INIT_OPTION= TD_CONDITIONS
FREESTREAM_OPTION= TEMPERATURE_FS

FREESTREAM_TEMPERATURE= 288.15 %Based on ISA-atmosphere at altitude of 0m
FREESTREAM_PRESSURE= 101325
FREESTREAM_DENSITY= 1.225

REYNOLDS_NUMBER= 139753.6 %kinematic viscosity 1.461E-5
REYNOLDS_LENGTH= 0.06

[pcg]

Have a look at TestCases/incomp_rans/AhmedBody/turb_ahmed.cfg

[talbring]

Also have a look here: https://su2code.github.io/docs_v7/Physical-Definition/

[cdomenig]

Thank you both!