Rotation/Curvature Correction for Spalart Allmaras model (SA-RC) is explained here.
Complessibility Correction for Spalart Allmaras model (SA-CC) is explained here.
Steady-state simulation of Ahmed Body (slant angle is 30 degrees) using compressible solver was done.
Mesh is explained here.
Solver: rhoLTSPimpleFoam
Wind speed: 60m/s
Turbulence model: SA-RC with and without Compressibility Correction
Div scheme: Gamma NVD scheme
From this article, I changed the value of nuTilda at the inlet to 7.5e-05 (that is 5.0*nu).
・Force Coefficients
・Gradient Contours
Flow separation at the slant was reproduced in the two compressible calculations.
Compressibility Correction didn't make large differences.
・Difference of pressure between compressible and incompressible calculations
In order to see the difference of pressure between the compressible and incompressible calculations, I calculated the difference of Cp (= (p - pRef)/(pDyn at inlet) ).
Complessibility Correction for Spalart Allmaras model (SA-CC) is explained here.
Steady-state simulation of Ahmed Body (slant angle is 30 degrees) using compressible solver was done.
Mesh is explained here.
Solver: rhoLTSPimpleFoam
Wind speed: 60m/s
Turbulence model: SA-RC with and without Compressibility Correction
Div scheme: Gamma NVD scheme
From this article, I changed the value of nuTilda at the inlet to 7.5e-05 (that is 5.0*nu).
・Force Coefficients
Incomp/Comp = incompressible/compressible
DDES = Delayed Detached Eddy Simulation
(no)CC = (not) Compressibility Correction employed
No large difference can be seen among 4 calculations above.
・Gradient Contours
nuTilda of SA-RC Incomp
nuTilda of SA-RC Comp noCC
nuTilda of SA-RC Comp CC
Cp of SA-RC Incomp
Cp of SA-RC DDES Incomp
Cp of SA-RC Comp noCC
Cp of SA-RC Comp CC
Ux of SA-RC Incomp
UMeanX of SA-RC DDES Incomp
Ux of SA-RC Comp noCC
Ux of SA-RC Comp CC
Flow separation at the slant was reproduced in the two compressible calculations.
Compressibility Correction didn't make large differences.
・Difference of pressure between compressible and incompressible calculations
In order to see the difference of pressure between the compressible and incompressible calculations, I calculated the difference of Cp (= (p - pRef)/(pDyn at inlet) ).
CpDiff = CpComp - CpIncomp
CpDiff on ZX Plane
CpDiff on surfaces
CpDiff on surfaces
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