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June 7, 2019, 13:03 
rhoSimpleFoam not working

#1 
New Member
Edoardo
Join Date: Mar 2019
Posts: 15
Rep Power: 7 
Hello everybody,
I am working (trying to ) on an external aerodynamic case with a compressible flow and I need to use a steady state solver. So I need to use rhoSimpleFoamm but the problem is that I am not able to let it run. What I know is the velocity field at the inlet Ma=0.6 and the p_inf (static) which is 35000 Pa. So I imposed the correspondent velocity at the inlet and the value of p_inf at the outlet. At first I had the problem that the sim was not able to start, but then I managed to limit the temperature between a maximum value and a minimum value and the sim started but after 50 iteration I had the temperature residual equal to 1 and then crashed. I know that the problem is due to the BCs. I add the BCs for U,T,p. Let me know if u need something else. T Code:
dimensions [0 0 0 1 0 0 0]; internalField uniform 236; boundaryField { inlet { type fixedValue; value uniform 236; } outlet { type inletOutlet; value uniform 236; inletValue uniform 236; } "nosebodywingstail" { type fixedValue; value uniform 236; } SphereW { type cyclicAMI; value $internalField; } SphereS { type cyclicAMI; value $internalField; } } U Code:
dimensions [0 1 1 0 0 0 0]; internalField uniform (0 0 0); boundaryField { inlet { type fixedValue; value uniform (0 185 0); } outlet { type zeroGradient; } "nosebodywingstail" { type fixedValue; value uniform (0 0 0); } SphereW { type cyclicAMI; value $internalField; } SphereS { type cyclicAMI; value $internalField; } } p Code:
dimensions [1 1 2 0 0 0 0]; internalField uniform 35687; boundaryField { inlet { type zeroGradient; } outlet { type fixedValue; value uniform 35687; } "nosebodywingstail" { type zeroGradient; } SphereW { type cyclicAMI; value $internalField; } SphereS { type cyclicAMI; value $internalField; } Cheers, CutMountain. 

June 7, 2019, 16:22 

#2 
Senior Member
Lasse Brams Vinther
Join Date: Oct 2015
Posts: 112
Rep Power: 10 
Hello cutmountain, would it be possilbe to upload the case for potential debugging? It could be an issue with fv solution oe schwme, I had a similar problem recently, being due to no residual control of h as e was specified inatead.
Regards Lasse 

June 8, 2019, 06:56 

#3 
New Member
Edoardo
Join Date: Mar 2019
Posts: 15
Rep Power: 7 
Dear Swagga,
thanks for caring. here there are my fvSolution, fvSchemes and fvOptions. I hope that my problem is the same as yours. You think that the boundary conditions are well posed? fvSolution Code:
solvers { p { solver GAMG; tolerance 1e08; relTol 0.1; smoother GaussSeidel; nCellsInCoarsestLevel 20; } "(Uekomega)" { solver GAMG; tolerance 1e08; relTol 0.1; smoother GaussSeidel; nCellsInCoarsestLevel 20; } } SIMPLE { nNonOrthogonalCorrectors 10; rhoMin 0.1; rhoMax 10.0; transonic no; consistent yes; } relaxationFactors { fields { p 0.4; rho 0.01; T 0.01; } equations { p 0.4; U 0.6; e 0.4; k 0.6; omega 0.6; } } fvSchemes Code:
ddtSchemes { default steadyState; } gradSchemes { default cellLimited Gauss linear 0.333; } divSchemes { default none; div(phi,U) bounded Gauss upwind; div(phi,k) bounded Gauss upwind; div(phi,omega) bounded Gauss upwind; div(((rho*nuEff)*dev2(T(grad(U))))) Gauss linear; div(phi,e) bounded Gauss upwind; div(phid,p) bounded Gauss upwind; div(phi,Ekp) bounded Gauss upwind; div((phiinterpolate(rho)),p) bounded Gauss upwind; } laplacianSchemes { default Gauss linear uncorrected; } interpolationSchemes { default linear; } snGradSchemes { default limited 0.333; } wallDist { method meshWave; } fluxRequired { default no; p ; } fvOptions Code:
limitT { type limitTemperature; active true; limitTemperatureCoeffs { Tmin 30; Tmax 1000; selectionMode all; } } Cheers, CutMountain. 

June 8, 2019, 07:08 

#4 
Senior Member
Lasse Brams Vinther
Join Date: Oct 2015
Posts: 112
Rep Power: 10 
How does your thermophysical property file look?
I havn't used cyclicAMI before, but could you give an illustration of the domain with the different patch names? I would suggest simply changing all the patches that aren't inlet or outlet to a simple wall to determine if its the boundary conditions, however the conditions seems fine from an initial glance. Just a side note is it correct that the temperature is 236Kelvin? Regards Lasse 

June 8, 2019, 07:41 

#5 
New Member
Edoardo
Join Date: Mar 2019
Posts: 15
Rep Power: 7 
This is the thermo
Code:
thermoType { type hePsiThermo; mixture pureMixture; transport sutherland; thermo hConst; equationOfState perfectGas; specie specie; energy sensibleInternalEnergy; } mixture { specie { nMoles 1; molWeight 28.9; } thermodynamics { Cp 1005; Hf 0; } transport { As 1.4792e06; Ts 116; } } The domain is a body inside a "windtunnel" that has a shape close to a bullet so I have just an inlet (the lateral surface of the bullet) and the outlet. I used the AMI because I had done two mesh separately and then merged because later I will have the necessity to turn the geometry, so instead of remeshing everytime I just rotate one of the two mesh and then I will merge them. But this work because I firt run some incompressible sim and they went very well and all of them converged. Maybe this mesh done in that way is not good for the compressible solver? (I can try to have a unique mesh and see if it works in that way) But the think that (from what I've learned, cause I always did incompressible sim) the pressure boundary conditions works differently between inc and compr solver so my concern is about the pressure BC. You think that it is ok? 

June 8, 2019, 15:27 

#6 
Senior Member
Lasse Brams Vinther
Join Date: Oct 2015
Posts: 112
Rep Power: 10 
I don't see any issues with your pressure BC's, maybe check out the tutorial case in tutorials>compressible>rhoSimpleFoam>angledDuctExplicitFixedCoeff or aerofoilNACA0012 for some comparability to your case.
Note that the tutorials are based upon openFOAM v6 don't know if its different from other distributions. You are welcome to share your case if able, I'm not certain what else to suggests. You could try the following fvSolution code: Code:
solvers { p { solver GAMG; tolerance 1e08; relTol 0.1; smoother GaussSeidel; nCellsInCoarsestLevel 20; } "(Uekomega)" { solver GAMG; tolerance 1e08; relTol 0.1; smoother GaussSeidel; nCellsInCoarsestLevel 20; } } SIMPLE { nNonOrthogonalCorrectors 10; pMinFactor 0.1; pMaxFactor 10.0; transonic yes; consistent yes; } relaxationFactors { fields { p 1; } equations { p 1; U 0.9; e 0.8; k 0.9; omega 0.9; } } 

June 14, 2019, 08:52 

#7 
Member
Giovanni Medici
Join Date: Mar 2014
Posts: 46
Rep Power: 12 
Have you tried decreasing the number of SIMPLE > nNonOrthogonalCorrector,?
As you are solving with a steady state solver, there is no requirement of convergence on each tilmestep, you will reach it through relaxation factor. If the reason of an high nNonOrthogonalCorrector is mesh quality, I would tackle that problem in the first place. You may find some interesting infos here: By the way rhoSimpleFoam is a quite picky solver, hence maybe an initialization of the flow field (in particular U), with potentialFoam may help. Have you tried initializing the U domain with potentialFoam? and with an internal value different than 0 (in your case something like (0 185 0) )? In order to cross check BC may I suggest you to take a look to the aerofoilNACA0012 tutorial? 

December 18, 2020, 03:53 

#8 
Senior Member
Michael Alletto
Join Date: Jun 2018
Location: Bremen
Posts: 615
Rep Power: 15 
Maybe it's a bit late but there is a OneraM6 wing tutorial available which was run with rhoSimpleFoam:
https://wiki.openfoam.com/OneraM6_by_Michael_Alletto 

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compressible, openfoam, rhosimplefoam 
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