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September 15, 2011, 12:10 
SST SimpleFoam Convergence Problems

#1 
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Hey Everybody,
I´am trying to simulate the flow over a backwardfacing step. (2D, SST, steadystate) But I don´t get any convergence. (I am looking at residuals and flow solution) I´ve imported the mesh from icem and as the geometry is quite simple I presume theres no mesh error. (6450 cells) I am running lowRe with the yPlus values: Patch 3 named BOTTOM y+ : min: 0.303561 max: 6.06216 average: 2.17811 Patch 4 named HOTWALL y+ : min: 0.0991544 max: 6.86093 average: 2.33885 Patch 5 named STEP y+ : min: 0.458733 max: 5.17977 average: 2.02599 Here are the fvSchemes and fvSolution. I have also attached the whole setup. Thanks for Help! Camoesas fvSchemes: Code:
ddtSchemes { default steadyState; } gradSchemes { default Gauss linear; grad(p) Gauss linear; } divSchemes { default none; div(phi,U) Gauss linearUpwind grad(U); div(phi,k) Gauss upwind; div(phi,omega) Gauss upwind; div((nuEff*dev(T(grad(U))))) Gauss linear; } laplacianSchemes { default Gauss linear corrected; } interpolationSchemes { default linear; } snGradSchemes { default corrected; } fluxRequired { default no; p; } Code:
solvers { p { solver PCG; preconditioner DIC; tolerance 1e06; relTol 0.1; } U { solver PBiCG; preconditioner DILU; tolerance 1e05; relTol 0.1; } T { solver PBiCG; preconditioner DILU; tolerance 1e05; relTol 0.1; } k { solver PBiCG; preconditioner DILU; tolerance 1e05; relTol 0.1; } omega { solver PBiCG; preconditioner DILU; tolerance 1e05; relTol 0.1; } } SIMPLE { nNonOrthogonalCorrectors 0; } relaxationFactors { p 0.3; U 0.7; k 0.7; epsilon 0.7; R 0.7; nuTilda 0.7; } 

September 15, 2011, 13:29 

#2 
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Felix L.
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Good evening, Camoesas,
I presume your mesh is fully orthogonal and the wall is appropriately resolved cellsizeratiowise? There are two things I'd comment to: 1. You say youre running the case on LowRe (Whats the Reynolds number of your case anyway?) and the y+ values at your wall are quite okay for that. So the mesh seems to be ready for a simulation with fully resolved wall boundary layers. But your BCs for nut and k still impose wall functions! (for omega this is okay as omegaWallFunction works for all y+ values) This is incorrect since the wall functions are only suitable for y+ > 30! 2. Tighten the tolerance for omega in fvSolution a bit. Set it to something like 1e20, as you can see in your residuals plot the omega equation converges rather quickly and isn't being solved anymore after that. It's better for the solution process to keep the omega tolerance quite tight. Greetings, Felix. 

September 15, 2011, 13:41 

#3 
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Hi Camoesas,
I simulate a backwardFacing Step, too and had problems with the convergence. Are you doing the Driver and Seegmiller backwardsFacing Step? I coudn't open your attached file, but it's maybe a problem with my system. Therefore I don't know what Boundary Conditions you are using. I have an acceptable solution for incompressible,steadyState and kOmegaSST. I'm using the solver simpleFOAM. I used following BC: Wall: U = fixed Value 0; p= zeroGradient; k= fixedValue 0; omega = fixedValue 1e8, nu_t=calculated Inlet: U = fixedValue U_in; p=zeroGradient Outlet: U=zeroGradient, p=fixedValue; Your fv_solution seems OK. I used in the fv_schemes everywhere Gausslinear corrected, but I think your schemes are working as well. I hope this helps you a little bit. Greetings blacksquirrel Last edited by blacksquirrel; September 15, 2011 at 14:08. 

September 19, 2011, 05:35 

#4 
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HI Felix,
HI blacksquirrel, 1) I Have an Reynolds Number of 28000 (calculated with step high) 2) I am using the Paper of Vogel: "Combined Heat Transfer and Fluid Dynamic Measurements Downstream of a BackwardFacing Step" (1985) The aim is to add heat transfer some day... 3) I have decreased tolerance a for omega a little bit ( 15 orders of magnitude:) from 1e5 to 1e20 4) Now I am using the following boundary conditions: Inlet: U = fixed 11.3; p = zero G; k = fixed 7.6e4; omega = fixed 0.55; nut calculated 0; Outlet: U = zero Gr; p = 0; k = fixedValue 7.6e4; omega = fixed 0.55; nut calculated 0; Walls: U = 0; p = zero Gr; k = fixedValue 7.6e4; omega = fixed 0.55; nut calculated 0; 5) What boundary conditions do I have to set for k omega and nut for a free slip boundary condition? Or where can I find a Answer to this question? I still get weird solutions for my problem. I think the mesh cant be a Problem, because its simple and checkMesh says its ok. Is there any other source of stupid errors I could have made? thanks Camoesas 

September 19, 2011, 06:19 

#5 
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Hello Camoesas,
Sorry, I can't answer your question no. 5. But at the wall the boundary Condition of k should be 0. Because k is calculated from U', which is 0 at the Wall. greetings Black Squirrel 

September 19, 2011, 08:35 

#6 
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Felix L.
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Good afternoon, Camoesas,
your wall boundary conditions are still wrong. Like the black squirrel said, k has to be set to 0 at the wall (for boundary layer resolving meshes!). Also, omega needs to be set to a value according to your first cell layer height  see http://turbmodels.larc.nasa.gov/sst.html for the formula. I recommend using omegaWallFunction (like I said in the second post!), because it does the calculation automatically. Free slip condition means no slip? Either use the noslip boundary condition or symmetry. These are basically the same. Greetings, Felix 

September 19, 2011, 13:02 

#7 
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HI Everybody!
I have choosen my boundary inlet condition computed by formulas from this page: http://www.cfdonline.com/Wiki/Turbu...ary_conditions At the wall U, k, omega have to be zero. But why is nut zero everywhere? Am I right that there is a difference between nut and nutilda? Now I have choosen my boundary conditions as follows: Now they must be right?! omega: Code:
boundaryField { INLET { type fixedValue; value uniform 0.55; } OUTLET { type zeroGradient; } TOP { type symmetryPlane; } BOTTOM { type omegaWallFunction; Cmu 0.09; kappa 0.41; E 9.8; beta1 0.075; value uniform 0.55; } HOTWALL { type omegaWallFunction; Cmu 0.09; kappa 0.41; E 9.8; beta1 0.075; value uniform 0.55; } STEP { type omegaWallFunction; Cmu 0.09; kappa 0.41; E 9.8; beta1 0.075; value uniform 0.55; } EMPTY { type empty; } } Code:
boundaryField { INLET { type calculated; value uniform 0; } OUTLET { type calculated; value uniform 0; } TOP { type symmetryPlane; } BOTTOM { type calculated; value uniform 0; } HOTWALL { type calculated; value uniform 0; } STEP { type calculated; value uniform 0; } EMPTY { type empty; } } Code:
boundaryField { INLET { type fixedValue; value uniform 0.000766; } OUTLET { type fixedValue; value uniform 0; } TOP { type symmetryPlane; } BOTTOM { type fixedValue; value uniform 0; } HOTWALL { type fixedValue; value uniform 0; } STEP { type fixedValue; value uniform 0; } EMPTY { type empty; } } Code:
boundaryField { INLET { type fixedValue; value uniform (11.3 0 0); } OUTLET { type zeroGradient; } TOP { type symmetryPlane; } BOTTOM { type fixedValue; value uniform (0 0 0); } HOTWALL { type fixedValue; value uniform (0 0 0); } STEP { type fixedValue; value uniform (0 0 0); } EMPTY { type fixedValue; value uniform (0 0 0); } } Code:
boundaryField { INLET { type zeroGradient; } OUTLET { type fixedValue; value uniform 0; } TOP { type symmetryPlane; } BOTTOM { type zeroGradient; } HOTWALL { type zeroGradient; } STEP { type zeroGradient; } EMPTY { type empty; } } 

September 19, 2011, 14:38 

#8 
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Felix L.
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At the OUTLET, k should be set to zeroGradient. The rest looks good, though!
Greetings, Felix 

September 20, 2011, 04:12 

#9 
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Hey Felix,
thanks for revising once again my boundary conditions! I will test them and tell results. Camoesas 

September 20, 2011, 09:35 

#10 
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I still get nonsense solutions
But I have tried my mesh with the setup of the pitzDaily tutorial and it works fine. So I can be sure the mesh´s ok. Now trying to change the turbulence modell from keps to SST ... 

September 20, 2011, 11:12 

#11 
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HI Everybody,
is it right to set: nut: calculated 0 everywhere? How about this explanation: The solution is not converging because the problem is transient. Im getting this impression by looking on my solution values (pictures) Can I tell from examining the residuals? next post Camoesas 

September 20, 2011, 11:14 

#12 
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here the residuals


September 20, 2011, 11:31 

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Hi Camoesas,
I set nut on a fixed value at the Inlet and on zero Gradient at the outlet. And I estimated the value of nut via nu/nut= 10~100. Here are my Boundary conditions: nut Code:
dimensions [0 2 1 0 0 0 0]; internalField uniform 1.511e4; boundaryField { Inlet { type fixedValue; value uniform 1.511e4 ; } Outlet { type zeroGradient; } Wall { type calculated; } empty { type empty; } } Code:
dimensions [0 2 2 0 0 0 0]; internalField uniform 9.526; boundaryField { Inlet { type fixedValue; value uniform 9.526; } Outlet { type zeroGradient; } Wall { type fixedValue; value uniform 0; } empty { type empty; } } Code:
dimensions [0 0 1 0 0 0 0]; internalField uniform 63044.616; boundaryField { Inlet { type fixedValue; value uniform 63044.616; } Outlet { type zeroGradient; } Wall { type fixedValue; value uniform 1e8; } empty { type empty; } } Black Squirrel 

September 20, 2011, 12:55 

#14 
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Hey Blacksquirrel,
I ´ve tested your BC, first I copied the types and then i copied them 1:1 But no converged solution. Why are youre omega values so high? I have computed my values with formulas from this page: http://www.cfdonline.com/Wiki/Turbu...ary_conditions But mine are five orders of magnitude smaller. Whats your value for turbulence length scale? Why are you setting omega 1e8 at the wall? I thought nut is supposed to be greater than nu?! Do you have a reference for your estimation? Thanks Camoesas 

September 20, 2011, 14:49 

#15 
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Felix L.
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Hello, guys,
black squirrel: Setting omega to 1e8 at the wall is clearly wrong. Omega approaches infinity when y+ > 0, so it has to be some finite, but pretty high value. See e.g. the book by WILCOX for more detailled information. camoesas: Please tell us something about the inlet turbulence characteristics of your case. I assume the inflow has a low turbulence intensity? From your U and k BCs I can estimate a TI of 0.2%, which is pretty low. This results in a quite low value for omega using the equations you referenced to. My experience is that the SST model has difficulties with low values for omega and e.g. the paper "Effective Inflow Conditions for Turbulence Models in Aerodynamic Calculations" of SPALART et.al. seems to confirm this. Usually my reasoning is: very low inflow turbulence intensity requires a high dissipation (omega), because then the turbulent viscosity is of the order of the molecular viscosity. Low k and Low omega might lead to very, very high turbulent viscosity values which clearly shouldn't be true for a lowturbulence inflow. Setting nut to calculated everywhere is fine, since nut = f(k,omega). k and omega are known everywhere after solving the transport equations, thus nut can easily be calculated. EDIT: I just had a look at your contour plots. Are you sure your domain is extended sufficiently in the streamwise direction? I'd double or even quadruple the distance, just to be sure. Shouldn't be too costly to do that. Greetings, Felix. 

September 21, 2011, 06:00 

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HI Felix,
Yea youre right! Turbulent intensity at the Inlet is very low: 0.2% In my opinion really low, but the paper tells so, but remains silent about turbulent length scale. So I had to guess: 1.38mm (calculated from the pitzdaily tutorial) Now I doubled the outlet. According to the motorbike tutorial (which is the only known tutorial for simpleFoam with SST) I changed in fvSolution to linear solvers: p: PCG > GAMG U,k,omega: PBiCG > smooth Solver And now i get this fine converged solution! Does this mean the other settings are wrong? Whats linear solver? Do I have loss in accuracy like first order? 

September 21, 2011, 06:04 

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and here the velocity for the fully resolved wall boundary layer


September 21, 2011, 06:23 

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HI,
I´ve also made a simulation with wallFunctions. And this simulation is just converging fine. I am using the following boundary conditions: k: inlet: value 7.66e4 outlet: zeroGradient walls: kqRWallFunction omega: inlet: value 0.55; outlet: zeroGradient; walls: omegaWallFunction nut: inlet: calculated 0; outlet: calculated 0; walls: nutkWallFunction; The fvSchemes and fvSolution are still the same: Code:
ddtSchemes { default steadyState; } gradSchemes { default Gauss linear; } divSchemes { default none; div(phi,U) Gauss linearUpwind grad(U); div(phi,k) Gauss upwind; div(phi,omega) Gauss upwind; div((nuEff*dev(T(grad(U))))) Gauss linear; } laplacianSchemes { default Gauss linear corrected; } interpolationSchemes { default linear; interpolate(U) linear; } snGradSchemes { default corrected; } fluxRequired { default no; p; } Code:
solvers { p { solver PCG; preconditioner DIC; tolerance 1e06; relTol 0.01; } U { solver PBiCG; preconditioner DILU; tolerance 1e05; relTol 0.1; } k { solver PBiCG; preconditioner DILU; tolerance 1e05; relTol 0.1; } omega { solver PBiCG; preconditioner DILU; tolerance 1e20; relTol 0.1; } } SIMPLE { nNonOrthogonalCorrectors 0; /* residualControl { p 1e4; U 1e5; "(kepsilonomega)" 1e5; }*/ } relaxationFactors { p 0.3; U 0.7; k 0.7; omega 0.7; } As I am using the same fvSchemes and fvSolution settings for the lowRe and for the highRe simulation, I conclude that for the lowRe I still have errors in the boundary conditions!? Because one is converging and one not. Edit: Yplus Values: Patch 3 named HOTWALL y+ : min: 6.18212 max: 56.0136 average: 39.387 Patch 5 named BOTTOM y+ : min: 1.70152 max: 30.41 average: 12.862 Patch 6 named STEP y+ : min: 6.34481 max: 24.2188 average: 16.7388 Here are my y+ Values they are still to small, aren't they? But I am hesitating to coarse the grid any more in my opinion its already to coarse 

September 21, 2011, 06:38 

#19 
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Felix,
youre experience is also right here. I have increased omega by 5 and 7 orders of magnitude and convergence is getting better but its still not satisfying. See pictures. But I am hesitating to fake the boundary conditions. 

September 21, 2011, 13:50 

#20 
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Felix L.
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Good evening, camoesas,
I don't understand your post #16. Did you extend the grid in flow direction AND change the linear solvers? The linear solvers are only responsible for solving the discretized system of equations (see CFD text books for that!). They shouldn't affect the convergence behaviour of the solution. But extending the domain seems to be the right way to me. It should be possible to use PBiCG/PCG for the linear system solving, this doesn't affect the order of accuracy of your solution (despite of the convergence error, of course, but this is easily eliminated), though, so you can also keep GAMG and smoothSolver. Wall functions shall only be used when (at least!) the average y+ is > 30. But your results in #16 seem to be quite reasonable so why use wall functions anyway? My recommendation: use the inlet values for k and omega you initially specified and keep on extending the domain until there's no reasonable effect on the solution anymore. Oh, and if you don't want your solution to degrade to 1st order, don't forget to use something more accurate than upwind for the divergence interpolation of k and omega! Greetings, Felix 

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