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rhoSimplecFoam Diverges for External Flow

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Old   January 31, 2014, 15:34
Default rhoSimplecFoam Diverges for External Flow
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Sohail
Join Date: Jul 2013
Posts: 10
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Hello guys,
I am trying to make a turbulent flow simulation over a wing using rhoSimplecFoam ver. OpenFOAM-2.0. I ran my case after 19 iteration I get an error message. After spending lots of time and many attempts I decided to open a tread in forum. Could someone help me where is the mistake in my boundary conditions or schemes..
I want to use kepsilon for turbulence modeling.

Here are by BC's

FoamFile
{
version 2.0;
format binary;
class volScalarField;
location "0";
object p;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [1 -1 -2 0 0 0 0];

internalField uniform 79500;

boundaryField
{
outlet
{
type fixedValue;
value $internalField;
}

wing_winglet
{
type zeroGradient;
}

inlet
{
type zeroGradient;
refValue uniform 79500;
refGradient uniform 0;
valueFraction uniform 0.3;
}

farfield
{
type zeroGradient;// fixedValue;
// value $internalField;
}


root
{
type symmetryPlane;
}
}

object U;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [0 1 -1 0 0 0 0];

internalField uniform (0 0 0);

boundaryField
{
inlet
{
type fixedValue;
value uniform (103 0 0);
}

outlet
{
type inletOutlet;
inletValue uniform (103 0 0);
value $internalField;
}

farfield
{
type zeroGradient;//inletOutlet;
//inletValue uniform (0 0 0);
//value $internalField;
}


root
{
type symmetryPlane;
}

wing_winglet
{
type fixedValue;
value uniform (0 0 0);
}

}


object T;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [0 0 0 1 0 0 0];

internalField uniform 278.8;

boundaryField
{
outlet
{
type zeroGradient;// inletOutlet;
// inletValue $internalField;
// value $internalField;
}

wing_winglet
{
type zeroGradient;
}

inlet
{
type fixedValue;
value $internalField;
}

farfield
{
type zeroGradient;// inletOutlet;
//inletValue $internalField;
//value $internalField;
}

root
{
type symmetryPlane;
}
}


object k;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [0 2 -2 0 0 0 0];

internalField uniform 1.5913;

boundaryField
{
outlet
{
type inletOutlet;
inletValue $internalField;
value $internalField;
}
inlet
{
type turbulentIntensityKineticEnergyInlet;
intensity 0.1;
value $internalField;
}
farfield
{
type zeroGradient;// inletOutlet;
// inletValue $internalField;
// value $internalField;
}

root
{
type symmetryPlane;
}
wing_winglet
{
type compressible::kqRWallFunction;
value $internalField;
}
}


object epsilon;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [0 2 -3 0 0 0 0];

internalField uniform 2.35;

boundaryField
{
outlet
{
type inletOutlet;
inletValue $internalField;;
value $internalField;
}
inlet
{
type compressible::turbulentMixingLengthDissipationRate Inlet;
mixingLength 0.14;
value $internalField;
}
farfield
{
type zeroGradient;//inletOutlet;
// inletValue $internalField;;
// value $internalField;
}

root
{
type symmetryPlane;
}

wing_winglet
{
type compressible::epsilonWallFunction;
Cmu 0.09;
kappa 0.41;
E 9.8;
value $internalField;;
}
}


object alphat;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [1 -1 -1 0 0 0 0];

internalField uniform 2e-5;

boundaryField
{
outlet
{
type calculated;
value $internalField;
}
wing_winglet
{
type alphatWallFunction;
Prt 0.89;
value $internalField;
}
inlet
{
type calculated;
value $internalField;
}
farfield
{
type zeroGradient;//calculated;
//value $internalField;
}

root
{
type symmetryPlane;
}
}


object mut;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [1 -1 -1 0 0 0 0];

internalField uniform 1.4876e-5;

boundaryField
{
outlet
{
type calculated;
value $internalField;
}
wing_winglet
{
type mutkWallFunction;
Cmu 0.09;
kappa 0.41;
E 9.8;
value $internalField;
}
inlet
{
type calculated;
value $internalField;
}
farfield
{
type zeroGradient;//calculated;
//value $internalField;
}

root
{
type symmetryPlane;
}
}


Here are my schemes and solutions dicts


ddtSchemes
{
default steadyState;
}

gradSchemes
{
default Gauss linear;
}

divSchemes
{
default none;

div(phi,U) bounded Gauss upwind;
div((muEff*dev2(T(grad(U))))) Gauss linear;
div(phi,e) bounded Gauss upwind;
div(phi,epsilon) bounded Gauss upwind;
div(phi,k) bounded Gauss upwind;

div(phid,p) bounded Gauss upwind;
div(phi,Ekp) bounded Gauss upwind;
div((phi|interpolate(rho)),p) Gauss upwind;
}

laplacianSchemes
{
default Gauss linear corrected;
}

interpolationSchemes
{
default linear;
}

snGradSchemes
{
default corrected;
}

fluxRequired
{
default no;
p;
pCorr;
}


object fvSolution;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

solvers
{
p
{
solver GAMG;
tolerance 1e-08;
relTol 0.1;
smoother GaussSeidel;
nPreSweeps 0;
nPostSweeps 2;
nFinestSweeps 2;
cacheAgglomeration true;
nCellsInCoarsestLevel 20;
agglomerator faceAreaPair;
mergeLevels 1;
}

"(U|e|k|epsilon)"
{
solver GAMG;
tolerance 1e-08;
relTol 0.1;
smoother GaussSeidel;
nPreSweeps 0;
nPostSweeps 2;
nFinestSweeps 2;
cacheAgglomeration true;
nCellsInCoarsestLevel 20;
agglomerator faceAreaPair;
mergeLevels 1;
}
}

SIMPLE
{
nNonOrthogonalCorrectors 0;
rhoMin rhoMin [1 -3 0 0 0] 0.1;
rhoMax rhoMax [1 -3 0 0 0] 1.0;
transonic yes;

residualControl
{
p 1e-3;
U 1e-4;
e 1e-3;

// possibly check turbulence fields
"(k|epsilon|omega)" 1e-3;
}
}

relaxationFactors
{
fields
{
p 1;
rho 1;
}
equations
{
p 1;
U 0.9;
e 0.9;
k 0.9;
epsilon 0.9;
}
}



Any help will be appreciated.
Thanks
Attached Files
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Tags
boundary conditions, cfd. openfoam, external flow, rhosimplecfoam, wing

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