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January 31, 2014, 16:34 |
rhoSimplecFoam Diverges for External Flow
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New Member
Sohail
Join Date: Jul 2013
Posts: 10
Rep Power: 13 |
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 |
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boundary conditions, cfd. openfoam, external flow, rhosimplecfoam, wing |
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