[dnsuman]

I am new to OpenFoam. I am trying to simulate flow over an aircraft fuselage at Re=36000000. I have created my mesh in ansys meshing using cutcell method with inflation layers and y+ ~ 30 and imported it in Openfoam. I am using k omega SST model and I have specified all boundary conditions to the best of my knowledge. I am using simpleFoam as the solver. The solution does not converge and I am getting completely wrong results. I am pasting my case files below. Can someone please take a look and tell me where the problem is? Any help would be greatly appreciated.



K

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

internalField   uniform 18.37479;

boundaryField
{
    inlet
    {
      type            fixedValue;
      value          uniform 18.37479;
    }

    outlet
    {
      type            zeroGradient;
    }
    wall
    {
        type            zeroGradient;
    }
    fuselage
    {
        type            kqRWallFunction;
    value        uniform 18.37479;
    }
    symmetry
    {
        type            symmetry;
    }
}

nut

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

internalField   uniform 1.6496e-5;

boundaryField
{
    inlet
    {
        type            freestream;
        freestreamValue uniform 1.6496e-5;
    }

    outlet
    {
        type            freestream;
        freestreamValue uniform 1.6496e-5;
    }

    wall
    {
        type            nutkWallFunction;
        value           uniform 1.6496e-5;
    }

    fuselage
    {
        type            nutkWallFunction;
        value           uniform 1.6496e-5;
    }

    symmetry
    {
        type            symmetry;
    }
}

omega

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

internalField   uniform 5.4941;

boundaryField
{
    inlet
    {
      type            fixedValue;
      value          uniform 5.4941;
    }

    outlet
    {
      type            zeroGradient;
    }  
  
    wall
    {
        type            zeroGradient;
    }

    fuselage
    {
        type            omegaWallFunction;
    value        uniform 5.4941;
    }

    symmetry
    {
        type            symmetry;
    }
}

p

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

internalField   uniform 0;

boundaryField
{
    inlet
    {
        type            zeroGradient;
    }
    outlet
    {
        type            freestreamPressure;
        freestreamValue $internalField;
    }

    wall
    {
        type            zeroGradient;
    }

    fuselage
    {
        type            zeroGradient;
    }

    symmetry
    {
        type            symmetry;
    }
}

U

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

internalField   uniform (70 0 0);

boundaryField
{
    inlet
    {
        type            freestreamVelocity;
        freestreamValue $internalField;
    }

    outlet
    {
        type            zeroGradient;
    }

    wall
    {
        type            slip;
    }

    fuselage
    {
        type            noSlip;
    }

    symmetry
    {
        type            symmetry;
    }
}

fvSolution

solvers
{
    p
    {
        solver             GAMG;
        tolerance         1e-10;
        relTol             0.01;
        smoother         GaussSeidel;
        nPreSweeps         0;
        nPostSweeps     2;
        cacheAgglomeration on;
        agglomerator faceAreaPair;
        nCellsInCoarsestLevel 120;
        mergeLevels     1;
        maxIter            500;
    }

    U
    {
        solver          smoothSolver;
        smoother        GaussSeidel;
        tolerance       1e-8;
        relTol          0.1;
        nSweeps         1;
    }

    k
    {
        solver          smoothSolver;
        smoother        GaussSeidel;
        tolerance       1e-8;
        relTol          0.1;
        nSweeps         1;
    }

    omega
    {
        solver          smoothSolver;
        smoother        GaussSeidel;
        tolerance       1e-8;
        relTol          0.1;
        nSweeps         1;
    }

}

SIMPLE
{       
    nNonOrthogonalCorrectors 3;
    nCorrectors 1; 
}

potentialFlow
{
    nNonOrthogonalCorrectors 10;
}

relaxationFactors
{
    fields
    {
        p               0.2;
    }    
    equations
    {
        U               0.5;
        k               0.5;
        omega           0.5;
    }
}

cache
{
    grad(U);
}

fvSchemes

ddtSchemes
{
    default         steadyState;
}

gradSchemes
{
    default         cellMDLimited Gauss linear 0.5;
    grad(U)         Gauss linear;
}

divSchemes
{
    default         none;

    div(phi,U)      bounded Gauss linearUpwind grad(U);
    div(phi,k)      bounded Gauss upwind;
    div(phi,omega)  bounded Gauss upwind;
    div((nuEff*dev2(T(grad(U))))) Gauss linear;

}


laplacianSchemes
{
    default         Gauss linear uncorrected;
}

interpolationSchemes
{
    default         linear;
}

snGradSchemes
{
    default         corrected;
}

fluxRequired
{
    default no;
    p;
}

wallDist
{
    method meshWave;
} 


// ************************************************************************* //

ControlDict

application     simpleFoam;

startFrom       startTime;

startTime       0;

stopAt          endTime;

endTime         1000;

deltaT          1;

writeControl    timeStep;

writeInterval   50;

purgeWrite      0;

writeFormat     ascii;

writePrecision  6;

writeCompression off;

timeFormat      general;

timePrecision   6;

runTimeModifiable true;

functions
{
    forces
    {
        type            forceCoeffs;
        libs            ("libforces.so");
        writeControl    writeTime;

        patches
        (
            fuselage
        );

    rho        rhoInf;
        rhoInf      1.0556;

        CofR        (0.4127 0 0);
        liftDir     (0 0 1);
        dragDir     (1 0 0);
        pitchAxis   (0 1 0);
        magUInf     70;
        lRef        8.669;
        Aref        5.01095;
    }
}

Please let me know where the problem is.