CFD Online Discussion Forums - pimpleFOAM setup for airfoil stall analysis

Hi all!

I am trying to simulate the flow over a NACA0012 airfoil at stall and post stall, in 2D, using the k-omegaSST model. I understand that the flow separation is inherently a 3D phenomenon but I would still like to know if this approach can work for achieving initial estimates of the cl and cd at high angles of attack. I have only used simpleFoam earlier so I am very new to pimpleFoam.

I used the fvSchemes and fvSolution that I found in a previous thread on a similar topic, but that didn't seem to work for me. I tried the fvSchemes and fvSolution from the wingMotion tutorial too, but the calculations stop after a single iteration.

My yPlus is 1, and I'm using an O-grid generated from Pointwise.

If someone could help me find out what it is that I can do to run this simulation successfully, I would be really grateful. Thanks in advance!

Here's my setup:

fvSolution

Code:

FoamFile

{

    version     2.0;

    format      ascii;

    class       dictionary;

    object      fvSolution;

}

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



solvers

{

    "pcorr.*"

    {

        solver           GAMG;

        tolerance        0.02;

        relTol           0;

        smoother         GaussSeidel;

    }



    p

    {

        $pcorr;

        tolerance        1e-7;

        relTol           0.01;

    }



    pFinal

    {

        $p;

        tolerance        1e-7;

        relTol           0;

    }



    "(U|k|omega)"

    {

        solver          smoothSolver;

        smoother        symGaussSeidel;

        tolerance       1e-06;

        relTol          0.1;

    }



    "(U|k|omega)Final"

    {

        $U;

        tolerance       1e-06;

        relTol          0;

    }



    cellDisplacement

    {

        solver          GAMG;

        tolerance       1e-5;

        relTol          0;

        smoother        GaussSeidel;

    }

}



PIMPLE

{

    correctPhi          yes;

    nOuterCorrectors    2;

    nCorrectors         1;

    nNonOrthogonalCorrectors 0;

}



relaxationFactors

{

    fields

    {

        p               0.3;

    }

    equations

    {

        "(U|k|omega)"   0.7;

        "(U|k|omega)Final" 1.0;

    }

}



cache

{

    grad(U);

}

fvSchemes

Code:

FoamFile

{

    version     2.0;

    format      ascii;

    class       dictionary;

    object      fvSchemes;

}

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



ddtSchemes

{

    default Euler;

}



gradSchemes

{

    default         Gauss linear;

    grad(p)         Gauss linear;

    grad(U)         Gauss linear;

}



divSchemes

{

    default         none;

    div(phi,U)      Gauss linearUpwind grad(U);

    div(phi,k)      Gauss limitedLinear 1;

    div(phi,omega)  Gauss limitedLinear 1;

    div((nuEff*dev2(T(grad(U))))) Gauss linear;

}



laplacianSchemes

{

    default         Gauss linear limited corrected 0.5;

}



interpolationSchemes

{

    default         linear;

}



snGradSchemes

{

    default         corrected;

}



wallDist

{

    method meshWave;

}

controlDict

Code:

FoamFile

{

    version     2.0;

    format      ascii;

    class       dictionary;

    location    "system";

    object      controlDict;

}

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



application     pimpleFoam;



startFrom       startTime;



startTime       0;



stopAt          endTime;



endTime         5;



deltaT          1e-5;



writeControl    adjustableRunTime;



writeInterval   1e-2;



purgeWrite      0;



writeFormat     binary;



writePrecision  10;



writeCompression off;



timeFormat      general;



timePrecision   6;



runTimeModifiable true;



adjustTimeStep  yes;



maxCo           0.9;



functions

{

    #includeFunc residuals

    #includeFunc forceCoeffsIncompressible

    #includeFunc forcesIncompressible

}

Code:

FoamFile

{

    version     2.0;

    format      ascii;

    class       volScalarField;

    location    "0";

    object      k;

}

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



dimensions      [0 2 -2 0 0 0 0];



internalField   uniform 1e-6;



boundaryField

{

    BaseAndTop

    {

        type            empty;

    }

    

    inlet-outlet

    {

        type            freestream;

        freestreamValue uniform 1e-6;

    }



    airfoil

    {

        type            fixedValue;

        value           uniform 1e-10;

    }

}

omega

Code:

FoamFile

{

    version     2.0;

    format      ascii;

    class       volScalarField;

    location    "0";

    object      omega;

}

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



dimensions      [0 0 -1 0 0 0 0];



internalField   uniform 1e3;



boundaryField

{

    BaseAndTop

    {

        type            empty;

    }

    

    inlet-outlet

     {

        type            freestream;

        freestreamValue uniform 1;

     }



    airfoil

    {

        type            omegaWallFunction;

        value           $internalField;

    }

}

I cannot figure out what I'm doing wrong, and really, really need help with this.
Thanks in advance!