[Garfield]

Hi all, i am trying to solve a problem with rhoSimpleFoam, but it returns the following error, I try to simulate a flow inside a two layer channel, I imported the mesh from fluent.mesh files :

Create time

Create mesh for time = 0


SIMPLE: convergence criteria
field p tolerance 0.01
field U tolerance 0.0001
field e tolerance 0.001
field "(k|epsilon|omega)" tolerance 0.001

Reading thermophysical properties

Selecting thermodynamics package
{
type hePsiThermo;
mixture pureMixture;
transport sutherland;
thermo hConst;
equationOfState perfectGas;
specie specie;
energy sensibleInternalEnergy;
}

Reading field U

Reading/calculating face flux field phi

Creating turbulence model

Selecting RAS turbulence model kEpsilon
kEpsilonCoeffs
{
Cmu 0.09;
C1 1.44;
C2 1.92;
C3 -0.33;
sigmak 1;
sigmaEps 1.3;
Prt 1;
}

No finite volume options present


Starting time loop

Time = 0.0005

smoothSolver: Solving for Ux, Initial residual = 1, Final residual = 0.0495126, No Iterations 2
smoothSolver: Solving for Uy, Initial residual = 1, Final residual = 0.094261, No Iterations 2
smoothSolver: Solving for Uz, Initial residual = 1, Final residual = 0.0408954, No Iterations 2
smoothSolver: Solving for e, Initial residual = 0.999995, Final residual = 0.0329298, No Iterations 2
GAMG: Solving for p, Initial residual = 1, Final residual = 0.0499349, No Iterations 15
time step continuity errors : sum local = 1.42277e-05, global = -1.44013e-06, cumulative = -1.44013e-06
rho max/min : 1.27951 1.25857
smoothSolver: Solving for epsilon, Initial residual = 0.22093, Final residual = 0.00844164, No Iterations 2
smoothSolver: Solving for k, Initial residual = 1, Final residual = 0.096524, No Iterations 2
ExecutionTime = 11.3 s ClockTime = 11 s

Time = 0.001

smoothSolver: Solving for Ux, Initial residual = 0.200468, Final residual = 0.00571057, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.272446, Final residual = 0.00881932, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.266989, Final residual = 0.0178839, No Iterations 4
smoothSolver: Solving for e, Initial residual = 0.512064, Final residual = 0.0490672, No Iterations 1
GAMG: Solving for p, Initial residual = 0.0572567, Final residual = 0.00273825, No Iterations 44
time step continuity errors : sum local = 0.000137462, global = -6.45329e-07, cumulative = -2.08546e-06
rho max/min : 1.29054 1.24481
smoothSolver: Solving for epsilon, Initial residual = 0.964019, Final residual = 0.0622479, No Iterations 2
smoothSolver: Solving for k, Initial residual = 0.653927, Final residual = 0.0158093, No Iterations 4
ExecutionTime = 21.13 s ClockTime = 21 s

Time = 0.0015

smoothSolver: Solving for Ux, Initial residual = 0.153799, Final residual = 0.00599166, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.1602, Final residual = 0.0075074, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.115999, Final residual = 0.0073149, No Iterations 4
smoothSolver: Solving for e, Initial residual = 0.0281063, Final residual = 0.0023541, No Iterations 1
GAMG: Solving for p, Initial residual = 0.0237124, Final residual = 0.00085322, No Iterations 12
time step continuity errors : sum local = 0.000201021, global = -1.98632e-05, cumulative = -2.19486e-05
rho max/min : 1.30101 1.2308
smoothSolver: Solving for epsilon, Initial residual = 0.923677, Final residual = 0.0609995, No Iterations 2
bounding epsilon, min: -0.65455 max: 459443 average: 1904.96
smoothSolver: Solving for k, Initial residual = 0.497815, Final residual = 0.0125684, No Iterations 4
ExecutionTime = 26.62 s ClockTime = 26 s

Time = 0.002

smoothSolver: Solving for Ux, Initial residual = 0.250991, Final residual = 0.006755, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.277747, Final residual = 0.00742504, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.173037, Final residual = 0.00478922, No Iterations 4
smoothSolver: Solving for e, Initial residual = 0.133343, Final residual = 0.01046, No Iterations 1
GAMG: Solving for p, Initial residual = 0.002813, Final residual = 0.000137325, No Iterations 12
time step continuity errors : sum local = 0.000168067, global = -6.01628e-05, cumulative = -8.21114e-05
rho max/min : 1.31096 1.21821
smoothSolver: Solving for epsilon, Initial residual = 0.201193, Final residual = 0.0021078, No Iterations 2
bounding epsilon, min: -1.88318 max: 3.87696e+06 average: 18333.5
smoothSolver: Solving for k, Initial residual = 0.366344, Final residual = 0.00802616, No Iterations 4
ExecutionTime = 32.17 s ClockTime = 32 s

Time = 0.0025

smoothSolver: Solving for Ux, Initial residual = 0.998187, Final residual = 0.0468286, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.999869, Final residual = 0.0458314, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.99515, Final residual = 0.0472566, No Iterations 4
smoothSolver: Solving for e, Initial residual = 1, Final residual = 0.0616162, No Iterations 1
#0 Foam::error:rintStack(Foam::Ostream&) at ??:?
#1 Foam::sigFpe::sigHandler(int) at ??:?
#2 ? in "/lib/x86_64-linux-gnu/libc.so.6"
#3 Foam::hePsiThermo<Foam:siThermo, Foam:ureMixture<Foam::sutherlandTransport<Foam:: species::thermo<Foam::hConstThermo<Foam:erfectGa s<Foam::specie> >, Foam::sensibleInternalEnergy> > > >::calculate() at ??:?
#4 Foam::hePsiThermo<Foam:siThermo, Foam:ureMixture<Foam::sutherlandTransport<Foam:: species::thermo<Foam::hConstThermo<Foam:erfectGa s<Foam::specie> >, Foam::sensibleInternalEnergy> > > >::correct() at ??:?
#5 ? at ??:?
#6 __libc_start_main in "/lib/x86_64-linux-gnu/libc.so.6"
#7 ? at ??:?
Floating point exception (core dumped)

Could any one tell me where is the problem?

[Garfield]

/*--------------------------------*- C++ -*----------------------------------*\
| ========= | |
| \\ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \\ / O peration | Version: 2.4.0 |
| \\ / A nd | Web: www.OpenFOAM.org |
| \\/ M anipulation | |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class dictionary;
location "system";
object fvSchemes;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

ddtSchemes
{
default steadyState;
}

gradSchemes
{
default Gauss linear;
}

divSchemes
{
default none;

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

div(phid,p) Gauss linear;
div(phi,Ekp) bounded Gauss linearUpwind grad(Ekp);
div((phi|interpolate(rho)),p) Gauss linear;
}

laplacianSchemes
{
default Gauss linear corrected;
}

interpolationSchemes
{
default linear;
}

snGradSchemes
{
default corrected;
}

fluxRequired
{
default no;
p;
pCorr;
}

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

[Saideep]

hi,

are you using the standard solver as it is or have you modified your solver? The floating point exception error is related to a calculation where the compiler is trying to divide some variable with 0.

But i guess it shouldn't be related to your mesh exporting.

Saideep

[Garfield]

Here are the other files

/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2.4.0                                 |
|   \\  /    A nd           | Web:      www.OpenFOAM.org                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      ascii;
    class       dictionary;
    location    "system";
    object      fvSolution;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

solvers
{
    p
    {
        solver          GAMG;
        tolerance       1e-08;
        relTol          0.05;
        smoother        GaussSeidel;
        cacheAgglomeration on;
        nCellsInCoarsestLevel 20;
        agglomerator    faceAreaPair;
        mergeLevels     1;
    }

    U
    {
        solver          smoothSolver;
        smoother        GaussSeidel;
        nSweeps         2;
        tolerance       1e-06;
        relTol          0.1;
    }

    e
    {
        solver          smoothSolver;
        smoother        symGaussSeidel;
        tolerance       1e-06;
        relTol          0.1;
    }

    "(k|epsilon)"
    {
        $U;
        tolerance       1e-07;
        relTol          0.1;
    }
}

SIMPLE
{
    nNonOrthogonalCorrectors 0;
    rhoMin          rhoMin [ 1 -3 0 0 0 ] 0.5;
    rhoMax          rhoMax [ 1 -3 0 0 0 ] 1.5;

    residualControl
    {
        p               1e-2;
        U               1e-4;
        e               1e-3;

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

relaxationFactors
{
    fields
    {
        p               0.3;
        rho             0.05;
    }
    equations
    {
        U               0.7;
        "(k|epsilon)"   0.7;
        e               0.5;
        p               0.6;
        k               0.6;
        epsilon         0.6;
    }
}


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

/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2.4.0                                 |
|   \\  /    A nd           | Web:      www.OpenFOAM.org                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      ascii;
    class       volVectorField;
    object      U;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

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

internalField   uniform (0 0 0);

boundaryField
{
    HEATED_WALL
    {
        type            fixedValue;
        value           uniform (0 0 0);
    }
    UNHEATED_WALL
    {
        type            fixedValue;
        value           uniform (0 0 0);
    }
    RIB
    {
        type            fixedValue;
        value           uniform (0 0 0);
    }

    INLET
    {
          //type            fixedValue;
          //value           uniform (0 0 12.65);
          type            flowRateInletVelocity;
          massFlowRate    constant 10;
          rhoInlet        1.225;    // Guess for rho
    }
    OUTLET
    {
        type            inletOutlet;
        value           uniform (0 0 0);
        inletValue      uniform (0 0 -1.21);
    }
}


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

/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2.4.0                                 |
|   \\  /    A nd           | Web:      www.OpenFOAM.org                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      ascii;
    class       volScalarField;
    object      p;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

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

internalField   uniform 110000;

boundaryField
{
    UNHEATED_WALL
    {
        type            zeroGradient;
    }
    HEATED_WALL
    {
        type            zeroGradient;
    }
    RIB
    {
        type            zeroGradient;
    }

    OUTLET
  {
        type            fixedValue;
        value           uniform 110000;
    }
    INLET
    {
        type            zeroGradient;
       // refValue        uniform 190000;
       // refGradient     uniform 0;
       // valueFraction   uniform 0.3;
        //type            mixed;
        //refValue        uniform 110000;
        //refGradient     uniform 0;
        //valueFraction   uniform 1;
        //type            transonicOutletPressure;
        //U               U;
        //phi             phi;
        //gamma           1.4;
        //psi             psi;
        //pInf            uniform 110000;
    }
}


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

[Garfield]

Originally Posted by Saideep

hi,

are you using the standard solver as it is or have you modified your solver? The floating point exception error is related to a calculation where the compiler is trying to divide some variable with 0.

But i guess it shouldn't be related to your mesh exporting.

Saideep

Hi, Saideep, Thank you.
Yes, I use the standard solver with the modification in the fvSchemes, I changed the original Gauss upwind to the Gauss linearUpwind grad().
Do you know usually what will cause the problem of " dividing 0 "?
Thanks again