[uni]

Hello, i'm new openfoam and try solve flow for naca12 with pimpleFoam in piso mode. airfoil in midle channel i use foamextend4. pimpleFoam always crash on second time step even if time step very smal. i dont know what problem is. anyone help? this is output

 pimpleFoam                 
/*---------------------------------------------------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | foam-extend: Open Source CFD                    |
|  \\    /   O peration     | Version:     4.0                                |
|   \\  /    A nd           | Web:         http://www.foam-extend.org         |
|    \\/     M anipulation  | For copyright notice see file Copyright         |
\*---------------------------------------------------------------------------*/
Build    : 4.0-10298020aac7
Exec     : pimpleFoam
Date     : Mar 16 2018
Time     : 19:57:17
Host     : carrera
PID      : 20863
CtrlDict : "/home/uniciti/foam/uniciti-4.0/test/testCase-NACA0012/system/controlDict"
Case     : /home/uniciti/foam/uniciti-4.0/test/testCase-NACA0012
nProcs   : 1
SigFpe   : Enabling floating point exception trapping (FOAM_SIGFPE).

// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //
Create time

Create mesh for time = 0


    From function void polyMesh::initMesh()
    in file meshes/polyMesh/polyMeshInitMesh.C at line 81
    Truncating neighbour list at 87789 for backward compatibility

PIMPLE: Operating solver in PISO mode

Reading field p

Reading field U

Reading/calculating face flux field phi

Selecting incompressible transport model Newtonian
Selecting turbulence model type RASModel
Selecting RAS turbulence model laminar
Reading field aU if present


Starting time loop

Courant Number mean: 0.0274887 max: 0.507163 velocity magnitude: 0.5
Creating minMaxField for field U
Creating minMaxField for field p
Time = 0.001

PIMPLE: iteration 1
BiCGStab:  Solving for Ux, Initial residual = 0.999999, Final residual = 1.66924e-10, No Iterations 2
BiCGStab:  Solving for Uy, Initial residual = 1, Final residual = 1.40851e-10, No Iterations 2
GAMG:  Solving for p, Initial residual = 1, Final residual = 7.57375e-07, No Iterations 31
time step continuity errors : sum local = 2.22698e-12, global = -8.61863e-21, cumulative = -8.61863e-21
ExecutionTime = 0.59 s  ClockTime = 0 s

Courant Number mean: 0.0281978 max: 0.791337 velocity magnitude: 1.0436
Field U magnitude min = 0 max = 0.742286
Field p min = -2.04446 max = 3.70447
Time = 0.002

PIMPLE: iteration 1
BiCGStab:  Solving for Ux, Initial residual = 0.028756, Final residual = 4.02589e-07, No Iterations 1
BiCGStab:  Solving for Uy, Initial residual = 0.0292767, Final residual = 3.73316e-07, No Iterations 1
Floating point exception

pressure boundary condition

/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  1.5-dev                               |
|   \\  /    A nd           | Revision: 1326                                  |
|    \\/     M anipulation  | Web:      http://www.OpenFOAM.org               |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      ascii;
    class       volScalarField;
    location    "0";
    object      p;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

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

internalField   uniform 0;

boundaryField
{
    sides
    {
        type            empty;
    }
    airfoil
    {
        type            zeroGradient;
    }
    top
    {
        type            zeroGradient;
    }
    bottom
    {
        type            zeroGradient;
    }
    inlet
    {
        type            zeroGradient;
    }
    outlet
    {
        type            fixedValue;
        value           uniform 0;
    }
}

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

velcocity boundary condition

/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | foam-extend: Open Source CFD                    |
|  \\    /   O peration     | Version:     4.0                                |
|   \\  /    A nd           | Web:         http://www.foam-extend.org         |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      ascii;
    class       volVectorField;
    location    "0";
    object      U;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

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

internalField   uniform ( 0.5 0 0 );

boundaryField
{
    sides
    {
        type            empty;
    }
    airfoil
    {
        type            fixedValue;
        value           uniform ( 0 0 0 );
    }
    top
    {
        type            fixedValue;
        value           uniform ( 0 0 0 );
    }
    bottom
    {
        type            fixedValue;
        value           uniform ( 0 0 0 );
    }
    inlet
    {
        type            fixedValue;
        value           uniform ( 0.5 0 0 );
    }
    outlet
    {
        type            inletOutlet;
        inletValue      uniform ( 0 0 0 );
        value           uniform ( 0.5 0 0 );
    }
}

[piu58]

Try to start with internal field of U = 0.

[uni]

same problem happen. also crash. i make it work by changing divSchemes for all convective terms to Gauss upwind. but crash again at 1s. i think problem is mesh. work in starccm but not openfoam.