[CFDnewbie147]

Hello together,

I'm trying to simulate a kind of rocket with rhoSimplecFoam and the following start-up conditions(it's laminar without any turbulence modell and a coarse mesh built with snappyhexmesh, the values are for standard atmosphere in 0km):

p
dimensions      [1 -1 -2 0 0 0 0];
internalField   uniform 101325;
boundaryField
{
    flange_CATIA
    {
        type            zeroGradient;
    }
 
    inlet
    {
        type            fixedValue;
  value  uniform 101325;
    }
 
    outlet
    {
        type            zeroGradient;
    }
 
 upperWall
 {
 
  type   zeroGradient;
 }
 
 lowerWall
 {
  type   zeroGradient;
 }
 
 frontAndBack
    {
        type            zeroGradient;
 }
}

T
dimensions      [0 0 0 1 0 0 0];
internalField   uniform 288.16;
boundaryField
{
    flange_CATIA
    {
        type            fixedValue;
        value           uniform 288.16;
    }
    inlet
    {
        type            fixedValue;
        value           uniform 288.16;
    }
    outlet
    {
        type            zeroGradient;
    }
 
 upperWall
 {
  type   zeroGradient;
 }
 
 lowerWall
 {
  type   zeroGradient;
 }
 
 frontAndBack
    {
        type            zeroGradient;
 }
}

U
dimensions      [0 1 -1 0 0 0 0];
internalField   uniform (272.215 0 0);
boundaryField
{
    flange_CATIA
    {
        type            fixedValue;
  value  uniform (0 0 0);
    }
 
    inlet
    {
        type            fixedValue;
  value  uniform (272.215 0 0);
    }
 
    outlet
    {
        type            zeroGradient;
    }
 
 upperWall
 {
  type  freestream;
 freestreamValue uniform (272.215 0 0);
 phi  phi;
 }
 
 lowerWall
 {
  type  freestream;
 freestreamValue uniform (272.215 0 0);
 phi  phi;
 }
 
 frontAndBack
    {
        type  freestream;
 freestreamValue uniform (272.215 0 0);
 phi  phi;
 }
}

for fvSolution I have:

solvers
{
    p
    {
        solver          GAMG;
        tolerance       1e-06;
        relTol          0.1;
        smoother        GaussSeidel;
        nPreSweeps      2;
        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 3;
    rhoMin          rhoMin [1 -3 0 0 0] 0.1;
    rhoMax          rhoMax [1 -3 0 0 0] 1.7;
    transonic       yes;
    residualControl
    {
        p               1e-3;
        U               1e-4;
        e               1e-3;
        // possibly check turbulence fields
        "(k|epsilon|omega)" 1e-3;
    }
}
 
relaxationFactors
{
    fields
    {
        p               0.1;
        rho             0.2;
    }
    equations
    {
        p               0.1;
        U               0.1;
        e               0.1;
        k               0.1;
        epsilon         0.1;
    }
}

and for fvSchemes:

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;
}

Ouput looks like:

GAMG:  Solving for Ux, Initial residual = 3.5620403e-05, Final residual = 1.145979e-07, No Iterations 1
GAMG:  Solving for Uy, Initial residual = 0.0016973702, Final residual = 6.0027881e-06, No Iterations 1
GAMG:  Solving for Uz, Initial residual = 0.001536366, Final residual = 4.8191816e-06, No Iterations 1
GAMG:  Solving for e, Initial residual = 0.00045292245, Final residual = 1.9744077e-06, No Iterations 1
GAMG:  Solving for p, Initial residual = 0.14242369, Final residual = 0.032751031, No Iterations 1000
GAMG:  Solving for p, Initial residual = 0.090691613, Final residual = 0.030714924, No Iterations 1000
GAMG:  Solving for p, Initial residual = 0.052047365, Final residual = 0.028755893, No Iterations 1000
GAMG:  Solving for p, Initial residual = 0.038641847, Final residual = 0.027810481, No Iterations 1000
GAMG:  Solving for p, Initial residual = 0.033185164, Final residual = 0.027251068, No Iterations 1000
GAMG:  Solving for p, Initial residual = 0.030303116, Final residual = 0.026959392, No Iterations 1000
time step continuity errors : sum local = 0.00026140328, global = -7.6367694e-16, cumulative = -1.1835275e-13
rho max/min : 1.5 1.1663043
ExecutionTime = 16521.99 s  ClockTime = 16533 s

if i reconstructPar and foamToVTK the last writen timestep and look at it in paraview i see a "normal" velocity distribution but when i look at pressure p there is all over the slice the standard pressure of 101325Pa which i dictate in the startup conditions. even if u look at the value range of p there's only this entry!

Can anyone help me and tell me, where is the problem or failure?
best regards,
cfdnewbie147