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vishal March 2, 2009 23:02

Hi Fomers, I am trying to s
 
Hi Fomers,

I am trying to simulate a shock boundary layer interaction for the inlet of ramjet engine. the Solver i chose for this purpose is ¨SonicTurboFaom¨

Where as the inlet conditions i am using are.

p = 15198.75 pascle ;, U = 3Mach, Temp = 110.71K
k = 1000 and Epsilon = 266000.

The model used for solving is RNG K-Epsilon.

the FvScheams are :-

ddtSchemes
{
default Euler;
}

gradSchemes
{
default Gauss linear;
}

divSchemes
{
default none;
div(phi,U) Gauss limitedLinearV 1;
div(phi,k) Gauss upwind;
div(phi,epsilon) Gauss upwind;
div(phi,R) Gauss upwind;
div(R) Gauss linear;
div(phid,p) Gauss limitedLinear 1;
div(phiU,p) Gauss limitedLinear 1;
div(phi,h) Gauss limitedLinear 1;
div((muEff*dev2(grad(U).T()))) Gauss linear;
}

laplacianSchemes
{
default none;
laplacian(muEff,U) Gauss linear corrected;
laplacian(DkEff,k) Gauss linear corrected;
laplacian(DREff,R) Gauss linear corrected;
laplacian(DepsilonEff,epsilon) Gauss linear corrected;
laplacian((rho*(1|A(U))),p) Gauss linear corrected;
laplacian(alphaEff,h) Gauss linear corrected;
}

interpolationSchemes
{
default linear;
}

snGradSchemes
{
default corrected;
}

fluxRequired
{
p;
}

and the FvSolutions are :-

solvers
{
p PBiCG
{
preconditioner DILU;
tolerance 1e-15;
relTol 0;
};
rho PCG
{
preconditioner DIC;
tolerance 1e-15;
relTol 0;
};
U PBiCG
{
preconditioner DILU;
tolerance 1e-15;
relTol 0;
};
h PBiCG
{
preconditioner DILU;
tolerance 1e-15;
relTol 0;
};
k PBiCG
{
preconditioner DILU;
tolerance 1e-15;
relTol 0;
};
epsilon PBiCG
{
preconditioner DILU;
tolerance 1e-15;
relTol 0;
};
R PBiCG
{
preconditioner DILU;
tolerance 1e-15;
relTol 0;
};
}

PISO
{
nCorrectors 2;
nNonOrthogonalCorrectors 2;
}

The model i am using is RNG-K Epsilon for solving the case.

I have several combinations of the inlet to be validated. For one of the case i have been able to validate the case to certain extent.

But when i am trying to simulate some of the critical combinations. i am unable to capture the physics as expected, specially near expansion fan.

The output for Check Mesh is as follows.

Checking geometry...
Domain bounding box: (-0.04 0 0) (0.14245 0.12 0.0001)
Boundary openness (1.29075e-19 6.73437e-19 4.70648e-16) OK.
Max cell openness = 4.31882e-16 OK.
Max aspect ratio = 23.2673 OK.
Minumum face area = 6.07919e-10. Maximum face area = 5.1264e-06. Face area magnitudes OK.
Min volume = 6.07919e-14. Max volume = 5.1264e-10. Total volume = 1.8832e-06. Cell volumes OK.
Mesh non-orthogonality Max: 33.9556 average: 12.2948
Non-orthogonality check OK.
Face pyramids OK.
Max skewness = 1.0548 OK.
All angles in faces OK.
Face flatness (1 = flat, 0 = butterfly) : average = 1 min = 1
All face flatness OK.

Mesh OK.

End

The problem i am facing as explained is i am unable to Capture the wall pressure as desired.

I have used the sampling method till now is there any alternative for this offered in OF-1.5.

Thanks in advance for your Support.

Cheers,
Vishal


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