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- - **OF15 for High Mach flows**
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Hi Fomers,
I am trying to sHi 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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