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- W2329899054 abstract "Accurate numerical simulation of separated ows in contoured rocket nozzles is challenging because of the complex ow eld phenomena, in which turbulence has a major role, that develops (shock-pattern, shock-boundary layer interaction, high-speed shear layers and vortices, uctuations). Hence, turbulence modeling is a key aspect for success in the simulations, specifically for the accurate prediction of shock-induced ow separation, as it is stressed by the failure of many existing turbulence models intended for engineering applications. In this work, the assessment of turbulence modeling with the commercial CFD code FLUENT is investigated. Validation results with separated cold gas ow in Thrust-Optimized Parabolic nozzle using the Spalart-Allmaras (SA) and the Shear Stress Transport (SST) turbulence models are compared in axisymmetric steady-state simulations carried out for the DLR-PAR subscale nozzle. The comparison with experimental data shows that the standard SST model yields more accurate results than the SA model, albeit still predicts an earlier separation location to some extent. The present study suggests tuning of the major coe cients in the eddy-viscosity equation of the SST model in order to improve the predictions, by matching the wall pressure distributions with" @default.
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- W2329899054 date "2011-07-31" @default.
- W2329899054 modified "2023-10-18" @default.
- W2329899054 title "Improved Prediction of Flow Separation in Thrust Optimized Parabolic Nozzles with FLUENT" @default.
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- W2329899054 doi "https://doi.org/10.2514/6.2011-5689" @default.
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