论文信息 - Turbulence Modelling for Supersonic Separated Flows

Turbulence Modelling for Supersonic Separated Flows

Shock-induced flow separation takes place in rocket nozzles when operate under over-expanded conditions. Numerical prediction of these supersonic separated flows has been a challenge for the existing RANS models and their respective LES/RANS techniques. In the present research work an extensive and comparative study of these turbulence modelling methodologies has been undertaken to investigate free shock separation flow configuration in thrust optimized contour (TOC) nozzle.

P. Comte | A. Shams

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