Hybrid RANS/LES Simulation of Shock-Induced Separated Flow in Truncated Ideal Contour Nozzle
The present study is motivated by the flow analysis of supersonic nozzles used in the rocket launcher, more specifically about the generation of side loads. The work aims at identifying and at modeling the dominant elements of the organized structure of the flow in overexpanded rocket nozzles.
The work presented is part of the nozzle research project ATAC led by the French Space Center (CNES). This work was performed using HPC resources from GENCI [TGCC] (Grant 2017 [A0012A10017]).
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