Abstract
In the case of high overexpansion, the exhaust jet of the supersonic nozzle of rocket engines separates from nozzle wall because of the large adverse pressure gradient. Correspondingly, to match the pressure of the separated flow region, an oblique shock is generated which evolves through the supersonic jet starting approximately at the separation point. This shock reflects on the nozzle axis with a Mach reflection. Thus, a peculiar Mach reflection takes place whose features depend on the upstream flow conditions, which are usually not uniform. The expected features of Mach reflection may become much difficult to predict, depending on the nozzle shape and the position of the separation point along the divergent section of the nozzle.
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Nasuti, F., Onofri, M. Shock structure in separated nozzle flows. Shock Waves 19, 229–237 (2009). https://doi.org/10.1007/s00193-008-0173-7
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DOI: https://doi.org/10.1007/s00193-008-0173-7