Shock structure in separated nozzle flows |
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Authors: | Francesco Nasuti Marcello Onofri |
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Institution: | (1) Dip. Meccanica e Aeronautica, Univ. Roma “La Sapienza”, Via Eudossiana 18, 00184 Rome, Italy |
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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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Keywords: | Rocket nozzle Mach reflection Flow separation |
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