A model to predict the Mach reflection of the separation shock in rocket nozzles

被引：0
|
作者：
Nasuti, F. [1 ]
Onofri, M. [1 ]
机构：
[1] Univ Roma La Sapienza, Dipartimento Meccan & Aeronaut, I-00184 Rome, Italy
来源：
SHOCK WAVES, VOL 2, PROCEEDINGS | 2009年
关键词：
D O I：
10.1007/978-3-540-85181-3_48
中图分类号：
TH [机械、仪表工业];
学科分类号：
0802 ;
摘要：
In 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. At the same time, to match the pressure of the separated flow region, an oblique shock is generated which evolves through the supersonic jet starting approximately from the separation point. This shock reflects oil 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. A simplified model is presented which is a first step to predict the expected features of Mach reflection depending oil the nozzle shape and oil the position of the separation point along the divergent section of the nozzle.
引用
收藏
页码：1093 / 1098
页数：6
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