Unsteadiness of flow separation and end-effects regime in a thrust-optimized contour rocket nozzle

被引：55
|
作者：
Nguyen, AT [1 ]
Deniau, H [1 ]
Girard, S [1 ]
De Roquefort, TA [1 ]
机构：
[1] Lab Etud Aerodynam & Therm, UMR CNRS ENSMA 6609, F-86036 Poitiers, France
来源：
FLOW TURBULENCE AND COMBUSTION | 2003年 / 71卷 / 1-4期
关键词：
free shock separation; nozzle; restricted shock separation; side loads;
D O I：
10.1023/B:APPL.0000014927.61427.ad
中图分类号：
O414.1 [热力学];
学科分类号：
摘要：
Turbulent flow separation in over-expanded rocket nozzles is investigated experimentally in a sub-scale model nozzle fed with cold air and having a thrust-optimized contour. Depending upon the pressure ratio either a free shock separation (FSS) or a restricted shock separation (RSS) is observed with a significant hysteresis between these two flow regimes. It is shown that the RSS configuration may involve several separated regions. Analysis of wall pressure fluctuations give quantitative information on the fluctuating pressure field directly connected with the occurrence of significant side loads. Direct measurements of the evolution of the side loads with respect to the pressure ratio show the occurrence of three distinct peaks which are explained by the wall pressure fluctuations measurements.
引用
收藏
页码：161 / 181
页数：21
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