Nozzle flow separation

被引：19
|
作者：
Romine, GL [1 ]
机构：
[1] Lockheed Martin Astronaut, Titan Tech Integrat, Denver, CO 80201 USA
来源：
AIAA JOURNAL | 1998年 / 36卷 / 09期
关键词：
D O I：
10.2514/2.588
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
During the sea-level ignition process of rocket motors, the nozzle is subjected to an overexpanded flow condition that can cause high side loads. Prediction of the symmetrical separation location is the first key step to a determination of the range of possible side-load magnitudes. The mechanisms responsible for causing the flow to separate from the nozzle wall are demonstrated, and the theory for a new solution of the separation location is presented. The model is also correlated with historical rocket data, a new approximate solution, and an empirical curve fit that has been in use for 35 years.
引用
收藏
页码：1618 / 1625
页数：8
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