兵工自动化2011，Vol.30Issue(12)：23-24,34,3.DOI:10.3969/j.issn.1006-1576.2011.12.007
固体火箭发动机喷管分离流动及其数值模拟
Flow Separation and Numerical Simulation of Solid Rocket Motor Nozzle
王晓辉 1于存贵1
作者信息
- 1. 南京理工大学机械工程学院,南京210094
- 折叠
摘要
Abstract
Separation flow could be generated in a high-altitude nozzle, in order to study the flow separation on the nozzle performance. A three-dimensional numerical simulation about the separation flow in the high-altitude nozzle of a solid rocket motor (SRM) was conducted. The flow results with different inlet total pressure were obtained by utilizing CFX software. It shows that, due to the separation flow, there are some adverse effects for the stability and thermal protection of the nozzle. The simulation provides a reference of the design of the high-altitude nozzle, also a basis for further study.关键词
固体火箭发动机/喷管/分离流动/数值模拟Key words
solid rocket motor/ nozzle/ flow separation/ numerical simulation分类
军事科技引用本文复制引用
王晓辉,于存贵..固体火箭发动机喷管分离流动及其数值模拟[J].兵工自动化,2011,30(12):23-24,34,3.
