航空工程进展2011，Vol.2Issue(3)：323-329,7.
基于单缝射流的二元推力矢量喷管设计及数值模拟
Two-dimensional Thrust Vectoring Nozzle Design and Numerical Simulation Based on Single Secondary Injection
王伟 1宋文艳 1罗飞腾 1李宁1
作者信息
- 1. 西北工业大学动力与能源学院,西安710072
- 折叠
摘要
Abstract
Nozzle is the main component of an engine,which produces thrust.Its aerodynamic performance is of a decisive influence to engine performance.A Two-Dimensional Convergent-Divergent（2DCD） thrust vectoring nozzle model with fixed length is designed by the simplified method of characteristics in this paper.The full flow-field of the 2DCD thrust vectoring nozzle with single secondary injection are numerically simulated by CFD method,with the RNG turbulence model and non-equilibrium wall functions employed.The influence of secondary injection locations,Nozzle Pressure Ratio（NPR） and Secondary Pressure Ratio（SPR） on aerodynamic performance of thrust vectoring nozzle are examined.The numerical results indicate that：the secondary injection location is of significant effect on shock intensity and thrust vectoring angle,the thrust vectoring angle gradually increase when secondary injection location is transferred toward the nozzle;at the same secondary injection location,the shock intensity and thrust vectoring angle are mainly affected by SPR;at the same of SPR,there exists a maximum thrust vectoring angle as NPR increasing.关键词
航空航天推进系统/推力矢量/喷管设计/激波诱导控制/数值模拟Key words
aerospace propulsion system/thrust vectoring/nozzle design/shock-induced vectoring control/numerical simulation分类
航空航天引用本文复制引用
王伟,宋文艳,罗飞腾,李宁..基于单缝射流的二元推力矢量喷管设计及数值模拟[J].航空工程进展,2011,2(3):323-329,7.
