超燃冲压发动机尾喷管构型参数灵敏度分析  

Parametric sensitivity analysis of scramjet nozzle configuration

作　　者：黄伟[1] 罗世彬[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2009年第6期691-695,共5页Journal of Propulsion Technology

基　　金：国防科技大学优秀研究生创新资助项目(B070101);湖南省研究生创新项目的资助

摘　　要：采用正交拉丁方设计和方差分析的方法对尾喷管气动-推进性能进行了研究,考察了设计参数对其性能的灵敏程度,发现尾喷管上壁面型线起始点切线角度和外罩后伸长度对其气动-推进性能影响显著,而外罩后掠角的影响不明显;同时,减小尾喷管上壁面型线起始点切线角度,增大外罩的后伸长度和后掠角能提高尾喷管的推力特性和俯仰力矩特性,而增大尾喷管上壁面型线起始点切线角度,减小外罩后伸长度则对尾喷管升力的提高有益。The methods of orthogonal latin squares design and variance analysis were introduced to investigate the aero-propulsive performance of nozzle, reviewing the influence of design variables on its performance. The results show that the reflection angle of the nozzle upper wall and the length of the lower wall have remarkable influence on nozzle performance. Meanwhile, in order to improve the thrust and pitching moment, the reflection angle of the nozzle upper wall should be smaller and the length of the lower ...

关 键 词：超音速冲压喷气发动机 尾喷管 性能 方差分析 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]