超燃冲压发动机尾喷管构型参数灵敏度分析

推进技术 ›› 2009, Vol. 30 ›› Issue (6): 691-695.

超燃冲压发动机尾喷管构型参数灵敏度分析

黄伟,罗世彬,王振国

国防科技大学航天与材料工程学院;国防科技大学航天与材料工程学院;国防科技大学航天与材料工程学院

发布日期:2021-08-15
基金资助:
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

Parametric sensitivity analysis of scramjet nozzle configuration

Inst. of Aerospace and Material Engineering, National Univ. of Defense Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defense Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defense Technology, Changsha 410073, China

Published:2021-08-15

摘要/Abstract

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。

关键词: 超音速冲压喷气发动机;尾喷管;性能;方差分析

Abstract: 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 wall and the flap angle should be larger. In order to improve the lift, the reflection angle of the nozzle upper wall should be larger and the length of the lower should be smaller.

Key words: Supersonic combustion ramjet engine;Nozzle;Performance;Analysis of variance

黄伟,罗世彬,王振国. 超燃冲压发动机尾喷管构型参数灵敏度分析[J]. 推进技术, 2009, 30(6): 691-695.