Computational analysis on shock induction control of circular vectoring exhaust nozzle

QIN Ya-xin; YU Jun-li; GAO Ge

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Computational analysis on shock induction control of circular vectoring exhaust nozzle

更新时间：2026-07-07

- Computational analysis on shock induction control of circular vectoring exhaust nozzle
- Vol. 24, Issue 10, (2009)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
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QIN Ya-xin, YU Jun-li, GAO Ge. Computational analysis on shock induction control of circular vectoring exhaust nozzle[J]. 2009, 24(10).
DOI：

QIN Ya-xin, YU Jun-li, GAO Ge. Computational analysis on shock induction control of circular vectoring exhaust nozzle[J]. 2009, 24(10). DOI：

摘要

利用时间推进的有限体积法求解三维雷诺平均Navier-Stokes方程

对激波诱导矢量控制方案的圆形收敛-扩张喷管全流场进行了数值模拟.从射流压强比及落压比的变化计算了次流对主流的控制效果.结果表明

利用激波诱导方式可有效的迫使主流偏转

在落压比为4、射流压强比为1.499时

矢量偏转角最大可以达到15.35°.通过分析

圆形喷管中形成的激波为三维曲面激波

结构比较复杂

数值研究可观察到清晰的流场结构

为试验研究提供参考.

Abstract

Three-dimensional Reynolds average Navier-Stokes equation was solved by using the time marching method in finite volume

and circular convergent-divergent nozzle flow fields in shock induction control vector scheme were numerically simulated.Injection pressure ratio and nozzle pressure ratio were considered in numerical analysis in this paper.The results indicate that

thrust vectoring can be obtained through the shock induction control scheme to turn the main flow.The vector angle reaches 15.35° when the nozzle pressure ratio is 4 and injection pressure ratio is 1.499.Through analysis

the shock surface formed in the circular exhaust nozzle was three-dimensional

and its configuration was complicated.The computational analysis is helpful for better understanding of the flow field structure of vectoring nozzle in experiments.

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