Dynamic investigation on hypersonic sidewall compression inlets with cowl valve during the process of transition

WU Jun-qi; ZHANG Kun-yuan

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Dynamic investigation on hypersonic sidewall compression inlets with cowl valve during the process of transition

更新时间：2026-07-07

- Dynamic investigation on hypersonic sidewall compression inlets with cowl valve during the process of transition
- Vol. 24, Issue 2, (2009)
- 作者机构：
  
  南京航空航天大学能源与动力学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
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WU Jun-qi, ZHANG Kun-yuan. Dynamic investigation on hypersonic sidewall compression inlets with cowl valve during the process of transition[J]. 2009, 24(2).
DOI：

WU Jun-qi, ZHANG Kun-yuan. Dynamic investigation on hypersonic sidewall compression inlets with cowl valve during the process of transition[J]. 2009, 24(2). DOI：

摘要

针对超燃冲压发动机从助推到接力工作的过渡状态

根据侧压式进气道从完全关闭到全部开启的工作要求

提出了一种新的变几何设计方案

即可变唇口活门方案.采用数值模拟和实验研究的方法

研究了发动机在工况变化的过渡过程中

可调唇口对进气道性能的影响

研究发现该方案可以实现进气道的启闭.在数值模拟的基础上

设计了一个唇口活门遥控调节的侧压式进气道模型

完成了这种变唇口侧压式进气道模型的Ma为3.85风洞试验

证明该进气道在设计起动马赫数Ma为3.85下能够正常开启并起动工作

验证了该方案的可行性.

Abstract

This paper aims at studying the transition of boosting to taking-over of scramjet.According to the working requirement of the sidewall compression inlets from completely close to completely open state

a new variable geometry inlet scheme for sidewall compression inlet——variable cowl valve scheme was presented.With the numerical simulation and experiment

the influence of variable cowl on performance of inlets was researched during the process of transition.Based on the numerical simulation

a variable cowl inlet model adjusted by remote control system have been designed

and this scheme has been firstly tested in Mach 3.85 wind tunnel.It proves that

at mach 3.85

the inlet can be opened and closed normally

thus further validating the feasibility of this scheme.

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Related Institution

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