Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow

JIE Ke; YANG Zhan-yu; ZHAO Lü-shun; LIU Jian; WANG Hong-ming; HUANG Yong; SHAN Peng

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Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow

更新时间：2026-07-07

- Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow
- Vol. 22, Issue 12, (2007)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院,北京,100083
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2007
- 稿件说明：
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JIE Ke, YANG Zhan-yu, ZHAO Lü-shun, et al. Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow[J]. 2007, 22(12).
DOI：

JIE Ke, YANG Zhan-yu, ZHAO Lü-shun, et al. Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow[J]. 2007, 22(12). DOI：

摘要

结合对应的数值计算

对一种带亚声速预燃室和流向涡掺混器的超声速燃烧模型燃烧室实验台

在其进口马赫数为2.5的来流条件下

进行了冷态流场的实验研究.实验测得其壁面静压分布和激波系结构与流场的CFD计算结果基本一致.实验结果表明

模型燃烧室全流场超声速

达到设计状态.马赫数2.5下的冷态实验数据和CFD计算数据为进行点火实验提供了依据.

Abstract

An experimental study of cold flow field was conducted under entrance Mach number 2.5 on a supersonic combustor experiment rig with subsonic pilot combustor and stream-wise vortices mixer.The experiment result suggests that the up-wall static pressure distribution of wall surface and shock wave structure coincide with the CFDcalculation results

and the full flow field supersonic combustor reaches the design state.The cold test data and CFDcalculation data under 2.5Mach provide a basis for ignition test.

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Related Institution

School of Aerospace, Tsinghua University

Institute of Mechanical Engineering, Southwest Jiaotong University

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