Research on two-dimensional hypersonic inlet based on dual-mode combustion

LI Hang; LI Bo

Chinese

您当前的位置：

首页 >

文章列表页 >

Research on two-dimensional hypersonic inlet based on dual-mode combustion

更新时间：2026-07-07

- Research on two-dimensional hypersonic inlet based on dual-mode combustion
- Vol. 27, Issue 7, (2012)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院,南京,210016
  2. 中国人民解放军 92724部队,山东,青岛,266000
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2012
- 稿件说明：
移动端阅览
LI Hang, LI Bo. Research on two-dimensional hypersonic inlet based on dual-mode combustion[J]. 2012, 27(7).
DOI：

LI Hang, LI Bo. Research on two-dimensional hypersonic inlet based on dual-mode combustion[J]. 2012, 27(7). DOI：

摘要

设计并研究了一种基于双模态燃烧的二元高超声速进气道.通过在进气道内设计一个隔板

将流道分为超声速通道和亚燃通道.采用数值模拟方法

研究了内压段肩部型面

隔板进口高度及水平位置

过渡段起始点及扩张角、下通道出口高度、隔板头部型面等几何设计参数对进气道性能的影响规律

并给出了参数选择建议.结果表明:在研究范围内

内压段肩部型面、隔板进口高度及水平位置和过渡段起始点对总压恢复系数影响较大;而隔板进口高度及头部型面、过渡段扩张角和下通道出口高度对抗反压能力有较大影响.

Abstract

Design and study of a two-dimensional hypersonic inlet based on dual-mode combustion was conducted.The duct was divided into a supersonic duct and a subsonic combustion duct by a splitter plate.The influence of the geometry parameters on the inlet performance was mainly studied by using numerical method.The geometry parameters included the profile of the shoulder

the height and position of splitter plate

the turning position and expansion angle of transition duct

the height of subsonic combustion duct and the shape of the head of splitter plate.Results indicate that the profile of the shoulder

the height and position of splitter plate

the turning position of transition duct have great effects on the total pressure recovery coefficient

while the height of splitter plate

the shape of the head of splitter plate

the expansion angle of transition duct and the height of subsonic combustion duct have great effects on characteristics of back pressure.

关键词

Keywords

references

Views

721

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Impact of suction position on starting of hypersonic inlet

Effect of suctions on maximum backpressure ratios of hypersonic inlets

Simulation method of short crack propagation in turbine disks based on crystal plasticity

Numerical simulation of internal flow field in gas generator of fire extinguishing bomb

Accurate prediction method of flow coefficient for 2D curved surface variable inlet

Related Author

WANG Wei-xing

YUAN Hua-cheng

HUANG Guo-ping

LIANG De-wang

CHANG Jun-tao

BAO Wen

CUI Tao

YU Da-ren

Related Institution

School of Energy Science and Engineering, Harbin Institute of Technology

School of Power and Energy，Northwestern Polytechnical University

Nondestructive Testing and Evaluation Laboratory， Dalian University of Technology

College of Civil Engineering， Hefei University of Technology

Key Laboratory of Aerospace Chemical Power Technology， Hubei Institute of Aerospace Chemical Techologh， China Aerospace Science and Technology Corporation，Xiangyang Hubei

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰