Investigation of the restart performance of a mixed-compression two-dimensional supersonic inlet with fixed-geometry

XIE Lü-rong; GUO Rong-wei

Chinese

您当前的位置：

首页 >

文章列表页 >

Investigation of the restart performance of a mixed-compression two-dimensional supersonic inlet with fixed-geometry

更新时间：2026-07-07

- Investigation of the restart performance of a mixed-compression two-dimensional supersonic inlet with fixed-geometry
- Vol. 23, Issue 2, (2008)
- 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：2008
- 稿件说明：
移动端阅览
XIE Lü-rong, GUO Rong-wei. Investigation of the restart performance of a mixed-compression two-dimensional supersonic inlet with fixed-geometry[J]. 2008, 23(2).
DOI：

XIE Lü-rong, GUO Rong-wei. Investigation of the restart performance of a mixed-compression two-dimensional supersonic inlet with fixed-geometry[J]. 2008, 23(2). DOI：

摘要

针对一种设计飞行马赫数范围为2.25～4.0的定几何混压式二元超声速进气道由于反压引起的不起动开展了再起动特性风洞实验研究.根据实验结果和二维非定常数值仿真结果分析表明:在Ma=2.51和3.01下进气道性能在进锥/退锥实验中规律一致;按照Ma=2.25的起动面积收缩比确定的喉道面积

使进气道在来流Ma≥2.51时具有自起动能力;而在稳定亚临界状态下具有高的总压恢复系数及形成类似于外压式的气动通道是进气道无回路迟滞现象的主要原因.

Abstract

An experimental study was conducted to investigate the restart performance of a fixed-geometry

mixed-compression

two-dimensional supersonic inlet under unstart condition due to raising backpressure

with a designed flight Mach number from 2.25 to 4.0.The test results and two-dimensional unsteady simulation results show that

the inlet performance is consistent in the inlet wall and exit section tests at Mach number of 2.51 and 3.01;the throat area is determined according to the start area shrinkage ratio at Mach=2.25

so that the inlet enables self-start at Ma=2.5 and above.The phenomenon of no hysteresis under stable subcritical condition is because of a high total pressure recovery and a flow pattern of inlet similar to external compression inlet.

关键词

Keywords

references

Views

446

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Characteristic analysis of unstart/restart of hypersonic inlets caused by variations of attack angle of freestream

Unstart Simulation of Scramjet Inlets

Numerical investigation on restart characteristics of two-dimensional twin-duct supersonic inlet at sideslip state

Study of start/unstart phenomenon of supersonic inlet in acceleration/deceleration process

Prediction method on equivalent thermal conductivity coefficient of plain braided C/SiC composites material based on finite element method

Related Author

CHANG Jun-tao

YU Da-ren

BAO Wen

GUO Xin-gang

CUI Tao

温玉芬

陈皓

马友林

Related Institution

School of Science and Technology Research, Harbin Institute of Technology

School of Energy Science and Engineering, Harbin Institute of Technology

中国航天科技集团公司中国运载火箭技术研究院

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

China Aviation Powerplant Research Institute, Aviation Industry Corporation of China

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