Experimental Studies of a Caret Inlet at Supersonic Speed

ZHU Yu; LEE Chun-hian; LI Tian

Chinese

您当前的位置：

首页 >

文章列表页 >

Experimental Studies of a Caret Inlet at Supersonic Speed

更新时间：2026-07-07

- Experimental Studies of a Caret Inlet at Supersonic Speed
- Vol. 18, Issue 2, (2003)
- 作者机构：
  
  1. 北京航空航天大学国家计算流体力学实验室,北京,100083
  2. 沈阳飞机设计研究所,辽宁,沈阳,110035
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2003
- 稿件说明：
移动端阅览
ZHU Yu, LEE Chun-hian, LI Tian. Experimental Studies of a Caret Inlet at Supersonic Speed[J]. 2003, 18(2).
DOI：

ZHU Yu, LEE Chun-hian, LI Tian. Experimental Studies of a Caret Inlet at Supersonic Speed[J]. 2003, 18(2). DOI：

摘要

对一种Caret进气道进行了试验研究

给出了该型进气道超音速基本气动特性。该进气道在Ma=1.6～2.0范围总压恢复急剧下降。在Ma=2.0时

由于亚临界防喘余量较小

在放气门关闭情况下将无进/发匹配点;在喘振点处

稳态周向畸变相对于临界状态在减小

而动态紊流度急剧增加;临界至超临界情况

在两个压缩斜板的交角后管道内出现流动分离。

Abstract

A Caret inlet was studied by testing.Basic aerodynamic characteristics of the inlet at supersonic speed are presented.The total pressure recovery rapidly drops from Mach 1.6 to 2.0.No inlet/engine match point at Mach 2.0 without bypass was found due to the fact that the surge margin happened to be too narrow.Steady circumferential distortion declines from surge to critical state

nevertheless

dynamic turbulence intensity increases rapidly.Flow separations are visible in duct from critical to supercritical states

these separations stem from the intersection of two ramps and low outboard.

关键词

Keywords

references

Views

414

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical Investigation of Inlet with Swept Compress Ramp

Experiment on influence of front/after⁃mounted propeller on turboprop engine performance

Modal decomposition and rapid prediction of shock train oscillation for inlet

Design and optimization of columniform distributed ejector for low speed wind tunnel inlet test

Aerodynamic performance influence of propeller slipstreamon engine intake

Related Author

ZHU Yu

LEE Chun-hian

LI Tian

Yuqing WEI

Feng GUO

Jianfeng ZHU

Wei LI

Xing HUANG

Related Institution

Beijing University of Aeronautics and Astronautics

Shenyang Aircraft Design Research Institute

School of Aerospace Engineering，Xiamen University

Hunan Aviation Powerplant Research Institute， Aero Engine Corporation of China

College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics

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