Study of design method of typical two-dimensional hypeisonic inlet

ZHANG Xiao-jia; LIANG De-wang; LI Bo; YUAN Hua-cheng

Chinese

您当前的位置：

首页 >

文章列表页 >

Study of design method of typical two-dimensional hypeisonic inlet

更新时间：2026-07-07

- Study of design method of typical two-dimensional hypeisonic inlet
- Vol. 22, Issue 8, (2007)
- 作者机构：
  
  南京航空航天大学内流研究中心,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2007
- 稿件说明：
移动端阅览
ZHANG Xiao-jia, LIANG De-wang, LI Bo, et al. Study of design method of typical two-dimensional hypeisonic inlet[J]. 2007, 22(8).
DOI：

ZHANG Xiao-jia, LIANG De-wang, LI Bo, et al. Study of design method of typical two-dimensional hypeisonic inlet[J]. 2007, 22(8). DOI：

摘要

综合了一系列典型二元高超声速进气道的设计和性能估算方法

给出了可行的设计原则.在满足流量、增压以及工作范围(起动性能和反压承受能力)的条件下

给出了进气道进口、外压波系、内压缩通道、唇罩及隔离段的设计方法.采用此方法

以H=22800 m、Ma0=6为设计点

完成了一高超声速进气道的初步设计

并估算得到了进气道性能参数、进气道的起动马赫数和反压承受能力

对比CFD计算结果

误差不大.通过该方法得到的进气道具有结构简单、流量系数大、压缩损失小的特点

不通过优化即可得到性能较为良好的模型.

Abstract

A feasible design principle was developed by combining a series of design and performance predicting methods of typical two-dimensional hypersonic inlets.The design methods of inlet entrance

external compression shocks

internal contraction tunnel

cowl and isolator were presented at the given flux

pressure rise ratio and working range(starting Mach number and capability of enduring back pressure).A preliminary design of hypersonic inlet at the design point of H=22 800 m

Ma0=6 was conducted

so the performance parameters(pressure rise ratio

Mach number

temperature rise ratio and total pressure recovery)

starting Mach number and capability of enduring back pressure were predicted and calculated with small error.With this method

the inlet could present simple construction

high flow coefficient and low compression loss in developing a satisfactory model without optimization.

关键词

Keywords

references

Views

449

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Comparison of technical characteristics of APU and micro turbine engines for large aircraft

Effect of suctions on maximum backpressure ratios of hypersonic inlets

Experimental investigation on the starting characteristics of a hypersonic inlet with moving entrance door

Design and numerical simulation of a transonic swept fan DING Jian2guo,H U Jun

Design of a High Rotating Speed,Low Flow Rate Axial Flow Fan Used on Helicopters

Related Author

HUANG Guo-ping

LIANG De-wang

HE Zhi-qiang

CHANG Jun-tao

BAO Wen

CUI Tao

YU Da-ren

WANG Yi

Related Institution

The Institute of Micro-Engine, Nanjing University of Aeronautics and Astronautics

Grand China Express Limited company

School of Energy Science and Engineering, Harbin Institute of Technology

Institute of Aerospace and Material Engineering, National University of Defense Technology

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