Design for Throat Length of Mix-Compression Supersonic Inlet with Numerical Analysis

您当前的位置：

首页 >

文章列表页 >

Design for Throat Length of Mix-Compression Supersonic Inlet with Numerical Analysis

更新时间：2025-07-09

- Design for Throat Length of Mix-Compression Supersonic Inlet with Numerical Analysis
- Vol. 43, Issue 3, Pages: 106-109(2009)
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：
  CLC： V211.3
- Online First：10 March 2009，
  
  Published：2009
- 稿件说明：
移动端阅览
Design for Throat Length of Mix-Compression Supersonic Inlet with Numerical Analysis[J]. 2009, 43(3): 106-109.
DOI：

Design for Throat Length of Mix-Compression Supersonic Inlet with Numerical Analysis[J]. 2009, 43(3): 106-109. DOI：

摘要

为了提高定几何混压式超声速进气道的性能

对冲压发动机轴对称混压式超声速进气道进行了研究

并重点研究了喉道长度的设计及激波附面层干扰对进气道性能的影响.数值计算结果表明:在进气道总长度一定的条件下

喉道长度小于激波链长度的设计对进气道的总性能更有利.在计算马赫数分别为3.5和4.0的条件下

将喉道长高比为3.75和10.0的进气道相比

其总压恢复系数分别增加了6.15%和5.04%; 对于长度一定的进气道

喉道越长

则扩张段越短

达到同样扩张比的扩张角就越大.因此

对于设计马赫数为4.0的进气道

取喉道长高比为3.75时

进气道的总压恢复系数最高

抗反压能力也较强

该结果可为定几何混压式超声速进气道的设计提供参考.

Abstract

To enhance the performance of mixed-compression axisymmetric supersonic inlet with fixed-geometry

the performances of designing Mach number 4 mixed-compression inlet of ramjet are investigated. The numerical calculation is carried out for the performance of inlet with the different length of throat. The research shows that it is necessary that the length of throat is less than the length of shock chain in the inlet of constant length. Especially for the shorter length of throat

total pressure recovery coefficient is enhanced at higher Mach number condition. When Mach number equals to 3.5 and 4.0

the total pressure recovery coefficient is enhanced by 6.15% and 5.04% for length-to-height ratio of throat 3.75 and 10 respectively. The longer the length of throat

the shorter the length of diffuser for given inlet length. Simultaneously

the performance of inlet will be deduced. When length-to-height ratio of inlet throat equals to 3.75

the total pressure recovery coefficient and the ability of resistance backpressure of the inlet are highest under design Mach number 4 condition. This result provides a reference for the design of the mixed-compression axisymmetric inlet with high designing Mach number.

关键词

Keywords

references

谢旅荣,郭荣伟. 定几何混压式轴对称超音速进气道气动特性数值仿真和实验研究 [J].航空学报,2007,28(1):78-83.

XIE Lürong, GUO Rongwei. Numerical simulation and experimental validation of flow in mixed-compression axisymmetric supersonic inlet with fixed-geometry[J]. Acta Aeronautica et Astronatica Sinica, 2007,28(1):78-83.

MAHONEY J J. Inlets for supersonic missiles[M]. Virginia, USA:AIAA Education Series, 1990.

ZHA Gecheng, KNIGHT D, SMITH D. Investigations of high-speed civil transport inlet unstart at angle of attack [J]. Journal of Aircraft, 1998, 35(6): 851-856.

WEIR L J, SANDERS B W, VACHON J. A new design concept for supersonic axisymmetric inlets, 2002-3775 [R]. New York, USA:AIAA,2002.

MARU Y. Multi-row disk arrangement concept for spike of axisymmetric air inlet, 2004-3407[R]. New York, USA: AIAA,2004.

KOBAYASHI H, TANATSUGU N, TETSUYA S, el al. Experimental study of multi-row disk inlets for hypersonic air breathing propulsion, 2004-861[R]. New York, USA:AIAA, 2004.

BENCZE D P, SORENSEN N E. A study of the relative merits of three axisymmetric inlets for a hypersonic cruise mission, 1970-687[R]. New York, USA: AIAA,1970.

SORENSEN N E, LATHAM E A, SMELTZER D B. Variable geometry for supersonic mixed-compression inlets, 74-1172 [R]. New York, USA: AIAA, 1974.

VERSTEEG H K, MALALASEKERA W. An introduction to computational fluid dynamics the finite volume method [M]. 北京:世界图书出版公司,1995.

GOKHALE S S, KUMAR V R. Numerical computations of supersonic inlet flow [J]. International Journal for Numerical Methods in Fluids, 2001, 36(5): 597-617.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical Calculation of Acoustic Properties of Porous Metal at High Sound Pressure Level

Calculating Magnetic Vector Potential in 3-D Electromagnetoquasistatic Field with Fast Multipole Method

Kinetic Characteristics Analysis for a Synchronal Rotary Refrigerating Compressor

Numerical Investigation to Performance of Centrifugal Impeller with Vortex Generator Jets

Lubrication Properties of Herringbone Groove Bearings in Micro-Motors

Related Author

陈天宁 1

张波 1

盛剑霓

罗先觉

王晓丽

俞炳丰

周慧

Related Institution

School of Mechanical Engineering, Ningxia University

School of Mechanical Engineering, Xi'an Jiaotong University

School of Electrical Engineering, Xi'an Jiaotong University

School of Energy and Power Engineering, Xi'an Jiaotong University

School of Mechanical Engineering, Xinjiang University

⁰