混压式超声速进气道喉道长度的设计与数值研究

王新月; 高强; 王占学

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混压式超声速进气道喉道长度的设计与数值研究

专题研究 | 更新时间：2025-07-09

- 混压式超声速进气道喉道长度的设计与数值研究
- Design for Throat Length of Mix-Compression Supersonic Inlet with Numerical Analysis
- 西安交通大学学报 2009年43卷第3期页码：106-109
- 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：
  
  : 2008-09-03. 作者简介: 王新月(1955-),女,教授. 基金项目: 国防科工委基础科研基金资助项目(A0420060522)
- DOI：
  中图分类号： V211.3
- 网络首发：2009-03-10，
  
  纸质出版：2009
- 稿件说明：
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王新月, 高强, 王占学. 混压式超声速进气道喉道长度的设计与数值研究[J]. 西安交通大学学报, 2009,43(3):106-109.

Design for Throat Length of Mix-Compression Supersonic Inlet with Numerical Analysis[J]. 2009, 43(3): 106-109.
王新月, 高强, 王占学. 混压式超声速进气道喉道长度的设计与数值研究[J]. 西安交通大学学报, 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.

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references

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