Investigation on hypersonic inward turning inlets with controlled pressure gradient

NAN Xiang-jun; ZHANG Kun-yuan; JIN Zhi-guang; SUN Bo

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Investigation on hypersonic inward turning inlets with controlled pressure gradient

更新时间：2026-07-07

- Investigation on hypersonic inward turning inlets with controlled pressure gradient
- Vol. 26, Issue 3, (2011)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院,南京,210018
  2. 南京理工大学机械工程学院航空宇航系,南京,210094
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
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NAN Xiang-jun, ZHANG Kun-yuan, JIN Zhi-guang, et al. Investigation on hypersonic inward turning inlets with controlled pressure gradient[J]. 2011, 26(3).
DOI：

NAN Xiang-jun, ZHANG Kun-yuan, JIN Zhi-guang, et al. Investigation on hypersonic inward turning inlets with controlled pressure gradient[J]. 2011, 26(3). DOI：

摘要

针对高超声速内收缩进气道

以有旋特征线理论研究了一种型面压升规律可控的新型轴对称基准流场;结合流线追踪技术

以等压力梯度为例

探讨了一种圆形进口的内收缩进气道设计方法

并对三种不同压升规律的内收缩进气道性能进行了比较.结果表明

采用基准流场的内收缩进气道

能较好地保持基准流场的预定压升规律

从而拓宽了基准流场的选择范围

提高了型面设计的灵活性.针对所研究的三种压升规律

压力梯度逐渐增大的进气道其压缩效率最高

等压力梯度次之

压力梯度逐渐减小的进气道压缩效率最低.此外

研究发现

通过调整压升规律还可改变进气道的内外压分配

有助于实现此类进气道的宽马赫数范围工作.

Abstract

Axisymmetric basic flowfields with controlled pressure gradient used for hypersonic inward turning inlets were investigated using the rotational method of characteristics.In combination with streamline tracing technique

a circular inward turning inlet with the law of constant pressure gradient was designed and numerically simulated.Results show that the inward turning inlet could maintain the same law of pressure rise as its basic flowfield.Through study of the three laws of wall pressure rise

pressure gradient increase

steadiness and decrease

it's found the inlet with the first law of pressure rise has the maximum compression efficiency

and the inlet with the third law of pressure rise has the lowest compression efficiency.In addition

we can get good internal and external compression assignment by adjusting the law of pressure rise

contributing to make this type of inlet operate well over a large wide range of Mach number.

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Related Author

JIN Zhi-guang

ZHANG Kun-yuan

NAN Xiang-jun

XIANG You-zhi

NAN Xiang-jun

WANG Lei

ZHANG Lin

FANG Li-cheng

Related Institution

School of Astronautics, Beijing University of Aeronautics and Astronautics

Internal Flow Research Center, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

Beijing Institute of Aerospace Testing Technology

国防科技大学高超声速技术实验室

合肥工业大学机械工程学院

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