攻角引起的高超声速进气道不起动/再起动特性分析

常军涛; 于达仁; 鲍文

攻角引起的高超声速进气道不起动/再起动特性分析

1.
哈尔滨工业大学科学技术研究院, 哈尔滨 150001
2.
哈尔滨工业大学能源科学与工程学院, 哈尔滨 150001

计量
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- 被引次数: 0
出版历程
- 收稿日期: 2007-01-04
- 修回日期: 2007-04-26
- 刊出日期: 2008-05-28

Characteristic analysis of unstart/restart of hypersonic inlets caused by variations of attack angle of freestream

1.
School of Science and Technology Research, Harbin Institute of Technology, Harbin 150001, China
2.
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 起动/不起动是高超声速进气道的重要流动现象,其影响进气道的工作范围和再起动能力.首先对典型的高超声速进气道二维流场进行了数值模拟,对攻角变化引起的高超声速进气道不起动/再起动过程进行了研究.从流动稳定性的角度阐述了高超声速进气道不起动/再起动特性形成的原因,分析了高超声速进气道不起动/再起动过程中进气道性能参数随来流攻角的变化规律,最后对进气道的再起动条件进行了讨论.
- 航空、航天推进系统 /
- 高超声速进气道 /
- 不起动 /
- 再起动 /
- 数值模拟
Abstract: Unstart/restart is one of most important phenomenon in hypersonic inlets,which affects the operation range and the restart capacity.Atwo-dimensional internal flow field of mixed-compression hypersonic inlets was simulated numerically.The flow characteristics of unstart/restart caused by variations of attack angle were also investigated.The reasons behind the formation of inlet unstart/restart was discussed from the viewpoint of hydrodynamic stability.The inlet performance parameters varying with angle of attack were analyzed.Finally,the condition of inlet restart was discussed.
- aerospace propulsion system /
- hypersonic inlets /
- unstart /
- restart /
- numerical simulation

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参考文献(14)

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