抽吸对高超侧压进气道自起动性能的影响

赵一龙; 范晓樯; 王翼; 王振国

抽吸对高超侧压进气道自起动性能的影响

国防科学技术大学航天科学与工程学院高超声速冲压发动机技术重点实验室, 长沙 410073

基金项目: 国家自然科学基金(10802096)

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出版历程
- 收稿日期: 2012-05-22
- 刊出日期: 2013-05-28

Effects of bleeding on self-starting characteristics of side-compression hypersonic inlet

Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China

摘要

摘要: 针对某型高超侧压进气道设计了纵向槽、横向槽和圆孔等4种抽吸方案,对各方案的进气道流场进行了数值模拟.结果表明:抽吸可以显著提升进气道的自起动性能,且对进气道不起动流场的分离区进行抽吸的效果最佳,文中最优方案将进气道的自起动马赫数由4.6降至3.7.对进气道进行了马赫数为4条件下变攻角的风洞试验,验证了抽吸对提升进气道自起动性能的有效性.
- 高超侧压进气道 /
- 自起动 /
- 抽吸 /
- 数值仿真 /
- 风洞试验
Abstract: Various bleeding cases with slots and holes were designed for a side-compression hypersonic inlet,and the numerical simulation was conducted.The results show that the self-starting characteristics of the inlet can be significantly improved,and bleeding in the separation zone of the inlet has the best effects.The self-starting Mach number of the inlet was reduced from 4.6 to 3.7 in the research.The inlets with different attack angles were tested in the wind tunnel at the flow condition of Mach 4.The experimental results confirmed the bleeding effects on the improvement of the self-starting characteristics of the inlet.
- side-compression hypersonic inlet /
- self-start /
- bleeding /
- numerical simulation /
- wind tunnel test

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参考文献(17)

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