| 双燃式(超燃)冲压发动机中激波与边界层之间相互作用对内部流动的影响 |
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| 引用本文： | 张树道,韩肇元,徐胜利,司徒明.双燃式(超燃)冲压发动机中激波与边界层之间相互作用对内部流动的影响[J].实验流体力学,1999,13(2). |
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| 作者姓名： | 张树道 韩肇元 徐胜利 司徒明 |
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| 作者单位： | 1. 中国科学技术大学力学和机械工程系,合肥,230027
2. 中国航天工业总公司三十一所,北京,100074 |
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| 基金项目： | 国家自然科学基金,中科院基金 |
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| 摘 要： | 在激波风洞中研究了激波与边界层之间相互作用对双燃式（超燃）冲压发动机进气道和燃烧室冷态内部流场的影响，实验发现在进气道中，激波与边界层之间的相互作用产生了两侧均为超声速流的滑移面。实验结果表明内涵道（亚燃室）中流动状态的变化与激波－边界层之间相互作用密切相关。
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| 关 键 词： | 激波与边界层相互干扰 超声速燃烧冲压发动机 双燃式 内流场 |
The Effect of Interaction of Shock Waves with Boundary Layers to The Cold Internal Flow Field of A Dual-Combustor Scramjet Model |
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| Zhang Shudao,Han Zhaoyuan,Xu Shengli,Situ Ming.The Effect of Interaction of Shock Waves with Boundary Layers to The Cold Internal Flow Field of A Dual-Combustor Scramjet Model[J].Experiments and Measur in Fluid Mechanics,1999,13(2). |
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| Authors: | Zhang Shudao Han Zhaoyuan Xu Shengli Situ Ming |
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| Abstract: | In this paper,the effect of interaction of shock waves with boundary layers to the cold internal flow field of the inlet and combustor of a dual combustor scramjet model has been investigated in a shock tunnel.It has been found that there was a contact surface caused by the interaction of shock waves with boundary layers on each side of which the flow was supersonic in the inlet.It has been proved that the flow state was closely related to the interaction of shock waves with boundary layers in the pilot duct. |
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| Keywords: | shock waves boundary layers interference scramjet engine dual combustor internal flow |
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