| 二元高超声速进气道激波振荡特性实验 |
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| 引用本文： | 李祝飞,高文智,李鹏,姜宏亮,杨基明.二元高超声速进气道激波振荡特性实验[J].推进技术,2012,33(5):676-682. |
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| 作者姓名： | 李祝飞 高文智 李鹏 姜宏亮 杨基明 |
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| 作者单位： | 中国科学技术大学,安徽合肥,230027 |
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| 摘 要： | 通过在进气道/隔离段模型出口附近设置固定的堵塞楔块提高反压,并采用高速纹影拍摄同步壁面压强测量的手段,在马赫数5.9的激波风洞中研究了二元高超声速进气道在不同堵塞度下的流动特征。研究结果表明,在较低的堵塞度下,进气道仍然能够保持起动状态,而在较高的堵塞度下,进气道出现激波振荡。上游产生的压缩波/激波在节流段的反射是出现激波振荡的重要原因之一。随着堵塞度的增加,激波振荡的频率有所升高。
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| 关 键 词： | 激波风洞 高超声速进气道 激波振荡 |
| 收稿时间： | 2011/12/19 0:00:00 |
| 修稿时间： | 3/6/2012 12:00:00 AM |
Experimental Investigation on the Shock Wave Oscillation Behaviors in a Two-Dimensional Hypersonic Inlet Flow |
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| LI Zhu-fei,GAO Wen-zhi,LI Peng,JIANG Hong-liang and YANG Ji-ming.Experimental Investigation on the Shock Wave Oscillation Behaviors in a Two-Dimensional Hypersonic Inlet Flow[J].Journal of Propulsion Technology,2012,33(5):676-682. |
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| Authors: | LI Zhu-fei GAO Wen-zhi LI Peng JIANG Hong-liang and YANG Ji-ming |
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| Institution: | University of Science and Technology of China, Hefei 230027, China;University of Science and Technology of China, Hefei 230027, China;University of Science and Technology of China, Hefei 230027, China;University of Science and Technology of China, Hefei 230027, China;University of Science and Technology of China, Hefei 230027, China |
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| Abstract: | |
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| Keywords: | Shock tunnel Hypersonic inlet Shock wave oscillation |
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