| 超声速进气道喘振的机理研究 |
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| 引用本文： | 王玉峰,杨宝娥.超声速进气道喘振的机理研究[J].火箭推进,2008,34(1):17-22. |
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| 作者姓名： | 王玉峰 杨宝娥 |
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| 作者单位： | 西安航天动力研究所,陕西,西安,710100 |
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| 摘 要： | 应用数值模拟方法对中心锥中心进气混压式进气道的喘振现象进行了研究。在数值计算的基础上,根据进气道出口截面每个网格点的压力、密度、速度等参数计算了进气道喘振过程中流量系数和总压恢复系数随时间的变化情况。同时给出了在喘振过程中激波振荡的振幅、频率、对应的波系图案。并根据进气道头部分离涡的发展情况以及进气道内通道中状态参数的变化情况对喘振产生的机理进行了分析,认为进气道头部分离涡对喘振的产生起关键的作用。
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| 关 键 词： | 进气道 喘振 分离涡 |
| 修稿时间： | 2007年6月26日 |
Study of the buzz mechanism of supersonic inlets |
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| Wang Yufeng,Yang Bao'e.Study of the buzz mechanism of supersonic inlets[J].Journal of Rocket Propulsion,2008,34(1):17-22. |
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| Authors: | Wang Yufeng Yang Bao'e |
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| Institution: | Wang Yufeng, Yang Bao＇e (Xi＇an Aerospace Propulsion Institute, Xi＇an 710100, China) |
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| Abstract: | In this paper buzz of a supersonic mixed-compression inlet with conic multi-compression is studied with numerical method. The periodical change of the pressure recovery and mass flow ratio is calculated on the base of the flow field result. The frequency,amplitude and shock wave train of the terminal shock wave oscillation during buzz process were analyzed. The development of the separated eddy on the compression surface works as a critical factor in inlet buzz based on the analysis of inlet flow field and state parameters. |
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| Keywords: | inlet buzz separate eddy |
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