高超声速条件下溢流液膜厚度测量方法
Measuring method of overflow liquid film thickness in hypersonic flow
查看参考文献16篇
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文摘
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高超声速溢流液膜冷却是一种新型的飞行器热防护方法,还处于探索阶段,液膜厚度作为最基本的参数,对研究液膜形成条件、冷却机理、冷却性能评估等方面具有重要的意义.针对膜厚测量的基本问题,总结各研究领域内相关的方法,并对各方法应用于高超声速溢流液膜冷却实验的可行性进行了详细的分析和讨论,筛选确定了利用电导法测量高超声速溢流液膜厚度.在高超声速激波风洞来流Ma=6的条件下,开展了15°楔模型溢流液膜冷却实验,利用电导法测量液膜建立过程中液膜厚度的变化,验证了电导法测量溢流液膜厚度的可行性,并对高超声速条件下的溢流液膜流动特性进行了初步分析. |
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其他语种文摘
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Hypersonic overflow liquid film cooling is a new method for aircraft thermal protection, and is still in the exploratory stage. As the most basic parameter, liquid film thickness helps to reveal the film forming conditions, which promotes the cooling mechanism research and evaluate cooling performance reasonably. In this paper, aiming at the film thickness measurement, methods in each research field were reviewed. Feasibility of the methods were analyzed and discussed in detail, and the conductance method was selected for its advantages. Experiments were carried out in a hypersonic wind tunnel, with a 15° wedge model and Mach number 6 flow condition. Liquid film thickness during the formation of liquid film was obtained, which verified the feasibility of the conductance method. Meanwhile, characteristics of the overflow liquid film in hypersonic flow were analyzed based on the measurement. |
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来源
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中国科学. 技术科学
,2018,48(6):629-638 【核心库】
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DOI
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10.1360/n092017-00178
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关键词
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高超声速热防护
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主动冷却
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液膜厚度
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电导法
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地址
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1.
中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190
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中国科学院大学工程科学学院, 北京, 100049
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1674-7259 |
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学科
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航天(宇宙航行) |
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基金
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国家自然科学基金
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文献收藏号
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CSCD:6277337
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