| 矩形截面高超声速进气道气动设计及实验验证 |
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| 引用本文： | 袁化成,郭荣伟.矩形截面高超声速进气道气动设计及实验验证[J].南京航空航天大学学报,2009,41(4). |
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| 作者姓名： | 袁化成 郭荣伟 |
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| 作者单位： | 南京航空航天大学能源与动力学院,南京,210016 |
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| 基金项目： | 国家高技术发展研究计划 |
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| 摘 要： | 首先对矩形截面高超声速进气道设计方法进行了研究,给出了设计流程,并据此设计了矩形截面高超声速进气道.接着对其进行了三维数值仿真研究,给出了进气道性能参数随来流马赫数、飞行迎角及飞行高度的变化规律.最后设计了实验模型,并进行了高焓风洞实验验证.数值模拟及高焓风洞实验验证均表明:本文采用的设计方法可达到预期的设计效果,设计的进气道达到了相应的设计要求,本文采用的数值仿真方法可以较为准确地模拟高超声速进气道内的流动,数值模拟结果可信.
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| 关 键 词： | 高超声速进气道 设计方法 矩形截面 实验验证 |
Design and Experimental Verification of Hypersonic Inlet with Rectangular Section |
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| Yuan Huacheng,Guo Rongwei.Design and Experimental Verification of Hypersonic Inlet with Rectangular Section[J].Journal of Nanjing University of Aeronautics & Astronautics,2009,41(4). |
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| Authors: | Yuan Huacheng Guo Rongwei |
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| Institution: | College of Energy and Power Engineering;Nanjing University of Aeronautics & Astronautics;Nanjing;210016;China |
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| Abstract: | The design method for a hypersonic inlet with a rectangular section is presented and the inlet is designed at the point of Ma=6.0.The flow in the hypersonic inlet is analyzed with a three-dimensional numerical analyzer.The flow characteristics at different Mach numbers,attack angles and flying attitudes are also discussed.The preliminary test verification is conducted in the hypersonic inlet at Ma=6 in a high enthalpy tunnel.The total pressure and static pressure distributions in flow of the inlet are obtai... |
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| Keywords: | hypersonic inlet design method rectangular section experimental verification |
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