高超声速高焓风洞试验技术研究进展
Progresses on experimental techniques of hypersonic and high-enthalpy wind tunnels
查看参考文献45篇
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文摘
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高焓风洞及其试验技术是助力人类进入高超声速飞行时代的基石,近年来取得了长足的进展。本文首先重点介绍了四种典型驱动模式的高焓风洞,即直接加热型高超声速风洞、加热轻气体驱动激波风洞、自由活塞驱动激波风洞和爆轰驱动激波风洞。通过这些代表性风洞的介绍,讨论了相关风洞的理论基础和关键技术及其长处与不足。由于高超声速高焓流动具高温热化学反应特征,风洞试验技术研究还包含着针对高焓特色的测量技术发展。本文介绍了三种主要测量技术:气动热测量技术、气动天平技术和光学测量技术。这些技术是依据常规风洞试验测量需求而研制的,又根据高焓风洞的特点得到了进一步的改进和完善。最后对高超声速高焓风洞试验技术发展做了简单展望。 |
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其他语种文摘
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The development of high enthalpy wind tunnel and its test technology are the cornerstone to help mankind enter the hypersonic era,and the great progress has been achieved in recent years.High enthalpy wind tunnels with four typical driving modes are introduced.Those are the air-directly-heated hypersonic wind tunnel,the light-gas-heated shock tunnel,the freepiston- driven shock tunnel,and the detonation-driven shock tunnel.Theories and critical techniques for developing these wind tunnels are introduced,and their merits and weakness are discussed based on tunnel performance evaluation.The measurement techniques are usually included into wind tunnel techniques because that the hypersonic and high-enthalpy flow is a chemically-reacting gas motion and its diagnose needs specially-designed instruments.Three measuring techniques are introduced here,including aerodynamic heat flux sensors,aerodynamic balances,and optical diagnose techniques.These techniques were usually developed for conventional hypersonic wind tunnels and combustion research,and are further improved to measure the hypersonic and high-enthalpy flows.The prospect for developing the experimental techniques of hypersonic and high-enthalpy wind tunnels is presented from author’s point view. |
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来源
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空气动力学学报
,2019,37(3):347-355 【核心库】
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DOI
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10.7638/kqdlxxb-2019.0009
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关键词
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高焓流动
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激波风洞
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高超声速飞行器
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气动力/热特性
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测量技术
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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宇航工程科学系, 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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综述型 |
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ISSN
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0258-1825 |
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学科
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航空 |
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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:6540685
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