Surface Tuft Flow Visualization in Hypersonic Inward Turning Inlet

Journal of Propulsion Technology ›› 2017, Vol. 38 ›› Issue (7): 1475-1482.

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Surface Tuft Flow Visualization in Hypersonic Inward Turning Inlet

Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Air-Breathing Hypersonic Technique Research Center of China Aerodynamics Research and Development Center，Mianyang 621000，China,Air-Breathing Hypersonic Technique Research Center of China Aerodynamics Research and Development Center，Mianyang 621000，China and Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China

Published:2021-08-15

高超声速内转式进气道流动的壁面丝线显示

李祝飞¹,黄蓉¹,郭帅涛¹,詹东文¹,刘坤伟¹,吴颖川²,余安远²,杨基明¹

中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国空气动力研究与发展中心吸气式高超声速技术研究中心，四川绵阳 621000,中国空气动力研究与发展中心吸气式高超声速技术研究中心，四川绵阳 621000,中国科学技术大学近代力学系，安徽合肥 230027

作者简介:李祝飞，男，博士后，研究领域为高超声速进气道。
基金资助:
国家自然科学基金(11402263；11132010)；中国博士后科学基金(2014M551818)。

Abstract

Abstract: Due to the difficulty in observing the internal flow of a hypersonic inward-turning inlet in wind tunnels，the flow structure of the three-dimensional shock wave/boundary layer interactions in such an inward-turning inlet cannot be obtained easily. The surface tuft flow visualization technique was extended，and then applied in a shock tunnel with a freestream Mach number of 5.9 to obtain the flow structure in an inward-turning inlet. With the help of a high-speed camera to monitor flow patterns of the surface tuft in real time，Schlieren associated with surface pressure measurement and analysis of numerical simulations and the dynamic response characteristics of the tuft was confirmed. The surface tuft flow visualization technique enriches the observation methods of the inward-turning inlet. To detect the inlet self-starting ability in the shock tunnel，a testing method of pre-setting a blockage in the inlet was used. The results indicate that the tuft of 402 polyester cotton sewing thread with a diameter of approximately 0.1mm and a length of approximately 15mm has fast?tracking ability?to intuitively and dynamically display the flow separation region on the inlet wall，which is proof of its good ability to indicate the start/unstart of the inward-turning inlet. The inward-turning inlet model is able to self-start at the test flow conditions. When the inlet is started，the shock structure near the cowl，the surface tuft flow patterns and the pressure distribution on the forebody agree well with the numerical simulations.

Key words: Inward turning inlet；Numerical simulation；Shock tunnel experiment；Surface tuft flow visualization；Self-starting

摘要： 针对风洞实验观测高超声速内转式进气道内部流动困难，不易获得内流道三维激波/边界层干扰主导的复杂流场结构的问题，通过拓展壁面丝线流动显示技术的潜力，在[Ma∞5.9]激波风洞中，借助高速摄影实时拍摄丝线流谱，并结合纹影、壁面压强测量以及数值模拟分析，验证了丝线的动态响应特性，丰富了内转式进气道的观测技术，获得了进气道的流场结构。采用预设堵块实验方法，在激波风洞中考核了内转式进气道模型的自起动能力。结果表明，直径约为0.1 mm，长度约为15 mm的402号涤纶/棉缝纫线的跟随性较好，能够直观、动态地显示出壁面流动分离区的范围，为判断内转式进气道是否起动提供了依据。内转式进气道模型在实验条件下能够自起动，起动状态下进气道唇口附近的波系结构以及前体压缩面的丝线流谱和压力分布与数值模拟符合较好。

关键词: 内转式进气道；数值模拟；激波风洞实验；壁面丝线流动显示；自起动

LI Zhu-fei¹,HUANG Rong¹,GUO Shuai-tao¹,ZHAN Dong-wen¹,LIU Kun-wei¹,WU Ying-chuan²,YU An-yuan²,YANG Ji-ming¹. Surface Tuft Flow Visualization in Hypersonic Inward Turning Inlet[J]. Journal of Propulsion Technology, 2017, 38(7): 1475-1482.

李祝飞,黄蓉,郭帅涛,詹东文,刘坤伟,吴颖川,余安远,杨基明. 高超声速内转式进气道流动的壁面丝线显示[J]. 推进技术, 2017, 38(7): 1475-1482.

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Surface Tuft Flow Visualization in Hypersonic Inward Turning Inlet

高超声速内转式进气道流动的壁面丝线显示

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