高超声速下表面凸起干扰气动热实验研究

流体力学与飞行力学

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高超声速下表面凸起干扰气动热实验研究

ESTRUCH-SAMPER David¹, 卜雪琴^2,3

1. Department of Aeronautics, Imperial College London, London SW7;
2. AZ 2. 北京航空航天大学航空科学与工程学院, 北京 100191;
3. 北京航空航天大学人机工效与环境控制重点学科实验室, 北京 100191

收稿日期:2011-11-07 修回日期:2011-12-05 出版日期:2012-09-25 发布日期:2012-09-22
通讯作者: 卜雪琴 E-mail:buxueqin@buaa.edu.cn

Experimental Investigation on Hypersonic Interference Heating Around Surface Protuberance

ESTRUCH-SAMPER David¹, BU Xueqin^2,3

1. Department of Aeronautics, Imperial College London, London SW7;
2. AZ, UK 2.School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;
3. Fandamental Science on Ergonomics and Environment Control Laboratory, Beihang University, Beijing 100191, China

Received:2011-11-07 Revised:2011-12-05 Online:2012-09-25 Published:2012-09-22

摘要/Abstract

摘要： 对高超声速飞行器表面凸起附近的气流流动和气动加热开展了实验研究和分析。实验在高超声速炮风洞中进行,来流马赫数为8.2、单位雷诺数为9.35×10⁶ m^-1。利用薄膜传热测量方法进行了凸起几何形状和边界层状态对干扰流动加热的影响评估。利用流油图谱和纹影摄像法得到了凸起周围的流动特征:若凸起上游边界层未分离,最大峰值热流发生在凸起侧方附近处;若凸起上游边界层完全分离,最大峰值热流通常发生在凸起的上游表面。实验发现最大峰值热流和来流边界层状态关系不大,原因是流动干扰区表现出较强的三维扰动特性,使得来流层流边界层在干扰区内会转变成过渡甚至完全湍流状态。

关键词: 高超声速, 表面凸起, 干扰加热, 实验, 最大峰值热流

Abstract: A study is performed to understand the details of the flow and heating characteristics around surface protuberances on hypersonic bodies. Experiments are conducted in a hypersonic gun tunnel at a freestream Mach number of 8.2 and Reynolds number of 9.35?10⁶ m^-1. The thin-film heat transfer measurements are used to assess the effects of the protuberance geometry and boundary layer state on surface heating. Oil-dot visualizations and high-speed schlieren videos are additionally used to qualitatively understand the flowfield around the protuberances. The highest heating is found to the side of the protuberance in interactions in which the incoming boundary layer remains unseparated upstream of the protuberance. In fully separated interactions, the highest heating generally takes place ahead of the protuberance and can become significantly high. The dependence of the maximum heating on the incoming boundary layer state is negligible. This is believed to be caused by the 3-dimensinality of the interactions which causes the incoming laminar boundary layer to become transitional or even fully turbulent.

Key words: hypersonic, surface protuberance, interaction heating, experiments, peak heat flux

中图分类号:

V211.7

ESTRUCH-SAMPER David, 卜雪琴. 高超声速下表面凸起干扰气动热实验研究[J]. 航空学报, 2012, 33(9): 1578.

ESTRUCH-SAMPER David, BU Xueqin. Experimental Investigation on Hypersonic Interference Heating Around Surface Protuberance[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(9): 1578.

参考文献

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E-mail：hkxb@buaa.edu.cn

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高超声速下表面凸起干扰气动热实验研究

Experimental Investigation on Hypersonic Interference Heating Around Surface Protuberance

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