刘向宏, 赖光伟, 吴杰. 高超声速边界层转捩实验综述[J]. 空气动力学学报, 2018, 36(2): 196-212. DOI: 10.7638/kqdlxxb-2018.0017
引用本文: 刘向宏, 赖光伟, 吴杰. 高超声速边界层转捩实验综述[J]. 空气动力学学报, 2018, 36(2): 196-212. DOI: 10.7638/kqdlxxb-2018.0017
LIU Xianghong, LAI Guangwei, WU Jie. Boundary-layer transition experiments in hypersonic flow[J]. ACTA AERODYNAMICA SINICA, 2018, 36(2): 196-212. DOI: 10.7638/kqdlxxb-2018.0017
Citation: LIU Xianghong, LAI Guangwei, WU Jie. Boundary-layer transition experiments in hypersonic flow[J]. ACTA AERODYNAMICA SINICA, 2018, 36(2): 196-212. DOI: 10.7638/kqdlxxb-2018.0017

高超声速边界层转捩实验综述

Boundary-layer transition experiments in hypersonic flow

  • 摘要: 高超声速边界层转捩直接影响飞行器表面的摩擦系数与热流分布,对于高超声速飞行器的气动布局以及热防护设计至关重要。尽管高超声速边界层层/湍流转捩的相关研究已经开展长达半个多世纪,但是由于高超声速流动的复杂性以及触发转捩的因素繁多,研究人员对于转捩过程的认识并不透彻,阻碍了先进高超声速飞行器的设计。地面风洞实验作为高超声速空气动力学设计的重要手段之一,在可预见的将来仍是研究高超声速边界层转捩不可或缺的方法。本文以高超声速边界层稳定性与转捩的风洞实验为重点,按照边界层自然转捩的发展过程,分别回顾了国内外在边界层感受性问题以及线性化阶段风洞实验研究的现状,文章最后总结了风洞实验在未来高超声速边界层转捩研究中的工作与意义,并针对未来的实验研究给出了几点建议。

     

    Abstract: Laminar/turbulent boundary-layer transition has a large impact on the viscous coefficient and the heat flux, which are critical for aerodynamic and thermal protection design of hypersonic vehicles. Due to the complexity of hypersonic flow and the numerous factors affecting transition, the mechanism of hypersonic laminar/turbulent boundary-layer transition is still outstanding despite the research upon this issue has been lasting for more than half a century, prohibiting the design of advanced hypersonic vehicles. Ground wind tunnel experiment acts as a significant approach in hypersonic aerodynamic design and is expected to play an important role in the research of hypersonic boundary-layer transition in the future. Based on the hypersonic boundary-layer instability and transition experiments in wind tunnel, the receptivity and linear phases were respectively reviewed according the process of natural transition. Discussions and suggestions were given for experimental study of hypersonic boundary-layer transition.

     

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