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Flow structures and unsteadiness in hypersonic shock wave/turbulent boundary layer interaction subject to steady jet

基于稳态射流控制的高超声速激波/湍流边界层干扰流动结构与非 定常性研究

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Abstract

Direct numerical simulations of Mach 6 hypersonic flow over a 34° compression corner subject to steady jet are conducted. Distributions of skin friction coefficient, wall pressure, mean velocity and temperature, boundary layer thickness and Stanton number demonstrate that the flow changes dramatically in the shock wave/turbulent boundary layer interaction area. It is found that the steady jet has no effect on suppressing flow separation unexpectedly, but increases its spatial scale instead. Instantaneous flow structures show that the turbulence amplification can be observed after the application of flow control, and abundant Gortler-like vorticities appear, but the strength of the main shock decreases. Analyzing the wall fluctuating pressure signals using weighted power spectral density, we found an interesting thing. That is, although the low-frequency oscillation phenomenon induced by separation shock is suppressed by the steady jet, wall fluctuating pressure beneath the jet shock is oscillating at a frequency lower than 0.1u∞/δref. Results of coherent and intermittency factor reveal that it is related to the backand- forth movement of the jet shock itself.

摘要

对稳态射流作用下马赫6高超声速压缩拐角激波/湍流边界层干扰流动开展了直接数值模拟研究. 表面摩阻系数、壁面压力、 平均速度和温度、边界层厚度和斯坦顿数的分布等结果表明, 激波/湍流边界层相互作用区的流动发生了显著变化. 研究发现, 垂直壁 面的稳定射流对抑制流动分离没有任何作用, 反而增加了其空间尺度. 瞬时流动结构表明, 在施加流动控制后, 可以观察到湍流增强效 应, 并出现大量的类Görtler涡结构, 但主激波强度降低. 使用加权功率谱密度分析壁面脉动压力信号, 我们发现了一件有趣的事情: 尽管 稳定射流抑制了分离激波引起的低频振荡现象, 但射流激波附近的壁面脉动压力以低于0.1u∞/δref的频率振荡. 相干性和间歇性因子的 结果表明, 这与射流激波本身的往复运动有关.

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Acknowledgements

This work was supported by the National Natural Science Foundation of China (Grant Nos. 12202488 and 12002377), the Natural Science Program of National University of Defense Technology (Grant No. ZK22-30), and Independent Cultivation Project for Young Talents in College of Aerospace Science and Engineering. Supercomputer time provided by the National Supercomputing Center in Beijing is also gratefully acknowledged.

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Authors and Affiliations

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, 410073, China

    Qiang Liu  (刘强), Wei Xie  (谢玮), Zhenbing Luo  (罗振兵), Mingbo Sun  (孙明波), Pan Cheng  (程盼), Xiong Deng  (邓雄) & Yan Zhou  (周岩)

  2. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, 410073, China

    Mingbo Sun  (孙明波)

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  1. Qiang Liu  (刘强)
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  2. Wei Xie  (谢玮)
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  3. Zhenbing Luo  (罗振兵)
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  5. Pan Cheng  (程盼)
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  6. Xiong Deng  (邓雄)
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  7. Yan Zhou  (周岩)
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Contributions

Qiang Liu: Data curation, Formal analysis, Funding acquisition, Investigation, Resources, Methodology, Visualization, Writing — original draft. Wei Xie: Data curation, Visualization, Validation, Methodology. Zhenbing Luo: Conceptualization, Writing — review & editing, Resources. Mingbo Sun: Writing — review & editing, Resources, Software. Pan Cheng: Project administration, Writing — review & editing. Xiong Deng: Writing — review & editing, Resources, Methodology. Yan Zhou: Writing — review & editing, Funding acquisition.

Corresponding author

Correspondence to Zhenbing Luo  (罗振兵).

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Liu, Q., Xie, W., Luo, Z. et al. Flow structures and unsteadiness in hypersonic shock wave/turbulent boundary layer interaction subject to steady jet. Acta Mech. Sin. 39, 123202 (2023). https://doi.org/10.1007/s10409-023-23202-x

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