Abstract
The effect of magnetohydrodynamic (MHD) plasma actuators on the control of hypersonic shock wave/turbulent boundary layer interactions is investigated here using Reynolds-averaged Navier-Stokes calculations with low magnetic Reynolds number approximation. A Mach 5 oblique shock/turbulent boundary layer interaction was adopted as the basic configuration in this numerical study in order to assess the effects of flow control using different combinations of magnetic field and plasma. Results show that just the thermal effect of plasma under experimental actuator parameters has no significant impact on the flow field and can therefore be neglected. On the basis of the relative position of control area and separation point, MHD control can be divided into four types and so effects and mechanisms might be different. Amongst these, D-type control leads to the largest reduction in separation length using magnetically-accelerated plasma inside an isobaric dead-air region. A novel parameter for predicting the shock wave/turbulent boundary layer interaction control based on Lorentz force acceleration is then proposed and the controllability of MHD plasma actuators under different MHD interaction parameters is studied. The results of this study will be insightful for the further design of MHD control in hypersonic vehicle inlets.
Abstract
目的
临近空间中下层巡航的新一代高超声速飞行器面 临着高马赫数激波/湍流边界层干扰的问题。本文 旨在探讨磁场/电弧放电耦合作用因素(焦耳热作 用、放电参数、磁场强度、电弧作用流向位置和 壁面距离等)对高马赫数工况下激波/湍流边界层 干扰控制的影响,并提出激波/湍流边界层干扰洛 伦兹力控制能力的参数表征,以揭示电磁控制的 原理和能力。
创新点
1. 建立低磁雷诺数假设下的激波/湍流边界层干扰 数值模拟方法,对高超声速激波/湍流边界层干扰 进行电磁控制,总结分析控制类型与控制机理, 并根据仿真结果提出最佳控制参数建议。 2. 建立针对激波/湍流边界层干扰的磁控能力预 测参数,以指导高超声速飞行器典型激波/湍流边 界层干扰的磁控设计。
方法
1. 建立低磁雷诺数假设下的激波/湍流边界层干扰 数值模拟方法,并分别对电磁力控制边界层、激 波/湍流边界层干扰和湍流边界层速度剖面进行 计算,验证使用方法的可靠性和有效性。2. 采用 相关实验的电磁激励器的半经验模型,对二维稳 态假设下的激波入射平板进行数值模拟,并研究 电磁输入参数对分离区大小的影响。3. 通过理论 分析,建立针对激波/湍流边界层干扰的磁控评价 参数,并通过不同磁控强度下的数值仿真进行验 证。
结论
1. 四种电磁控制类型的控制机理和控制效果不 同;电磁控制区位于分离泡内的等压区且距离壁 面越近对减弱激波/湍流边界层干扰分离的效果 越好。2. 电磁控制后等压区压力梯度与外加电磁 力处于同一量级且呈近似线性关系。3. 本文所提 出的磁控参数的物理意义更加明确,可进一步应 用于对不同工况下激波/湍流边界层干扰分离控 制的预测。
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Hao JIANG conducted the literature survey, wrote the first draft of the manuscript, and revised and edited the final version. Jun LIU put forward the original idea of the proposed classification framework and supervised the research activities. Shi-chao LUO and Jun-yuan WANG assisted with the literature survey, and document delivery and arrangement. Wei HUANG provided suggestions on the classification framework.
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Hao JIANG, Jun LIU, Shi-chao LUO, Jun-yuan WANG, and Wei HUANG declare that they have no conflict of interest.
Project supported by the National Key R&D Program of China (Nos. 2019YFA0405300 and 2019YFA0405203) and the Chinese Scholarship Council (CSC) (No. 201903170195)
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Jiang, H., Liu, J., Luo, Sc. et al. Hypersonic flow control of shock wave/turbulent boundary layer interactions using magnetohydrodynamic plasma actuators. J. Zhejiang Univ. Sci. A 21, 745–760 (2020). https://doi.org/10.1631/jzus.A2000025
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DOI: https://doi.org/10.1631/jzus.A2000025