Full Text:   <191>

Summary:  <76>

CLC number: V211.48

On-line Access: 2020-06-11

Received: 2020-01-17

Revision Accepted: 2020-06-05

Crosschecked: 2020-08-28

Cited: 0

Clicked: 257

Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Hao Jiang

https://orcid.org/0000-0001-7251-7875

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Journal of Zhejiang University SCIENCE A 2020 Vol.21 No.9 P.745-760

http://doi.org/10.1631/jzus.A2000025


Hypersonic flow control of shock wave/turbulent boundary layer interactions using magnetohydrodynamic plasma actuators


Author(s):  Hao Jiang, Jun Liu, Shi-chao Luo, Jun-yuan Wang, Wei Huang

Affiliation(s):  Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   jiangjeb@163.com

Key Words:  Hypersonic, Shock wave/turbulent boundary layer interaction, Magnetohydrodynamic (MHD), Flow control


Hao Jiang, Jun Liu, Shi-chao Luo, Jun-yuan Wang, Wei Huang. Hypersonic flow control of shock wave/turbulent boundary layer interactions using magnetohydrodynamic plasma actuators[J]. Journal of Zhejiang University Science A, 2020, 21(9): 745-760.

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%A Shi-chao Luo
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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.

高超声速激波/湍流边界层干扰电磁控制研究

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.

关键词:高超声速; 激波/湍流边界层干扰; 磁流体; 流动控制

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

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