基于鼓包的激波/边界层干扰控制研究进展

doi:10.7527/S1000-6893.2023.28411

Abstract

Abstract:

The flow control of hypersonic vehicles faces complex shock wave/boundary layer interaction problems， and effective shock wave/boundary layer interaction control technologies have become a research hotspot. This paper reviews the research progress of passive control of shock wave/boundary layer interaction based on bumps. The main flow characteristics of shock wave/boundary layer interaction are introduced， and the research progress of shock wave/boundary layer interaction is summarized. The mechanism and research progress of shock wave control bumps for drag reduction of transonic wings in the external flow field， and wall bumps for supersonic and hypersonic flow control in the internal flow field are reviewed. The flow control performance of bumps is analyzed and its development prospected.

Key words: shock wave/boundary layer interaction, flow separation, flow control, bump, passive control

CLC Number:

V211.3

Shanshan TIAN, Liang JIN, Zhaobo DU, Xiangyu ZHONG, Wei HUANG, Yuanyang LIU. Research progress of shock wave/boundary layer interaction controls induced by bump[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(18): 28411-028411.

Figures/Tables 33

Table 1

Shock wave/boundary layer interaction control methods and corresponding mechanisms

激波/边界层干扰控制方法		流动控制机理
被动控制方法	壁面鼓包^［6-9］	壁面外凸形变，模仿分离流结构，置换或排移低能流边界层，减小激波入射点附近的逆压梯度并将强激波分为若干道弱激波结构，近似实现等熵压缩，大幅减少波阻
	微型涡流发生器^［10-13］	引入流向涡，向边界层内输运高动量流体，增强边界层展向涡和脉动涡，增加边界层对分离的抵抗能力
	后向台阶^［14-16］	来流经过后向台阶在台阶角处出现一个膨胀扇，膨胀扇与激波相互作用减弱激波引起的逆压梯度
	边界层抽吸^［17-18］	壁面抽吸元将近壁面的低动量流体吸除，降低边界层厚度，增加壁面附近流动的动量
	次流循环^［19-22］	在分离区的高压区及前部的低压区下方开孔设置循环管道，利用压力差形成次流循环，形成边界层抽吸及吹除组合，减小分离泡的尺寸，抑制边界层分离的产生
	无源凹腔^［23-24］	凹槽形成自然的回流区，使高压流体通过空腔向低压区再循环，同时拆分激波系，减少激波系损失，达到降低激波阻力及减弱边界层增长的目的
主动控制方法	吹除控制^［25-26］	在激波的起始点或者入射点的上游，通过缝隙往边界层内切向注入流体，为边界层中被阻滞的流体质点提供能量
	射流控制^［27-33］	通过射流与来流耦合形成正、反向旋转涡对，将高能流注入到边界层内，减弱分离激波强度，增强边界层抵抗逆压梯度的能力
	等离子体控制^［34-39］	通过激励器的放电实现空气电离和能量注入，增强气体的动量，改变流场特征
	磁流体MHD控制^［40-42］	通过在电场产生等离子体的作用上叠加洛伦兹力，增加上游边界层的能量，抑制分离

Table 1

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Research progress of shock wave/boundary layer interaction controls induced by bump

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