Hypersonic boundary layer (BL) transition generates a significant increase in viscous drag and heat flux, which leads to severe restrictions on the performance and thermal protection systems of hypersonic vehicles. Among various passive/active transition control strategies, acoustic metasurfaces demonstrate minimal effects on the mean flow but significantly suppress the Mack second mode. Therefore, it can be considered one of the most promising transition control technologies. Acoustic metasurfaces are planar metamaterial structures that comprise monolayer or multilayer stacks of subwavelength microstructures, which affect unstable modes via acoustic wave manipulations. This paper presents a review of the research progress made on acoustic metasurfaces for hypersonic BL stabilization over the past two decades. Acoustic characteristics and their corresponding stabilization effects on the first and second modes are compared and discussed. Recent improvements in the mathematical modeling of acoustic metasurfaces have been highlighted. An outline of the theoretical, numerical, and experimental investigations is then provided. Finally, a future research potential, especially for broadband design strategies and full direct numerical simulations, is prospected.

高超声速边界层 (BL) 过渡会显着增加粘性阻力和热通量，从而严重限制高超声速飞行器的性能和热保护系统。在各种被动/主动过渡控制策略中，声超表面对平均流量的影响最小，但显着抑制了麦克第二模式。因此，它可以被认为是最有前途的过渡控制技术之一。声学超表面是平面超材料结构，包括亚波长微结构的单层或多层堆叠，通过声波操作影响不稳定模式。本文回顾了过去 20 年在声学超表面用于高超声速 BL 稳定的研究进展。对第一和​​第二模式的声学特性及其相应的稳定效果进行了比较和讨论。最近在声学超表面的数学建模方面的改进已经得到强调。然后提供了理论、数值和实验研究的大纲。最后，展望了未来的研究潜力，特别是宽带设计策略和全直接数值模拟。