激波/边界层干扰及微型涡流发生器控制研究进展

doi:10.7527/S1000-6893.2021.25371

Abstract

Abstract: The shock wave/boundary layer interaction is a common phenomenon that occurs in supersonic/hypersonic flows, causing flow separation, flow field structure oscillation, local high heat flux and pressure load. This article mainly summarizes recent research advances on the shock wave/boundary layer interaction and its control induced by the micro vortex generator in the past decade. The micro vortex generator is currently the most studied and widely used control approach with its flow performance and control mechanism extensively explored. However, to adapt to the changes in incoming flow conditions and meet the needs of actual working conditions, quantitative evaluation and parametric design methods should be developed. Meanwhile, the combination of the micro vortex generator and other control methods should be considered to achieve flow field control with a larger degree and a wider range.

Key words: shock wave/boundary layer interaction, supersonic/hypersonic flow, flow separation, flow control, micro vortex generators

CLC Number:

V211.3

WU Han, WANG Jianhong, HUANG Wei, DU Zhaobo, YAN Li. Research progress on shock wave/boundary layer interactions and flow controls induced by micro vortex generators[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(6): 25371-025371.

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Research progress on shock wave/boundary layer interactions and flow controls induced by micro vortex generators

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