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Direct numerical simulations of supersonic turbulent boundary layer with streamwise-striped wall blowing

机译：具有流地性条纹壁吹塑超声波湍流边界层的直接数值模拟

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摘要

Direct numerical simulations of a spatially developing Ma 2.25 supersonic turbulent boundary layer with streamwise-striped wall blowing (SSB) are performed for the purpose of turbulence drag reduction. The SSB is designed to blow through long and straight slots in the flow direction. The slots are equally distributed in spanwise direction, with different stripe spacing and width. Blowing amplitudes of 0.1% and 0.2% are investigated. For comparison, uniform blowing (UB) of 0.1% is also simulated. It is found that in spite of weak control amplitudes, 7.4% and 14.5% drag reduction can be achieved in the case of 6SSB 0.1% and 6SSB 0.2%, respectively. Similar to UB, the boundary layer displacement thickness is thickened by SSB, with a thicker viscous sub-layer and a logarithmic zone which moving away from the wall. Turbulence intensities and turbulent coherent structures are enhanced, although the streamwise scales of the latter are attenuated. Turbulent kinetic energy analysis presents that both the production and dissipation are increased in the near wall. Compressible Renard-Deck decomposition of C-f shows that it is the spatially growth term that mainly responsible for the turbulence drag reduction. (c) 2021 Elsevier Masson SAS. All rights reserved.
机译：用于具有流动条纹壁吹塑（SSB）的空间显影MA 2.25超声波湍流边界层的直接数值模拟。 SSB设计用于在流动方向上吹过长轴和直的槽。槽均在翼展方向上均匀分布，具有不同的条纹间距和宽度。研究了0.1％和0.2％的吹出幅度。为了进行比较，还模拟了0.1％的均匀吹塑（UB）。发现，尽管对照幅度较弱，但在6SSB 0.1％和6SSB 0.2％的情况下，可以实现7.4％和14.5％的阻力。与UB类似，边界层位移厚度由SSB加厚，具有较厚的粘性子层和远离壁的对数区。湍流强度和湍流相干结构得到增强，尽管后者的流动尺度衰减。湍流动能分析表明，近墙上的生产和耗散增加。 C-F的可压缩雷纳德 - 甲板分解表明，它是主要负责湍流减阻的空间生长项。 （c）2021 Elsevier Masson SAS。版权所有。

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