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Large-eddy simulation of shock-wave/turbulent boundary-layer interactions and its control using Sparkjet

机译：冲击波/湍流边界层相互作用的大涡模拟及其Sparkjet控制

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摘要

Large-eddy simulations (LES) of the oblique impinging shock-wave/flat plate boundary layer interactions at Mach=2.3 and Reδ=20000 were carried out to investigate the underlying flow physics associated with flow separation and shock unsteadiness. The digital filter method was used to generate synthetic inflow turbulence without introducing any artificial low-frequency motions. The LES results were firstly well validated by comparing with the corresponding measurement data. The low-frequency characteristic of separation shock-wave was then studied by analyzing the obtained time sequence of the wall static pressure signals to realize its amplitudes, frequencies and wave-lengths. Finally, the study was extended by integrating with a control module of an active actuator “SparkJet” concept, in order to investigate its influences on the flow separation and the low-frequency motion of shock-wave unsteadiness. The analysis of flow topology and flow structure around separation region reveals that the actuator acts as a fluidic-like vortex generator, promotes the mixing process within the boundary layer, and thus largely elevates the near-wall turbulence kinetic energy level, leading to its enhanced ability to resist the flow separation. Details of the study will be presented in the final full paper.
机译：对斜撞击冲击波/平板边界层在Mach = 2.3和Reδ= 20000时的大涡模拟（LES）进行了研究，以研究与流分离和激波不稳定相关的潜在流物理学。数字滤波方法用于生成合成的入流湍流，而不会引入任何人工的低频运动。通过与相应的测量数据进行比较，首先对LES结果进行了很好的验证。然后，通过分析所获得的壁静压力信号的时序，研究分离冲击波的低频特性，以实现其振幅，频率和波长。最后，通过与主动执行器“ SparkJet”概念的控制模块集成来扩大研究范围，以研究其对流动分离和冲击波不稳定的低频运动的影响。对分离区域周围的流动拓扑和流动结构的分析表明，该致动器起着类似于流体的涡旋发生器的作用，促进了边界层内的混合过程，从而大大提高了近壁湍流的动能水平，从而使其增强。抵抗流分离的能力。该研究的详细信息将在最终论文全文中介绍。

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