Shock wave/turbulent boundary layer interactions are widely observed in supersonic flows with many adverse effects on the flow field, resulting in increasing investigation on their control. This paper optimizes the secondary recirculation configuration based on our previous investigations. Six secondary recirculation configurations are designed, and the adaptive control schemes for these configurations are developed for incoming Mach numbers equaling 2.5, 3.0, and 3.5. The three-dimensional implicit Reynolds-Averaged Navier–Stokes equations employing the two-equation shear stress transport k–ω turbulence model are used to perform simulation calculations for each case. An evaluation approach is developed for the control performance and utilized to perform quantitative calculations. The calculation results are used to analyze the control effects of the separation zone volume, total pressure recovery coefficient, and peak wall heat flux for different configurations to find the best control configuration with the widest operating Mach number range. Finally, a configuration with a grid pattern distribution of suction holes, each with a length and width of 2.828 mm uniformly distributed over 52 < x/D < 124 and −12 < z/D < 12, is obtained for the shock wave/turbulence boundary layer control studied in this study.
Optimization study on adaptive control performance of shock wave/boundary layer interactions with different secondary recirculation configurations
Note: This paper is part of the special topic, Hypersonic Flow.
Xiang-Yu Zhong, Wei Huang, Meng-Fei Cao, Han Wu, Lin Dai, Zhao-Bo Du; Optimization study on adaptive control performance of shock wave/boundary layer interactions with different secondary recirculation configurations. Physics of Fluids 1 April 2023; 35 (4): 045114. https://doi.org/10.1063/5.0142076
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