The flow of high-speed air in ducts may result in the occurrence of multiple shock-wave/boundary-layer interactions. Understanding the consequences of such interactions, which may include distortion of the velocity field, enhanced turbulence production, and flow separation, is of great importance in understanding the operating limits and performance of a number of systems, for example, the high-speed intake of an air-breathing missile. In this paper, the results of a computational study of multiple shock-wave/boundary-layer interactions occurring within a high-speed intake are presented. All of the results were obtained using the in-house computational fluid dynamics solver of Glasgow University, HMB3. First simulations of a Mach \(M=1.61\) multiple shock-wave/boundary-layer interaction in a rectangular duct were performed. The \(M=1.61\) case, for which experimental data is available, was used to establish a robust numerical approach, particularly with respect to initial and boundary conditions. A number of turbulence modelling strategies were also investigated. The results suggest that Reynolds-stress-based turbulence models are better suited than linear eddy-viscosity models. This is attributed to better handling of complex strain, in particular modelling of the corner separation. The corner separations affect the separation at the centre of the domain which in turn alters the structure of the initial shock and the subsequent interaction. Having established a robust numerical approach, the results of a parametric study investigating the effect of Mach number, Reynolds number, and confinement on the baseline solution are then presented. Performance metrics are defined to help characterize the effect of the interactions. The results suggest that reduced flow confinement is beneficial for higher-pressure recovery.

管道中的高速空气流动可能导致发生多个冲击波/边界层相互作用。了解此类相互作用的后果（包括速度场失真，湍流产生增强和流动分离），对于理解许多系统的运行极限和性能（例如，高速进气系统）非常重要。呼吸空气的导弹。在本文中，给出了高速进气中发生的多个冲击波/边界层相互作用的计算研究结果。所有结果均使用格拉斯哥大学内部计算流体动力学求解器HMB3获得。马赫\（M = 1.61 \）的首次模拟在矩形管道中进行了多次冲击波/边界层相互作用。的\（M = 1.61 \）可以利用实验数据的案例来建立鲁棒的数值方法，尤其是在初始条件和边界条件方面。还研究了许多湍流建模策略。结果表明，基于雷诺应力的湍流模型比线性涡流-粘度模型更适合。这归因于对复杂应变的更好处理，尤其是转角分离的建模。拐角间隔会影响磁畴中心的间隔，进而改变初始冲击和后续相互作用的结构。建立了稳健的数值方法后，将提供调查马赫数，雷诺数和约束对基线解的影响的参数研究结果。定义了性能指标以帮助表征交互作用的效果。结果表明，减少流量限制有利于高压回收。