Parametric study of multiple shock-wave/turbulent-boundary-layer interactions with a Reynolds stress model

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