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• W4379644256 abstract "Shock-wave/boundary-layer interactions (SWBLI) strongly influence the aerodynamic behaviour of many aerospace, propulsion and transportation systems. They have therefore been studied intensively — with different methods, configurations, and test facilities. Regions of favourable pressure gradient are often placed downstream of the SWBLI region., e.g. to prevent wind-tunnel blockage. To be able to better understand their effect and compare cases from varying sources, a joint experimental–numerical study of a supersonic compression/expansion corner flow is carried out. A high-resolution long-time numerical simulation complements particle-image velocimetry measurements, both using the same configuration and conditions. Derived setups without the downstream expansion corner are also explored; both for the same compression-corner angle and for a ramp angle inducing a separation bubble of the same size as for the original compression/expansion configuration. Results demonstrate that the topology and very low-frequency dynamics of the separation bubble developing over the compression corner are altered by the downstream expansion corner. Differences are mainly found for the downstream motion of the shock/shrinking of the separated region and extend downstream of the reattachment point up to the expansion corner." @default.
• W4379644256 created "2023-06-08" @default.
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• W4379644256 date "2023-08-01" @default.
• W4379644256 modified "2023-09-25" @default.
• W4379644256 title "Effects of favourable downstream pressure gradients on separated shock-wave/boundary-layer interactions" @default.
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• W4379644256 doi "https://doi.org/10.1016/j.ijheatfluidflow.2023.109164" @default.
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