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Investigation and numerical simulation of shock-boundary layer interaction in supersonic flow and the effect of boundary layer suction on flow separation
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Mojtaba Zahedzadeh *   , Mehdi Hamzai |
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Abstract: (42 Views) |
Shock/boundary layer interactions still belong to the fundamental problems of modern aerothermodynamics and high-speed fluid dynamics, which to a large extent causes many problems, especially in flight technology and satellite flights. The flow characteristics of shock-boundary layer interactions are observed in many high-speed engineering devices such as gas turbine blades, aircraft wings, control surfaces, inlet systems for jet engines, ramjet engines, scramjets, etc. In the past, much work has been done to investigate the characteristics of shock-boundary layer interactions and various properties. Interesting results such as boundary layer thickening, boundary layer separation and reattachment, shock wave instability, etc. have been obtained. In the present work, the results of numerical simulation of the interaction between an oblique shock wave and a turbulent boundary layer formed in a supersonic flow (Mach number M = 5) of a flat plate are presented. The results of numerical simulations have been compared and validated with experimental data. Then, the effect of boundary layer suction on the flow separation region due to shock-boundary layer interaction has been investigated. |
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| Keywords: Shock-boundary layer interaction, flow separation, boundary layer suction, numerical simulation |
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Full-Text [PDF 1763 kb]
(11 Downloads)
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Type of Study: Research |
Subject:
Special
Received: 2025/06/3 | Accepted: 2025/08/30 | Published: 2025/09/1
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