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http://dx.doi.org/10.6108/KSPE.2021.25.6.036

Numerical Study of Shock Wave-Boundary Layer Interaction in a Curved Flow Path  

Kim, Jae-Eun (Department of Aerospace Engineering, Pusan National University)
Jeong, Seung-Min (Department of Aerospace Engineering, Pusan National University)
Choi, Jeong-Yeol (Department of Aerospace Engineering, Pusan National University)
Hwang, Yoojun (Agency for Defense Development)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.25, no.6, 2021 , pp. 36-44 More about this Journal
Abstract
Numerical analysis was performed on the shock wave-boundary layer interaction generated in the internal flow path of the curved interstage of the scramjet engine flight test vehicle. For numerical analysis, the turbulence model k-ω SST was used in the compressibility Raynolds Averaged Navier Stokes(RANS) equation. Representatively, the separation bubbles on the upper wall of the nozzle, the interaction between the concave shock wave and the boundary layer, and the shock wave-shock wave interaction at the edge were captured. The analysis result visualizes the shock wave-boundary layer interaction of the curved internal flow path to enhance understanding and suggest design considerations.
Keywords
Scramjet Engine; Hypersonic Flight Test Vehicle; Supersonic Internal Flow; Shock Wave-Boundary Layer Interaction (SBLI);
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