Flow patterns of dual-incident shock waves/turbulent boundary layer interaction
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SHORT P APER
Xin Li • Hui-jun Tan
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Yue Zhang • He-xia Huang • Yun-jie Guo • Zheng-kang Lin
Flow patterns of dual-incident shock waves/turbulent boundary layer interaction
Received: 9 December 2019 / Revised: 22 June 2020 / Accepted: 23 June 2020 Ó The Visualization Society of Japan 2020
Abstract The ice-cluster-based planar laser scattering technique, a high spatiotemporal resolution technique, is used to obtain the fine structures of dual-incident shock waves/turbulent boundary layer interaction. A double wedge produces these two incident shock waves. Three different interval distances between the incident shock waves are examined to obtain the influence of the second shock wave on the entire flow-field configuration. The overall flow pattern of dual-incident shock wave/turbulent boundary layer interaction flow is shown dominated by a quasi-triangular separation when the two shock waves intersect at the wall. As the interval distance increases, a trapezoid separation appears and finally no apparent flow separation occurs in the turbulent boundary layer. Keywords Dual-incident shock waves Turbulent boundary layer Interaction Flow separation
1 Introduction Shock wave/turbulent boundary layer interactions (SWTBLI) are frequently encountered in many internal and external compressible flows of supersonic and hypersonic air vehicles. The shock wave imposes an adverse pressure gradient on the boundary layer, causing the latter unsteady and even separated. As a classical and complex aerodynamic problem, SWTBLI can take on a variety of different forms, depending on the shock wave type, the application geometry and the flow conditions. In general, four types of these interactions, namely, incident shock wave/turbulent boundary layer interaction (ISWTBLI), compressible ramp shock wave/turbulent boundary layer interaction (CRSWTBLI), normal shock wave boundary/turbulent boundary layer interaction (NSWTBLI) and swept shock wave /turbulent boundary layer interaction (SSWTBLI), have attracted an abundance of theoretical, numerical and experimental investigations in the past decades (Babinsky and Harvey 2011). In the intake system of supersonic and hypersonic vehicles, multi-stage compression by shock waves is often utilized to achieve high-pressure ratio, which causes multishock waves/boundary layer interaction (MSWTBLI). For example, in supersonic inlet/isolator models, the cowl shock wave and the downstream contour-induced shock waves interact with the boundary layer near the ramp-side wall in sequence (Tan et al. 2012; Huang et al. 2017), which might induce a strong coupling effect and lead to a large-scale separation of the turbulent boundary layer. Obviously, MSWTBLI presents more complex characteristics than the widely considered SWTBLI caused by a single shock wave. However, few research interests have been focused on MSWTBLI in previous works. Considering that the single ISWTBLI is a classical interaction-type received extensive attention (Green 1970; Delery et al. 1986; Dupont et al. 2006; Pirozzoli and Gr
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