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Numerical and experimental investigation into hypersonic boundary layer transition induced by roughness elements

查看全文 作　　者：Hao [1]DONG;Shicheng [1]LIU;Xi [1]GENG;Song [1]LIU;Liming [2]YANG;Keming [1]CHENG 高影响力作者 机构地区：[1]Department of Aerodynamics, Nanjing University of Aeronautics and Aeronautics;[2]Department of Mechanical Engineering, National University of Singapore高影响力机构 出　　处：《Chinese Journal of Aeronautics》索引2019年第32卷第3期,共9页高影响力期刊 基　　金：the China Scholarship Council(CSC);the Aeronautics Science Foundation of China(No.20163252037);the China Postdoctoral Science Foundation(No.2017M610325);the Natural Science Foundation of Jiangsu Province of China(No.BK20170771);the Fundamental Research Funds for the Central Universities of China(No.NP2017202)for their support 摘　　要：In this work, the Direct Numerical Simulation(DNS) and Oil-Film Interferometry(OFI)technique are used to investigate the hypersonic boundary layer transition induced by single and double roughness elements at Mach number 5. For single roughness, the DNS results showed that both horseshoe vortices and hairpin vortices caused by shear layer instability can affect the boundary layer instability. The generation of the near-wall unstable structure is the key point of boundary layer transition behind the roughness element. At the downstream of the roughness element, the interaction between horseshoe vortices and hairpin vortices will spread in the spanwise direction.For double roughness elements, the effect of the spacing between roughness elements on the transition is studied. It is found that the case of higher spacing between roughness elements is more effective for inducing transition than the lower one. The interaction between two adjacent roughness elements can suppress the evolution of horseshoe vortices in the downstream and trigger the instability of shear layer. Thus, the transition will be suppressed accordingly. 关 键 词：Boundary layer transition HYPERSONIC Direct NUMERICAL simulation (DNS) Oil-film INTERFEROMETRY ROUGHNESS elements
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