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首页> 美国政府科技报告 >Investigation of Three-Dimensional Shock Wave Boundary Layer Interactions. A Flow-Field Model of the Glancing Shock/Turbulent Boundary Layer Interaction
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Investigation of Three-Dimensional Shock Wave Boundary Layer Interactions. A Flow-Field Model of the Glancing Shock/Turbulent Boundary Layer Interaction

机译：三维激波波边界层相互作用的研究。掠过冲击/湍流边界层相互作用的流场模型

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Three-dimensional glancing-shock/turbulent boundary-layer interaction has been investigated at the Cranfield Institute of Technology in two separate test programmes using a 2.5 x 2.5 inch intermittent tunnel and a 9 x 9 inch continuous tunnel, at a Mach number of approximately 2.5. The experimental results include oil-flow pictures, vapour-screen photographs, surface static pressure distributions, local heat transfers, liquid crystal pictures of surface temperature, and viscous layer surveys. The test data indicate that the interaction region consists of two different viscous flows, the side-wall boundary layer and an induced layer originating near the shock generator root and crossing the path of the side-wall boundary layer. In this flow field model, no flow separation appears as long as the surface stream lines of the side-wall boundary layer can be pliable enough to be bent along the edge of the induced layer, even when the surface-flow deflection exceeds the shock angle. However, an ordinary separation does take place when the induced layer forces the surface stream lines to deflect beyond a maximum permissible angle. (Author)

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