Hypersonic Flat Plate Boundary Layer Transition Experimental Studies Of Flow Visualization At Mach 6

With the development of hypersonic vehicle,hypersonic boundary layer transition has become a hot topic of the research,the development of the surface of hypersonic boundary layer and transition process occupies an important position in its aerodynamic design.It's have a important promoting for recognition,forecast and controls of hypersonic aerodynamic design high Mach number.Firstly,we had focus on hypersonic experimental study on smooth flat plate boundary layer flow using low-noise technology of hypersonic wind tunnel and NPLS,using the smooth flat plate flow for the flow experimental study of hypersonic boundary layer transition in Mach number 6,on the whole the hypersonic smooth flat plate boundary layer analysis on the spatial features.Secondly,we conducted four roughness element flat plate boundary layer to make flow visualization experiment with low-noise technology of hypersonic wind tunnel and NPLS,showing the roughness hypersonic boundary layer with high accuracy flow visualization,getting fine structures of hypersonic boundary layer flow,and analysis the overall spatial characteriatics under the influence of different roughness of hypersonic boundary layer flow.Rectangular roughness element,respectively,flat,diamond-shaped rib plate,segment Prism rib plate and sinusoidal Mach number for the rib plate 6 of the flow experimental study of hypersonic boundary layer transition,and these four rough forms of hypersonic boundary layer flow under the influence of the overall space characteristics analysis and time-related characteristics.