Abstract:
The characteristics of the supersonic turbulent boundary layer subjected to the streamwise curved wall surface is an important scientific issue in fluid mechanics. To know clearly its laws is of great significance for improving the design level of hypersonic vehicles. Research on this issue in the international community has continued for more than 50 years. In recent years, with the improvement of experimental measurement and numerical simulation capabilities, breakthrough progress has been made in the influence mechanism of streamwise curvature rate. This paper systematically summarizes the evolution mechanism of supersonic turbulent boundary layer subjected to convex curved wall and concave curved wall, introduces the influence law of key impact factors such as flow direction curvature, pressure gradient and volume expansion/compression. The characteristics and causes of turbulence attenuation of convex supersonic wall boundary layer, as well as the characteristics and causes of Görtler instability and backpressure gradient enhanced turbulence fluctuation in the concave supersonic wall boundary layer, is summarized. Finally, the developing trend is summarized, and suggestions are made for the next step of research on the curved wall supersonic turbulent boundary layer.