采用薄激波层理论和流管质量守恒相结合的方法,分析了高超声速二维钝楔边界层外缘熵的分布规律,研究了熵层对边界层外缘密度、马赫数以及壁面气动加热等气动参数的影响.结果表明:边界层外缘熵在倒圆-肩部区下降最为剧烈,熵层对气动参数的影响在高超声速下不可忽略,特别是使转捩区和湍流区的气动加热增加约53.6%.因此,将表面流态控制在层流模式对高超声速飞行器热防护具有重要意义. Based on the combination of the thin shock wave theory and the conservative flow tube, the entropy distribution of the outer edge of the hypersonic two-dimensional blunt wedge boundary layer is analyzed. The influence of the entropy layer on the outer boundary layer density, Mach number and aerodynamic heating The results show that the entropy of the edge of the boundary layer descends the most intensely in the rounding-shoulder area, and the effect of the entropy layer on the aerodynamic parameters can not be neglected at high supersonic speeds. In particular, the aerodynamic heating in the transition zone and the turbulent zone is increased About 53.6% .Therefore, the control of surface flow in laminar flow mode is of great significance to the thermal protection of hypersonic vehicles.