[Untitled]

Results of experimental investigations of the evolution of natural disturbances and laminar–turbulent transition in a supersonic boundary layer on the attachment line of a circular cylinder with a sweep angle of 68° and a free‐stream Mach number M = 2 are presented. The experimental studies are supplemented by calculations of the mean flow and stability characteristics. Flow regimes in the boundary layer on the attachment line are determined by a hot‐wire technique as functions of the Reynolds number and height of two‐dimensional roughness elements. The results are compared with NASA (Ames) experiments.