Stability and transition on a swept cylinder in a supersonic flow

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 $68^\circ$ and a free-stream Mach number $\mathrm{M}=2$ 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.