Experimental study of natural disturbances of a supersonic boundary layer on a swept-wing model with periodic roughness

This article is devoted to the experimental study of perturbations in a modulated swept-wing boundary layer at Mach 2. The modulation of the boundary layer was created using periodic roughness of the surface of the experimental model. The mean flow and pulsations were measured using a hot-wire anemometer. Spectral analysis of the disturbances showed that modulation of the boundary layer can lead to the stabilization of the development of disturbances in a wide frequency spectrum.