On the artificial wave packet development in a spanwise modulated boundary layer on the swept wing at Mach 2.5

The results of an experimental study of the perturbation development created by pulsed glow discharge on the swept wing surface with periodic distributed roughness along the leading edge at Mach 2.5 are presented. This work continues research on this model at Mach 2. It was found that the mean flow modulation in the boundary layer of a swept wing with a sweep angle of 40 degrees leads to a change in the amplitude of artificial pulsations excited in the boundary layer by a disturbance source and to a strengthening of the oblique breakdown mechanism at a Mach number of 2.5.