On the artificial wave packet development in a spanwise modulated boundary layer on the swept wing at Mach 2.

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 are presented. The influence of periodic roughness on the model surface on the excitation and development of wide-spectrum disturbances in the process of laminar-turbulent transition is determined. 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 strengthening of the oblique breakdown mechanism. [ABSTRACT FROM AUTHOR]