Experimental study of evolution of disturbances in a supersonic boundary layer on a swept-wing model under controlled conditions

Experimental data on stability of a three-dimensional supersonic boundary layer on a swept wing are presented. Evolution of artificial wave trains was studied. The experiments were conducted for Mach number $\mathrm{M}=2.0$ and unit Reynolds number $\mathrm{Re}_1=6.6\cdot10^6$ m$^{-1}$ on a swept-wing model with a lenticular profile and a $40^\circ$ sweep angle of the leading edge at zero incidence. Excitation of high-frequency disturbances caused by secondary-flow instability at a high initial amplitude was observed. It is shown that the evolution of disturbances at frequencies of $10$, $20$, and $30$ kHz is similar to the development of travelling waves for the case of subsonic velocities.