Abstract
The evolution of artificial disturbances in a laminar boundary layer on a flat plate model in the presence of an incident shock wave is considered. The flow is supersonic with the freestream Mach number M = 1.43. The results obtained in the two-dimensional computation are compared with the results obtained using the linear stability theory. The simulation is carried out in order to determine the possibility of using an electric discharge in the experiment as a source of first-mode disturbances. The discharge is simulated as a heat source. The results show a good agreement of two-dimensional computation with linear stability theory. It was demonstrated that discharge may be used as the source of first-mode disturbances.
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