To the Defining of the Oblique Breakdown Mechanism in the Boundary Layer on a Flat Plate at Mach 2

Experimental study of the mechanisms of disturbances interaction in boundary layers is an important task for the theoretical description of wave processes of laminar-turbulent transition (LTT) [1, 2]. Two essential methods are applicable for modeling LTP: direct numerical simulation and calculations based on the wave approach of the hydrodynamic stability theory. For comparison with numerical results, experimental data, which can be obtained by introducing controlled disturbances into the supersonic boundary layer, are required [3]. This paper presents the results of oblique breakdown mechanism identification in a supersonic boundary layer on a flat plate, the flow in which is distorted by a longitudinal disturbance generated at the sharp leading edge by a pair of weak shock waves. This work is a follow of the research cycle begun in [4].