The paper presents experimental results on the influence of weak shock waves on the development of controlled disturbances in a supersonic boundary layer on a flat plate with a Mach number equal 2.0. Results were obtained using constant-temperature anemometry method. A pair of shock waves in the incoming flow are generated by 150×7×0.13-mm 2D surface irregularity provided on the side wall of the T-325 wind tunnel (available at ITAM SB RAS). Controllable disturbances were generated in a flow by a high-frequency glow discharge within the chamber inside the model. Interacting from pair weak shock waves with the leading edge of plate creates a stationary wake in the boundary layer where controllable pulsations are generated. The paper focuses on a weak-nonlinear regime of evolution for controllable disturbances under conditions of a distorted wake of a flat plate and a uniform boundary layer. The characteristics of disturbance waves were analyzed. A method for evaluating dispersion ratio was developed. The paper compared experimental data with computation results. Numerical computations were performed using the linear stability theory under the uniform boundary-layer conditions.
Ermolaev et al. (Thu,) studied this question.