Experimental Investigation of the Structure of Disturbances from Two Pulsed Sources in the Flat-Plate Supersonic Boundary Layer

Abstract The work is devoted to the development of a new experimental method for entering controlled disturbances with given frequency-wave structure into supersonic boundary layer. Experimental data on formation from two pulsed sources (pulsed glow discharge) in laminar flat-plate layer at Mach number equal 2 are given. experiments were carried out T-325 wind tunnel ITAM SB RAS. localized spaced same distance leading edge plate 6 mm each other spanwise. Flow pulsations measured using hot-wire probe constant temperature anemometer, signal was recorded synchronously ignition discharges. This made it possible distinguish discharges against background random uncontrolled “natural” spatial-temporal and generated single or discharges, operating time delay, analyzed. It found that maximum difference one observed central region, while side boundaries disturbances, close all considered cases. In wave spectra nodes antinodes formed. Their position determined by between delay their operation.