Search

The evolution of the artificial wave packet in the supersonic boundary layer of swept wing was experimentally studied for the first time by hot-wire measurements. The localized disturbances were generated by pulse glow discharge. Analysis of the mean flow, integral dependences, and the averaged waveforms of wave packet in supersonic boundary layer of swept wing has been executed.

The work is devoted to the study of the regularities of laminar-turbulent transition in supersonic boundary layers. New experimental data are presented on the evolution downstream of natural disturbances in the boundary layer of a flat plate. The experiments were carried out in a low-noise supersonic wind tunnel T-325 of ITAM SB RAS at Mach number M=2.5. The measurements were made by a constant-temperature hot-wire anemometer in the scanning mode. The procedure of decomposition of the fluctuations of the boundary layer into temperature and mass flux disturbances is carried out.

The evolution of the artificial wave packet in laminar flat-plate boundary layer was experimentally studied by hot-wire measurements at M=2. The localized disturbances were generated by pulse glow discharge. The wave analysis of evolution of wave packet was provided. It was found, that the most unstable waves are oblique, that consistent with results of linear theory.