Evolution of mass flow and total temperature pulsations in flat-plate and swept-wing boundary layers at Mach 2 and 2.5

Abstract

Abstract The experimental data on the development of natural disturbances during the laminar-turbulent transition in the boundary layers of a flat plate and a swept wing with a supersonic leading edge at Mach 2 and 2.5 are analyzed. Data are obtained using a hot-wire anemometer in the automatic scanning mode for overheating of the probe. The levels of pulsations of mass flow and disturbances of total temperature are determined using the modified diagrammatic method of Kovasznay taking into account the coefficient of correlation. It was found that at all stages of the laminar-turbulent transition of the flow in the boundary layer, the ratio of the levels of pulsations of the total temperature and pulsations of the mass flow and the correlation coefficient remain almost constant.