Investigation of laminar-turbulent transition of supersonic boundary layer by scanning constant temperature hot-wire anemometer at Mach 2-4

Abstract

The work is devoted to the experimental study of the development of mass flow and total temperature pulsations in the boundary layers of a flat plate and a swept wing at Mach numbers 2, 2.5 and 4. The experiments were carried out in a T-325 supersonic wind tunnel of the ITAM SB RAS. The pulsations were measured using a constant temperature hot-wire anemometer in the automatic scanning mode based on probe overheating. The analysis of the experimental data showed that for the experimental conditions at all stages of the laminar-turbulent transition of boundary layers, the mass flow and total temperature pulsations develop similarly, and the ratio of the pulsation levels practically does not change.