Hot-wire measurements of the evolution of total temperature and mass flow pulsations in supersonic boundary layer on flat plate with coating permeability

摘要

An experimental study of supersonic boundary layer on a flat plate with coating permeability at two Mach numbers 2 and 2.5 was carried out. The flow disturbances were measured by a constant-temperature anemometer (CTA), operating in the scanning regime. The procedure for calibrating a constant-temperature anemometer has been performed. It was shown that the coefficients of sensitivity to pulsations of mass flow rate and stagnation temperature are practically independent of the Mach number of the oncoming flow. In experiments on a flat plate with porosity, the positions of the laminar-turbulent transition were determined. The obtained experimental data can be used in calculations and numerical prediction of a laminar-turbulent transition in a supersonic boundary layer.