An experimental investigation of heat transfer in a highly cooled turbulent boundary layer of supersonic flow of air: Measurement procedure and results

The paper presents new experimental data on turbulent heat transfer, when a flat plate is flowed by a high-temperature air flow (temperatures-up to $6000$ K, pressures-up to $5$ atm, Mach numbers-up to $2.9$). This heat transfer occurred under conditions of strong cooling of the boundary layer and with enthalpy factor equal to $0.01$–$0.1$. For the first time, data on critical Reynolds numbers have been obtained for the transitions from the laminar to turbulent flow regime in the boundary layer.