Convective heat-transfer in the boundary-layer behind a shock-wave moving over a flat-plate with a sharp leading-edge – computing method and comparison with experimental data

The authors have numerically investigated flow and heat transfer in a boundary layer formed over a flat plate of a supersonic stream of high-temperature air behind a shock wave moving along the plate. They describe a method developed for solving the problem. They propose a method for describing transition from the laminar to the turbulent flow regime in the unsteady boundary layer behind the shock wave. They compare the results of calculations with experimental data on heat transfer in laminar and turbulent unsteady and steady boundary layers in air, obtained in shock tubes.