Film Cooling in Laminar and Turbulent Supersonic Flows

Film-cooling experiments of generic supersonic flat-plate flows have been conducted at the Shock Wave Laboratory, RWTH Aachen University, for the laminar and turbulent boundary-layer regimes. To obtain a cooling film, coolant is injected through different blowing geometries to the surface of the plate. The model geometry as well as the width of the blowing slots have been carefully chosen to guarantee a two-dimensional flow at the centerline. Therefore, all blowing geometries share the same width. Different injection angles and coolant mass flow rates, as well as different freestream conditions, are investigated to obtain an empirical correlation for the cooling efficiency, a value often referred to in literature that describes the cooling effect.