ABSTRAKT

Some results from the direct numerical simulation of a spatially developing turbulent boundary layer flow at a free-stream Mach number of 2.25 along a cooled wall (T_w/T_aw < 1) are presented. The effect of wall-temperature variation can have a large effect on the turbulence dynamics of a wide variety of aeronautical and industrially relevant flows. Engineering flows ranging from turbine blade cooling at or near transonic speeds to nozzle flows at high supersonic or hypersonic velocities provide ample motivation for investigating such isothermal conditions. The mean and fluctuating turbulent statistics presented here primarily focus on comparisons with the same Mach number developing flow field under adiabatic wall conditions.