As a prerequisite for relevant model development and improvement of
design methodologies for supersonic vehicles, this study aims at
investigating the influence of wall heat-transfer and shock
interaction on the turbulence structure of supersonic boundary
layers. Incipient separation conditions and two different wall
thermal boundary conditions (adiabatic and cold) are considered.
The analysis focuses on the evolution of mean and turbulent flow
properties along the interaction region and in the relaxation
region downstream of the shock-system. The strong influence of the
mean pressure gradient is quantified through the analysis of mean
flow profiles and boundary layer integral parameters. The
anisotropic amplification of turbulent quantities through the
interaction region is characterized and the turbulent events
associated with the modification of the turbulence structure of the
perturbed boundary layer are identified. The mean and turbulent
thermal fields are shown to be strongly modified by the wall
cooling which significantly dampens more particularly the turbulent
thermal quantities levels across the boundary layer.
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