Краткое описание

A spatially evolving, supersonic boundary layer flow with an impinging shock has been computed using direct numerical simulation. The free stream Mach number M_∞ is 2.25 and the momentum thickness Reynolds number (based on free stream conditions) Re_θ is 4000. The same turbulent flow but without the impinging shock is the comparison basis that provides a gauge to assess the extent by which the turbulent statistical moments are altered due to the presence of the shock. In this impinging shock study, some scalar fluxes and velocity second- and higher-order moments are monitored and assessed at several stations along the plate so that the effect of the shock can be assessed both upstream, downstream and in close streamwise proximity to the impingement point.