Classical ramjet engines feature high propulsive performances but drastically decreasing for increasing values of the flight Mach number. In the hypersonic regime (above Mach 6), the use of a supersonic combustion ramjet - a.k.a scramjet - may remedy this limitation. Computational fluid dynamics is one of the tools used for the study of such high-speed turbulent reactive flows. It must take into account the specificities of high Mach number reactive flows, which feature chemical reaction time scales with the same order of magnitude as flow time scales. The present study focuses on the improvement of a CFD tool by taking finite-rate chemistry and micro-mixing effects into account within the framework of the partially stirred reactor concept. In a first step of the validation procedure, the UPaSR closure hence proposed is applied to the numerical simulation of supersonic reactive co-flowing jets. The corresponding numerical results proved to be very encouraging, confirming the essential influence of both finite-rate chemical kinetics and compressibility effects for such conditions. Finally, the UPaSR closure is retained to analyse a full-scale scramjet geometry (RESTM12) experimentally studied at the University of Queensland. Two different approaches are applied and compared to evaluate the main performance indices.
