Comparison of hybrid RANS/LES methods for supersonic combustion in a model scramjet combustor

Abstract

Numerical studies are carried out on the boundary layer behavior on a flat plate as well as on the non-reactive and reactive flows in a scramjet combustor to analyze the effects of various hybrid RANS/LES methods. Three hybrid RANS/LES methods are selected—an improved delayed detached eddy simulation, the l 2ω-detached eddy simulation, and the dynamic l 2ω-detached eddy simulation. The present method is based on the finite-volume approach on structured mesh, and the governing equations are treated using the Favre averaging approach. Inviscid fluxes are discretized using 5th order WENO schemes. Turbulent combustion is modeled as a level-set flamelet model. Based on the results from the flat plate and the non-reacting and reacting simulation, most of the hybrid RANS/LES methods show equivalent trends. However, dramatic differences are found in the calculations for the improved delayed detached eddy simulation and dynamic l 2ω-detached eddy simulation in terms of eddy capturing.