Large-Eddy Simulation of a Dual-Mode Scramjet Combustor Using Non-Adiabatic Flamelet Modeling

Abstract

In this study, non-adiabatic flamelet combustion model have been conducted for resolving finite rate chemistry effects on University of Virginia’s Scramjet Facility Dual-Mode Scramjet Combustor Configuration A using large-eddy simulation(LES). Numerical results are compared with coherent anti-stokes raman spectroscopy measurements (CARS). Flamelet structure is defined with mixture fraction, scalar dissipation rate and heat loss ratio (enthalpy defect). In addition, Reynolds – averaged Navier- Stokes(RANS) based computational grid investigation is presented with three different grid resolutions. The result of this study, the effectiveness and accuracy of non-Adiabatic flamelet combustion model, is investigated. © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.