Large-Eddy Simulation of Turbulent Supersonic Cold Flow in Ramp-Cavity Combustor With Injector

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Development of efficient supersonic propulsion systems requires a deep understanding of the flow within such combustors. Performing numerical simulation of flow in a scramjet engine is challenging due to the concurrent presence of shock waves and turbulence. In this work, we employ a high-order discontinuous spectral element method (DSEM). An entropy-based artificial viscosity method is used to capture the shock and the turbulence model is the standard Smagorinsky-Lilly model in conduction with two new sensors that prevent addition of turbulent viscosity in non-turbulent regions. Results are presented for the simulation of supersonic turbulent cold flow in a ramp-cavity combustor with an injector at the ramped side of the cavity. The Reynolds number based on the cavity height and mean inlet flow velocity is Re=25,288 and the Mach number is Ma=2.