Numerical Simulation of Multi-Component Flows with Variable Thermodynamic Properties Towards Supersonic Flow Over a Cavity

High-resolution numerical methods are implemented for multi-component gaseous flows with variable thermodynamic properties. These include a gradient based reconstruction method with monotonicty-preserving (MP) limiting for a shock capturing convective flux discretization and an α-damping approach for the viscous flux discretization. The double flux model is used to avoid pressure oscillations across material interfaces due to varying specific heat ratio. To demonstrate the capabilities of these methods, and for validation, a number of cases of shock wave interactions with bubbles are presented as well as a triple point shock interaction. The improved spectral properties of the methods are demonstrated with a comparison to those from the WENO-Z scheme. Some results are shown for the pure air (no fuel injection) supersonic flow in the Air Force Research Labs (AFRL) Research Cell 19 (RC19) cavity combustion chamber, including mean velocity profiles at a number of locations in the cavity. Additionally, some preliminary results are shown for the case of upstream fueling in the cavity combustion chamber. Work for this case is still underway, however some instantaneous two dimensional results are shown for the fuel mass fractions, stream-wise velocity, and temperature. Finding from these preliminary results will be used to help extend to full three dimensional simulations.