The computational tool resulting from this project will have wide-ranging commercial applications. The Hybrid RANS-LES methodology can be used for a wide variety of engineering applications involving unsteady turbulent flows. The reacting flow capability can be used for simulating combusting flows in various industrial applications, such as gas turbine engines, diesel engines, etc. The real-fluids methodology can be used in a large number of industrial flow situations involving both chemically inert and reacting flows. With additions of multi-phase combustion modeling capability, the applicability of this tool can be further broadened. The outcome of Phase I and Phase II research activities will be a powerful CFD-based design and analysis tool for propulsion engines at NASA. This tool is envisioned to very beneficial for space propulsion devices including full rocket engine simulations, injector design, etc. Specific applications at NASA of this capability include: (a) design improvements of J-2X and RS-68 injectors, (b) design of space propulsion engines involving LOX and LCH4 propellants, (c) modeling of multi-element injectors coupled with fuel and oxidizer feedlines and manifolds, (d) prediction of stability and stability margins, (e) design of acoustic cavities for combustion stability, etc.