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 will facilitate full rocket engine simulations, injector design, launchpad induced environment simulations, turbopump design, etc. Specific applications at NASA of this capability include: (a) design improvements of liquid rocket engine injectors, (b) modeling of multi-element injectors coupled with fuel and oxidizer feedlines and manifolds, (c) prediction of stability and stability margins, (d) design of acoustic cavities for combustion stability, (e) analysis of small valves and turbopumps, (f) prediction of loads during launch of new launch vehicle, (g) prediction of acoustic loads on rocket engine test stands, (h) launch pad modifications, (i) development of new launch facilities, (j) analysis of rocket engine exhaust plumes, (k) modeling of flow of liquids and supercritical fluids through piping system components such as valves a 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.