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 multi-phase combustion modeling 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. The outcome of Phase 2 work will be a powerful CFD-based design and analysis tool for propulsion engines at NASA. This will facilitate analysis of flow environments in propulsion devices including full rocket engine simulations, injector design, turbopump and valve design, etc. Specific applications at NASA include: (a) design improvements of injectors of J-2X and RS68 engines as well as other engines using LOX and LCH4 as part of the PCAD project, (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 and run tanks.