Nozzle flow simulations of conventional and advanced rocket nozzles including essential loss effects are performed, using numerical methods. The influence of different loss origins on integral performance data, e.g. thrust and specific impulse, is studied and quantified by individual loss efficiencies. Absolute values and tendencies of the different loss efficiencies are analyzed for conventional nozzles as function of characteristic engine design parameters, e.g. combustion chamber pressure, nozzle geometry, nozzle exit area ratio or mixture ratio. Numerical simulations of advanced rocket nozzles of H_2-O_2 engines, promising a gain in integral performance data compared to conventional nozzles, are presented. The influence of turbine exhaust gas injection on main nozzle flow and performance parameters of a Vulkan-type nozzle are demonstrated. Furthermore, flowfield analyses of a dual-expander nozzle are presented and systematically evaluated. Individual loss efficiencies for these advanced nozzles are calculated. (orig.)SIGLEAvailable from TIB Hannover: RN 437(95-40) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman
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