Abstract
Using a modified version of JANNAFs Two-Dimensional Kinetic Program (TDK), parametric calculations of rocket nozzles were performed. Efficiencies of energy release in rocket engines are defined. The domain of nozzle losses is classified by two-dimensionality, frictionand kinetic. Their dependencies versus characteristic nozzle design parameters were investigated. In addition, the influence of shocks isthe nozzle and cooling effects of the efficiencies has been considered. The losses are determined using nozzle shapes of SSME andVulcan engines which are characteristic for future rocket launchers. The nozzle design parameters are parametrically derived versus thrust, chamber pressure, mixture ratio, nozzle area ratio, and nozzle geometry. All these parameters are systematically varied, and their effects on nozzle efficiencies are pesented. These efficiencieswill be used as a data base for further system analyses of future rocket launchers.
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