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- W2348193670 abstract "An aerodynamic profile parametric design method of engine exhaust system and aerodynamic performance were investigated for highbypassratio turbofan engine.The bypass duct and core duct of the nozzle were designed by controlling the centerlines and corresponding cross-section area of the two ducts.The nozzle flow field was simulated by CFD,and the influence of bypass nozzle pressure ratio and ambiance Mach number on nozzle thrust coefficient was analyzed.The results show that the nozzle thrust coefficient increase with the rising of bypass pressure ratio when the ambiance Mach number is 0.050,and correspondingly the nozzle thrust coefficient decrease with the rising of bypass pressure ratio when the ambiance Mach number is 0.785.Additionally,the nozzle thrust coefficient increase with the growth of ambiance Mach number.When the bypass nozzle pressure ratio is identical,the bigger the ambiance Mach number is,the larger the proportion of the axial force of B stage of core engine cover cowling and tail-cone is in nozzle total thrust,the more obvious the influences on nozzle thrust coefficient is." @default.
- W2348193670 created "2016-06-24" @default.
- W2348193670 creator A5089733147 @default.
- W2348193670 date "2014-01-01" @default.
- W2348193670 modified "2023-09-23" @default.
- W2348193670 title "A Design Method and Performance Research of Separately Exhaust System" @default.
- W2348193670 hasPublicationYear "2014" @default.
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