Abstract
Research using numerical simulation methods on the aerodynamic performance of the high bypass ratio civil engine exhaust system for civil aircraft has been launched in this paper. The influence of flight conditions and aircraft integration on the aerodynamic performance of the exhaust system is systematically analyzed. The result shows that flight Mach number manifests an inhibition influence on the mass flow of the exhaust system and a positive impact on the thrust of the exhaust system. Flight altitude has a negative influence on the mass flow and the thrust of the exhaust system. Aircraft body integration represents a gain on the exhausting flow and an opposite influence on the thrust.
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