Title: Integrated control for supersonic inlet/engine
Abstract: A component-level mathematical model of supersonic inlet with bleeding adjustment was developed to study of integrated performance for supersonic inlet/engine.Meanwhile,a coupling mathematical model of supersonic inlet and turbofan engine was built via a biaxial turbofan engine component-level models and inlet component-level models to describe their collaborate relationship.The properties of outside and inside flux of the intake were calculated base on this integrated component-level model for inlet/engine.Inlet bleeding properties in supersonic working mode were also analyzed.At last,the engine installed thrust was verified to be effectively enhanced 3% by the bleeding adjustment of inlet when the aircraft worked at supersonic flight in the middle and afterburner states.
Publication Year: 2014
Publication Date: 2014-01-01
Language: en
Type: article
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Cited By Count: 2
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