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.