The integral aerodynamic design of aircraft and its propulsion system becomes a difficult task due to the lack of steady pneumatic parameter data of the engine.While the discrete test run data of an aero-engine was adapted using the high order multi-parameters polynomial fit method

the steady characteristic curves were founded.The inverse simulation of pneumatic characteristics for the engine was thus performed

and the state characteristic curves of flow parameters at inlet and outlet of the engine were created

thus providing a basis for integral design of the aircraft and its engine.