|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64D-029/00 B64D-027/00 B64D-033/02 F02K-007/10 F02K-003/02 B64C-030/00 B64D-027/02|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 9|
A propulsion system for a supersonic aircraft includes an engine including an engine core and an engine bypass, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a plurality of vortex generators positioned upstream of the engine. The vortex generators have a height such that when the supersonic aircraft is flown at a predetermined altitude and predetermined speed, the plurality of vortex generators create vortices that propagate partially...
1. A propulsion system for a supersonic aircraft, the propulsion system comprising: an engine including an engine core and an engine bypass, the engine core having a higher sensitivity than the engine bypass to a change in stagnation pressure;a compression surface disposed upstream of the engine;a shroud partially surrounding the engine and configured to direct an airflow passing over the compression surface towards the engine; anda plurality of vortex generators positioned upstream of the engine, each vortex generator of the plurality of vortex generato...