|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02B-027/00 F02C-007/042 B64D-033/02 F02C-007/045|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 87|
A supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle is disclosed herein. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a superso...
1. A method of decelerating a supersonic flow for a supersonic propulsion system, the method comprising: cruising at a predetermined supersonic speed;receiving a supersonic flow in an inlet opening of a supersonic inlet of the supersonic propulsion system;generating a first shock wave upstream of the inlet opening;directing the first shock wave into the inlet opening;generating a terminal shock wave, during operation of the inlet at the predetermined supersonic speed, in the inlet opening;splitting a subsonic flow downstream of the terminal shock wave in...