|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/04 B21D-053/92 F02C-007/042 B64D-033/02|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 87|
A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine perf...
1. An inlet for an engine of a supersonic aircraft comprising: an inlet ramp;a cowl lip spaced outwardly of said inlet ramp and configured to receive an air flow between said inlet ramp and said cowl lip;a forward portion of said inlet ramp from which an oblique shock extends outwardly to pass proximate said cowl lip when the supersonic aircraft is operating at a predetermined supersonic Mach speed;a rearward portion of said inlet ramp from which a terminal shock extends outwardly to a point proximate said cowl lip when the supersonic aircraft is operati...