|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/767; 060/768; 060/204; 137/015.1; 244/053B|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 3 인용 특허 : 82|
A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, 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 performance.
1. A supersonic propulsion system, said propulsion system designed for flight at a specific and pre-determined Mach number, comprising: an engine comprising an air intake and an exhaust system;a subsonic diffuser section coupled to the air intake of the engine, and configured to diffuse a flow and to admit the diffused flow to said air intake of said engine at a predetermined subsonic condition suitable for the engine; anda supersonic compression section coupled to the subsonic diffuser section by a throat, the supersonic compression section comprising a...