Patent ID: 9027583
Filing Date: 2015-05-12
Classification: B64D,F02C,F02K,F05D,Y02T,Y10T

Abstract:
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 into a primary flow portion and a bypass flow portion; directing the primary flow portion to an engine of the propulsion system; and directing the bypass flow portion to a nacelle bypass that bypasses the engine, the bypass flow portion including substantially all flow distortion introduced when the inlet opening receives the first shock wave.