Tail-integrated boundary-layer ingesting propulsion

Abstract

Propulsion systems, methods and aircraft related to boundary layer ingestion are described. In some embodiments, an aircraft may include a fuselage with a plurality of boundary layer ingesting propulsors may be disposed on and distributed around at least a portion of a 5 perimeter of the fuselage. An annular exit nozzle may be fluidly coupled to a plurality of propulsor outlets of the plurality of propulsors such that an outflow from the plurality of propulsors flows through the annular exit nozzle during operation of the aircraft. In other embodiments, a boundary layer ingesting propulsor may be disposed on the fuselage where a portion of the fuselage upstream from the inlet may be configured to provide a desired Mach 10 number for fluid located within a predetermined distance of the propulsor inlet during cruise of the aircraft.

Dependencies are inferred from the claim text.