DRAG RECOVERY SCHEME USING BOUNDARY LAYER INGESTION
Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.
1 . An aircraft, comprising: a blended wing body;
at least one engine housed within a nacelle, wherein the at least one engine is mechanically coupled to at least one fan;
at least one bypass intake duct configured to receive boundary layer air from a top surface of the blended wing body, the at least one bypass intake duct located proximate to a fan intake of the at least one fan;
at least one bypass exhaust duct located proximate to a fan exhaust of the at least one fan, wherein the at least one bypass exhaust duct is configured to output the boundary layer air into the fan exhaust of the at least one fan;
a passageway, located substantially between the blended wing body and the at least one engine, fluidically connecting the at least one bypass intake duct with the at least one bypass exhaust duct and configured to direct the boundary layer air from the at least one bypass intake duct to the at least one bypass exhaust duct; and
a nozzle configured to direct the boundary layer air and the fan exhaust out of a nozzle exit located forward of a trailing end of the blended wing body.
2 .- 20 . (canceled)