Boundary layer scoop for the enhancement of Coanda effect flow d

Details Boundary layer scoop for the enhancement of Coanda effect flow d Boundary layer scoop for the enhancement of Coanda effect flow d

1977-09-16

1979-03-27

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft, heavier-than-air

Airplane and fluid sustained

244204, 244207, B64C 2102

Patent

active

041461975

ABSTRACT:
A STOL aircraft having turbojet or torbofan engines mounted above and forward of the wing whereby the engine exhaust gases flow over and, by the Coanda effect, attach to the upper surfaces of the wing and a downwardly curved extendible flap to produce a downwardly turned exhaust flow having a large vertical component of thrust. Premature separation of the exhaust flow from the wing or flap due to reduced velocity in the boundary layer of the flow, which would result in decreased turning of the exhaust gases and a reduced vertical thrust component, is prevented by a boundary layer scoop extending across the exhaust flow, in an area just prior to where the exhaust flow would separate from the wing or flap, for removing the boundary layer gases and discharging them beneath the wing.

REFERENCES:
patent: 3827657 (1974-08-01), Schwarzler
patent: 3884433 (1975-05-01), Alexander
patent: 3940092 (1976-02-01), Farris

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