Accession Number : ADD005952

Title :   Boundary Layer Scoop for the Enhancement of Coanda Effect Flow Deflection Over a Wing/Flap Surface.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C

Personal Author(s) : Grotz,Charles A

Report Date : 27 Mar 1979

Pagination or Media Count : 4

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 componnent, 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. (Author)

Descriptors :   *Patents, *Exhaust gases, *Boundary layer flow, *Coanda effect, *Wings, *Flaps(Control surfaces), Short takeoff aircraft, Turbojet engines, Turbofan engines, Gas flow, Thrust, Vertical orientation

Subject Categories : V/STOL
      Fluid Mechanics
      Combustion and Ignition

Distribution Statement : APPROVED FOR PUBLIC RELEASE