Accession Number : ADD004709

Title :   Jet Engine Tail Pipe Flow Deflector.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C

Personal Author(s) : Vaughan,John C , III

Report Date : 24 Jan 1978

Pagination or Media Count : 5

Abstract : Apparatus for producing a component of thrust at right angles to the main thrust direction of a jet engine. The apparatus comprises a deflecting device which provides a surface, bounded by side walls normal to the surface, that curves outwardly from tangency to the main thrust direction at the tail pipe edge. A series of control ports extending transversely of the curved surface at the point of tangency are connected to ambient air pressure through a normally open remotely controlled air valve. Closure of the air valve causes that portion of the jet stream adjacent to the curved surface to follow the surface because of the Coanda effect, thus producing a thrust component normal to the main jet stream. The device is particularly useful for yaw control of air cushion equipped jet powered aircraft when taxiing and during the low speed portions of takeoff and landing runs. (Author)

Descriptors :   *Patents, *Jet engines, *Tail assemblies, *Air flow, *Deflectors, Thrust control, Pipes, Edges, Ports(Openings), Air pressure, Valves, Coanda effect, Jet streams, Yaw, Air cushion vehicles, Takeoff, Landing

Subject Categories : Surface Effect Vehicles & Amphibious Vehicles
      Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE