Wingtip vortex device for induced drag reduction and vortex canc

Details Wingtip vortex device for induced drag reduction and vortex canc Wingtip vortex device for induced drag reduction and vortex canc

1998-03-11

1999-08-10

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft power plants

Auxiliary

244199, B64D 3300

Patent

active

059346124

ABSTRACT:
The present invention is a wingtip vortex device for induced drag reduction and vortex cancellation. The wingtip vortex device is an aerodynamic drag reduction system installed at the wingtips of an aircraft. The wingtip vortex device comprises an impeller located ahead of the wingtip chord, a wind turbine device located behind the wingtip chord, and an intermediate gear device for coupling the impeller with the wind turbine and/or for generating power. Thus, the wingtip vortex device is self-contained as the impeller is powered by the vortex-driven turbine. As a result, induced drag is reduced without requiring an external power source such as the aircraft propulsion system.

REFERENCES:
patent: 1245902 (1917-11-01), Gretsky
patent: 1717552 (1929-06-01), Dunn
patent: 1850066 (1932-03-01), Altieri
patent: 1932532 (1933-10-01), Plillips
patent: 2485218 (1949-10-01), Shaw
patent: 4917332 (1990-04-01), Patterson, Jr.

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