Wingtip vortex impeller device for reducing drag and vortex canc

Details Wingtip vortex impeller device for reducing drag and vortex canc Wingtip vortex impeller device for reducing drag and vortex canc

1998-03-11

1999-07-06

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244 58, B64C 2302

Patent

active

059188359

ABSTRACT:
The present invention is a wingtip vortex device installed at the wingtips of an aircraft for induced drag reduction and vortex cancellation. Also, the wingtip vortex device is self-contained and is powered by the wingtip vortex. The wingtip vortex device comprises a shaft coupled between the wing and a spinner. The spinner is a streamlined body of revolution with a number of radial fins. The wingtip vortex of the aircraft induces spinner whirl, which is opposite to that of the wingtip vortex. As a result, the spinner-induced whirl produces an upwash superimposed on the downwash of the vortex. Thus, the total downwash, and hence the induced drag, are reduced.

REFERENCES:
patent: 1849547 (1932-03-01), Marsan
patent: 4045144 (1977-08-01), Loth
patent: 4047832 (1977-09-01), Sforza
patent: 4917332 (1990-04-01), Patterson, Jr.
patent: 5100085 (1992-03-01), Rubbert

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