Underwing compression vortex attenuation device

Details Underwing compression vortex attenuation device Underwing compression vortex attenuation device

1992-05-22

1993-07-27

Mitchell, David M.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244198, B64C 2306

Patent

active

052304868

ABSTRACT:
A vortex attenuation device is presented which dissipates a lift-induced vortex generated by a lifting aircraft wing. The device consists of a compression panel attached to the lower surface of the wing and facing perpendicular to the airflow across the wing. The panel is located between the midpoint of the local wing cord and the trailing edge in the chord-wise direction and at a point which is approximately 55% of the wing span as measured form the fuselage center line in the spanwise direction. When deployed in flight, this panel produces a positive pressure gradient aligned with the final roll-up of the total vortex system which interrupts the axial flow in the vortex core and causes the vortex to collapse.

REFERENCES:
patent: 3984070 (1976-10-01), Patterson, Jr.
patent: 3997132 (1976-12-01), Erwin
patent: 4377267 (1983-03-01), Haworth
patent: 4955958 (1990-09-01), Dellinger et al.
patent: 5037044 (1991-08-01), Seyfang
James Scheiman et al. "Exploratory Investigation of Factors Affecting the Wing Tip Vortex" Apr. 1972.

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