3881669 is referenced by 22 patents and cites 4 patents.

Herein are disclosed a method and apparatus for eliminating or substantially attenuating the dangerous vortices which typically trail the airfoils of heavier-than-air aircraft in flight. The disclosed method consists of injecting a fluid stream into the core of the vortex (a) in a direction such that the longitudinal axis of the injected fluid stream is substantially colinear and coaxial with the longitudinal axis of the vortex where the injected stream enters the vortex core, and (b) at a momentum flux of such magnitude relative to that of the free air stream that the vortex will be rendered hydrodynamically unstable. The criteria as to the direction and the magnitude of the momentum flux of the injected fluid stream are disclosed as critical to the successful practice of the invention. It is preferable that the departure from colinearity be not more than 4.degree..The apparatus of the invention comprises, in combination with an airfoil, a pair of nozzles adapted for injecting a fluid stream of the required orientation and of a momentum flux of such magnitude relative to the free air stream into the trailing vortex that the trailing vortex will be rendered hydrodynamically unstable and apparatus for supplying a suitable fluid to the nozzles.

Title
Method and apparatus for elimination of airfoil trailing vortices
Application Number
05/360,928
Publication Number
3881669
Application Date
May 16, 1973
Publication Date
May 6, 1975
Inventor
Lessen Martin
Agent
Bramson Esquire Robert S
Drobile Esquire James A
IPC
B64c 23/06
B64C 23/00
B64C 23/06
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