Supersonic vortex generator

Details Supersonic vortex generator Supersonic vortex generator

1994-12-15

1997-02-04

Kashnikow, Andres

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244198, 244200, 2961801, 2961802, 180762, B64C 2306

Patent

active

055989900

ABSTRACT:
A vortex generator for attenuating flow separation which occur during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet propulsion unit, turbine or compressor blades, or similar surfaces subjected to supersonic airflow. A series of vortex generators are provided each of which comprises a cavity in the component over which the supersonic air is flowing that is configured to generate a spiral vortex which attenuates flow separation and weight drag resulting from the supersonic airflow. Each cavity is of generally triangular configuration defined by two side walls which diverge in a direction away from the apex of the triangular cavity, and a flat bottom wall joined to the side walls. In an alternate embodiment, means is provided for selectively shifting the bottom wall from a retracted inner position, to an outer location essentially flush with the surface over which the supersonic airflow is occurring.

REFERENCES:
patent: 4354648 (1982-10-01), Schenk et al.
patent: 4714197 (1987-12-01), Thayer et al.
patent: 4789117 (1988-12-01), Paterson et al.
patent: 4836473 (1989-06-01), Aulehla et al.
patent: 5058837 (1991-10-01), Wheeler
patent: 5186415 (1993-02-01), Li

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