Charles T Dixon

US Patent:

6715717, Apr 6, 2004

Filed:

Sep 6, 2002

Appl. No.:

10/236726

Inventors:

Charles J. Dixon - Kennesaw GA 30152
Arthur C. Hughes - Marietta GA 30067

International Classification:

B64C 2306

US Classification:

244130, 244199

Abstract:

A method and apparatus of creating vortices via vortex controllers, wherein the vortices are capable of entraining high-energy surrounding flow to induce a series of powerful longitudinal vortices that reattach separated flow by merging into single vortices along the undersurface of the afterbody to reenergize the fuselage boundary layer, thus preventing undersurface flow separation and reducing overall afterbody drag.

US Patent:

63186772, Nov 20, 2001

Filed:

Aug 6, 1999

Appl. No.:

9/370645

Inventors:

Charles J. Dixon - Kennesaw GA

International Classification:

B64C 2306

US Classification:

244199

Abstract:

Method and apparatus for generating a stable leading edge lifting vortex controller that significantly improves flight control and safety of an aircraft. More specifically, in a preferred embodiment, the present invention is generally a triangular or diamond-shaped member, as seen in a plan view, having a leading edge and a trailing edge wherein the trailing edge of the member is attached to the leading edge of an aircraft wing in substantially the same plane as the wing. The distal end of the leading edge of the member has a slightly drooped rounded nose. The member has a variable thickness wherein the upper surface of the member has a camber and wherein the member is substantially shaped like an airfoil. The thickness at the centerline of the member proximal to the wing is approximately the thickness of the leading edge of the wing to provide a smooth transition along the centerline. The thickness decreases from the centerline to the two distal opposing edges from the centerline that contact the leading edge of the wing to form a sharp point having negligible thickness.