Accession Number : ADD018292

Title :   Guided Wing for Aircraft Flying at High Angles of Attack.

Descriptive Note : Patent, Filed 19 Jan 95, patented 19 Nov 96,

Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON DC

Personal Author(s) : Tai, Tsze C

Report Date : 19 Nov 1996

Pagination or Media Count : 11

Abstract : The invention is directed to an apparatus for attaching to a wing operating in a fluid medium for increasing the angle of attack at which the wing experiences aerodynamic/hydrodynamic stall. The wing includes upper and lower surfaces extending between a leading edge and a trailing edge and having a maximum thickness therebetween and between a root and a tip, wherein the leading and trailing edges define a chord and the root and tip define a span. The apparatus comprises at least one substantially triangular shaped plate member projecting normal to the upper surface of the wing. The at least one plate member has a straight top surface and a curvilinear bottom surface which corresponds to the contour of the upper surface of the wing. The top and bottom surfaces define the height of the at least one plate member and extend in a substantially chordwise direction between an anterior end and a posterior end of the at least one plate member. The at least one plate member has its minimum height at the anterior end and its maximum height at the posterior end wherein the maximum height corresponds to a fully attached boundary layer thickness of a fluid flowing over the upper face, the boundary layer thickness determined at the trailing edge at a predetermined operating condition.

Descriptors :   *WINGS, *PATENTS, VORTICES, ANGLE OF ATTACK, STALLING, LEADING EDGES, FLOW SEPARATION, AERODYNAMIC LIFT, BOUNDARY LAYER CONTROL, BOUNDARY LAYER FLOW, WING TIPS, TRAILING EDGES, THREE DIMENSIONAL FLOW, AERODYNAMIC CONTROL SURFACES, DRAG REDUCTION

Subject Categories : Aerodynamics
      Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE