Aerodynamic surface tip vortex attenuation system

Claim 1

In an aircraft wing of finite span having an upper wing surface, a lower wing surface and a wing tip, said wing being capable of producing lift or thrust when in relative motion through a fluid, said fluid being higher pressure fluid below said lower wing surface and lower pressure fluid above said upper wing surface during said motion, apparatus for attenuating wing tip vortices and thereby increasing wing efficiency and overall aerodynamic efficiency and decreasing wake turbulance, comprising: a Coanda surface on said wing tip, said Coanda surface having an upper bound and a lower bound; and adjustable flow rate means for discharging tipwardly spanwise, tangentially along a portion of said upper wing surface and adjacent said upper bound of said Coanda surface, compressed fluid having variable mass flow; whereby when said compressed fluid is discharged at least a portion of said compressed fluid is entrained by said Coanda surface and deflected downward from said Coanda surface, said compressed fluid forming a fluid barrier for substantially preventing crossflow of said high pressure fluid from below said lower wing surface to above said upper wing surface and thereby stemming generation of said vortices; said fluid barrier defining a plane which extends in a generally chordwise direction and downward from said Coanda surface substantially perpendicular to the plane defined by said wing and substantially perpendicular to the span line defined by said wing; said fluid barrier being tangential to said wing tip at the outboard-most location of said wing tip and generally along a line which defines the mean camber line of said wing tip; said fluid barrier extending downward from said Coanda surface a sufficient distance and in a generally chordwise direction a sufficient distance for and aft for substantially preventing flow of said higher pressure fluid beyond said fluid barrier; the length of said fluid barrier in a generally chordwise direction being substantially equivalent to the planwise contour length of said wing tip; said adjustable flow rate means for discharging compressed fluid including a fluid discharge slot located in said upper wing surface; said fluid discharge slot defining a shape which is substantially parallel to the planwise contour of said wing tip from the leading edge of said wing to the trailing edge of said wing; said fluid discharge slot extending in a generally chordwise direction from a location proximate said leading edge of said wing to a location proximate said trailing edge of said wing; said fluid discharge slot being bordered, in said generally chordwise direction, by an upper slot edge and a lower slot edge, each said slot edge being integrated in said upper wing surface; said lower slot edge being located below, in a generally elevational direction, said upper slot edge; said upper slot edge being located, in a generally spanwise direction, outboard of said lower slot edge; said Coanda surface being an elevationally convex Coanda surface which intersects said outboard-most location of said wing tip; said convexity of said Coanda surface defining a substantially semicircular shape having a diametric plane, connecting said upper bound and said lower bound of said Coanda surface, which is substantially parallel to said plane defined by said fluid barrier, substantially perpendicular to said plane defined by said wing, said substantially perpendicular to said span line defined by said wing; each said bound of said Coanda surface extending in a generally chordwise direction from a location proximate said leading edge of said wing to a location proximate said trailing edge of said wing; each said bound of said Coanda surface defining a shape which is substantially parallel to said shape defined by said fluid discharge slot and substantially parallel to said planwise contour of said wing tip from said leading edge of said wing to said trailing edge of said wing.