Vortex alleviating wing tip

• US 4,477,042 A
• Filed: 01/17/1983
• Issued: 10/16/1984
• Est. Priority Date: 01/19/1981
• Status: Expired due to Fees

• Current Assignee: Roger W. Griswold II
• Original Assignee: Roger W. Griswold II
• Inventors: Griswold, Roger W. II
• Primary Examiner(s): Basinger, Sherman D.
• Application Number:
  US06/458,736
• Time in Patent Office: 638 Days
• Field of Search: 244/198, 244/199, 244/201, 244/207, 244/208, 244/91, 244/35 R, 244/210
• US Class Current: 244/199.2
• CPC Class Codes: B64C 23/065 at the wing tips
• CPC Class Codes: B64C 23/069 using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A wing tip is contoured and shaped to bring about a controlled mergence of fluid flows across the upper and lower wing surfaces and alleviation of the resulting vortex when the wing is producing lift or thrust. Control through geometry of the wing tip can be augmented by discharging fluid into the merging flows which weakens the strength of the vortex and results in more rapid dissipation in the wake of an aircraft. Additionally, the origin of the vortex is prevented from migrating inboard of the wing tip which improves overall wing efficiency.

Claims

1. In a wing of finite spanwise extent for producing lift or thrust by virtue of a dynamic flow of fluid over oppositely disposed upper and lower wing surfaces, each of the surfaces extending chordwise from a leading to a trailing edge, an improved tip at the spanwise termination of the wing for bringing about a controlled mergence of the fluid flowing over the upper and lower surfaces at different pressure levels comprising:

contoured surface portions joined with the upper and lower wing surfaces and blending smoothly into the upper and lower wing surfaces without abrupt changes in the spanwise direction, the contoured surface portions forward of the chord point of maximum thickness being convexedly rounded without concave portions at any spanwise section in the forward part of the tip and convergent along the outboard edge at large obtuse angles generally at 180 degrees to smoothly interconnect the forward parts of the upper and lower wing surfaces, and aft of the chord point of maximum thickness, the contoured surface portions including a convex lower portion bending gradually upwardly in the spanwise direction with substantially uniform curvature from the junction of the tip and lower wing surface to the outboard edge and joined with a concave upper portion also bending gradually upward in the spanwise direction with substantially uniform curvature from the junction of the tip and upper wing surface to define a gradually tapered, sharp, upwardly swept edge portion and bring about a controlled mergence of the flows above and below the wings, the gradually bending upper and lower portions approaching one another at the outboard edge at acute angles progressively decreasing from the chord point of maximum thickness to the trailing edge, and forming a sharply angled outboard edge without substantial curvature of the surfaces in the chordwise direction to reduce differential pressure and to precipitate vortices generated by the confluence of flows over the upper and lower surfaces with immediate separation at the spanwise termination of the wing.

2. The wing of claim 1 wherein the spanwise dimensions of the wing tip aft of the chord point of maximum thickness are not smaller in planform than the spanwise dimension of the tip at said chord point.

3. The wing of claim 1 wherein the sharply angled edge aft of the chord point of maximum thickness slopes upwardly and outwardly of the wing from said point to maintain an effective aspect ratio of the wing not substantially less than the geometric aspect ratio of the wing.

4. The wing of claim 1 further including means defining a fluid discharge in the gradually tapered, sharply angled, swept edge portion, and fluid supply means connected with the discharge defining means for discharging pressurized fluid into the confluence of the flows at the outboard edge.

5. The wing of claim 4 wherein the means defining a fluid discharge includes means defining a slot in the outboard edge.

6. The wing of claim 4 wherein the fluid supply means comprises ram inlet means defining a fluid inlet adjacent the leading edge of the wing, and a fluid conduit within the wing and connecting the inlet with the discharge at the outboard edge.

7. The wing of claim 1 wherein the aft portion of the sharply angled edge lies in a plane above the upper wing surface.

23. In a wing of finite spanwise extent, an improved tip at the spanwise termination as defined in claim 1 wherein the gradually bending upper and lower tip portions meet at the outboard edge aft of the chord point of maximum thickness in acute angles not greater than 10 degrees.

8. A lift-producing wing of limited span for reducing induced drag and vortex strength comprising:

upper and lower wing surfaces joined forwardly at a leading edge and aft at a trailing edge, the wing surfaces also extending spanwise and having shaped upper and lower terminal portions projecting in a gradually tapered fashion outwardly to a spanwise flattened tip and joined with one another at the tip along a sharply angled outer edge of the wing aft of the chord point of maximum thickness to permit fluid flows above and below the wing surfaces to merge at the angled outer edge, the angled outer edge of the wing extending forward from a point at the trailing edge at least as far outboard on the wing as any other point on the wing, and the terminal portions being shaped with uniform, curvatures in the spanwise direction between the wing and the outer edge, one of the portions having a concave curvature and the other having a convex curvature; and

aperture means located at the angled outer edge of the wing and defining an opening for discharging fluid outwardly and rearwardly in the direction of lift producing fluid flowing from below the wing into merging flows from below and above the wing surfaces as the wing develops lift or thrust to thereby weaken wing tip vortices and shift the vortex origins outboard of the wing.

9. A wing of limited span as defined in claim 8 wherein the aperture means defines a slot in the sharply angled outer edge.

10. A wing of limited span as defined in claim 8 wherein the shaped terminal portion having the concave curvature is an extension of the upper wing surface, and the shaped terminal portion having the convex curvature is an extension of the lower wing surface to define a tip portion of negative conical camber.

11. A wing of limited span as defined in claim 8 wherein the shaped terminal portion having the concave curvature is an extension of the lower wing surface, and the shaped terminal portion having the convex curvature is an extension of the upper wing surface to define a tip portion of positive conical camber.

12. A wing of limited span as defined in claim 8 further including fluid conduit means connected with the aperture means at the sharply angled outer edge for directing the discharged fluid outboard of the edge and generally tangent to the shaped and joined terminal portions at the edge.

13. A wing of limited span as defined in claim 8 wherein the terminal portions of the wing surfaces are also joined with one another along a rounded outer edge;

and the rounded edge is located forward of the chord point of maximum thickness.

14. An aircraft comprising a main body and an airfoil having upper and lower surfaces for producing lift when the airfoil is moved through air, the airfoil being connected at one end with the body of the craft and having an opposite, outer end from which fluid dynamic vortices emanate due to the mergence of fluid flows from above and below the foil while the foil is producing lift, the outer end of the foil projecting spanwise and gradually tapering to a sharply angled outer edge aft of the chord point of maximum thickness for vortex precipitation which edge in planform is located effectively no closer to the main body at the trailing edge of the foil than at the midchord region to prevent inward migration of the vortex origins and to reduce the induced drag, the gradual tapering being accompanied by substantially no curvature of the surfaces in the chordwise direction between the chordpoint of maximum thickness and the trailing edge to correspondingly reduce the differential pressure between the upper and lower surfaces and reduce the strength of the vortices produced thereby, and means defining an outwardly and rearwardly directed conduit at the projecting, sharply angled edge for discharging a fluid into the mergence of the fluid flows to dissipate the fluid dynamic vortices which are produced.

15. An aircraft as defined in claim 14 wherein the outer end of the airfoil has a zero camber.

16. An aircraft as defined in claim 14 wherein the outer end of the airfoil is upswept and defines a negative conical camber.

17. An aircraft as defined in claim 14 wherein the outer end of the airfoil is downswept and defines a positive conical camber.

18. An aircraft as defined in claim 14 wherein the airfoil comprises a wing having another airfoil in the form of a flap connected at the trailing edge of the wing and movable between a lowered and raised position;

and an end plate is connected to one end of the flap to inhibit the formation of vortices on the flap.

19. An airfoil as defined in claim 18 further including an aileron movable about a neutral position and connected at the trailing edge of the wing adjacent the outboard end of the flap;

and the end plate is mounted on the end of the flap adjacent the aileron and is shaped to effectively close the space between the aileron in the neutral position and the flap in a lower position.

20. In a craft having lift generating foils extending from a central body laterally outboard at each side of the craft, improved aerodynamic tips at the outboard ends of the foils comprising:

a rounded tip at the outboard end of each lift-generating foil;

means at the outboard end of each lift-generating foil for discharging fluid alternatively outboard tangentially of the foil and over the rounded tip for vortex alleviation, or tangentially inboard over the foil into the region of vortex origins to improve vortex generation;

fluid supply means connected with the discharging means for providing the fluid to be discharged inboard and outboard; and

fluid control means connected with the discharging means for controlling the discharging of fluid and directing the fluid alternatively outboard or inboard over the foil.

21. The improved aerodynamic tips of claim 20 wherein the discharging means comprises a first tangential discharge passageway for directing fluid outboard of the foil and the craft, a second tangential discharge passageway for directing fluid inboard over the foil, and valve means for selectively directing fluid out of the first and second passageways, the fluid control means being connected with the valve means.

22. The improved aerodynamic tips of claim 21 wherein the fluid supply means comprises a fluid duct within the lift-generating foil and having an inlet receiving ram-pressurized fluid from outside the craft.

24. An aircraft comprising a main body and an airfoil having upper and lower surfaces for producing lift when the airfoil is moved through air, the airfoil being connected at one end with the body of the craft and having an opposite, outer end from which fluid dynamic vortices emanate due to the mergence of fluid flows from above and below the foil while the foil is producing lift, the outer end of the foil projecting spanwise and having upper and lower surfaces meeting substantially at 180 degrees without concave portions at any spanwise section in the part of the tip forward of the chord point of maximum thickness, and aft of the chord point of maximum thickness gradually tapering to a sharply angled edge for vortex precipitation which edge in planform is located effectively no closer to the main body at the trailing edge of the foil than at the midchord region to prevent inward migration of the vortex origins and to reduce the induced drag, the gradual tapering providing substantially no curvature of the surfaces in the chordwise direction aft of the chordpoint of maximum thickness to correspondingly reduce the differential pressure between the upper and lower surfaces and reduce the strength of the vortices produced thereby.