Aircraft winglet design having a compound curve profile
An improved winglet design is presented for aircraft wherein the winglet configuration is well suited for aircraft wings having moderate to no aft swept, or wings having forward swept. The winglets ( 302 ) are located at the outer end of each wing ( 300 ) and curve upwardly as they extend outwardly from their intersection ( 304 ) with the wings ( 300 ). The curvature profile ( 303 ) of the winglets ( 302 ) when viewed from the rear (or front) of the aircraft at least approximates a specified curve profile made up of more than one curved section, e.g. the winglet trailing edge profile ( 305 ) having a perpendicular projection onto a plane normal to the winglet inner or root chord ( 342 ), said projection creating a winglet profile curve approximating a compound curve composed of two arc segment ( 306, 307 ). The two arc segments are tangent to each other at there point of connection ( 306 b, 307 a ) wherein the arc segment ( 306 ) at the lower portion of the winglet connects to the outer end of the wing ( 300 ) and is tangent with the wing's reference plane ( 331 ). This lower arc segment ( 306 ) of the winglet profile connects to and is tangent with a second arc segment ( 307 ) forming the profile of the upper portion of the winglet ( 302 ). A unique design specification for the plan form or developed shape of the winglet that is suitable for wings having nominal (less than 15 degrees) aft sweep, or have neutral, or forward sweep is also provided.
1. An aircraft including a central fuselage and a pair of wings statically secured to the sides of the fuselage, each wing comprising:
an inner end secured to the fuselage, an outer end, a leading edge, and a trailing edge; and
a winglet having an inner end, or transition, section, an upper, or soil, section; a leading edge and a trailing edge;
wherein the inner end of said winglet is connected to the outer end of said wing, and the leading and trailing edges of the winglet are continuations of the leading and trailing edges of the wing, respectively;
wherein when viewing the shape of the winglet in developed profile having a coordinate system y prime (y′), x prime (x′) (y′, x′ coordinate system) wherein the winglet developed span distance is in the y′ direction and the winglet developed airfoil section Chord lengths are in the x′ direction, and wherein for a specified y′ span location, the x single prime (x′) coordinate value is at the winglet Chord leading edge point, and the x double prime (x″) coordinate value is at the winglet Chord trailing edge point, the winglet section Chord length, CW, being defined as the x′ coordinate distance between the winglet leading edge point x′ and trailing edge point x″, and each of the wings' trailing edge, have a negative or forward sweep angel, gamma(γ), measured in degrees, and the winglet trailing edge is curved at least in part; and
wherein the intersection point of the trailing edge curve or a tangent line extension thereof of the upper, or sail, section of the winglet with the winglet reference chord line, CW=x″+x′, said winglet reference chord line being located at a span distance, y′, from the winglet root at y′=0, said intersection point is offset by a distance Cx, wherein Cx is defined as a ratio of the Winglet Root Chord length, CW root, at Y′=0, and said offset distance, Cx, is in the aft direction from a point of intersection of the wing's trailing edge line extension with the winglet reference chord line, (CW =x″−x′) at winglet span distance y′ measured in the developed profile and the point of intersection of the winglet trailing edge curve or tangent line extension thereof with the winglet reference chord line, CW, at winglet span distance y′ measured in the developed profile, wherein the magnitude of the amount of offset distance, Cx, between the two reference intersection points on the reference chord line, CW is within the range of values determined by the following:
Cx=G*CW root
Where: G=offset parameter; if gamma, (γ)<=0 deg:
G=−H* (( y′y 0′)/ CW root)*tan(γ), if γ<=0 deg
Where: H is a positive value between 0.3 and 0.9,
CWroot=Winglet Root Section Chord Length at winglet span distance y′=0
Cx =Winglet Upper or Sail Section Aft or x’ Offset Displacement Distance from the intersection point of the wing trailing edge line extension with the winglet reference chord line, (CW =x″−x′) at winglet span distance y′ measured in the developed profile and the point of intersection of the winglet trailing edge curve or tangent line extension thereof with the winglet reference chord line, CW, at winglet span distance y′ measured in the developed profile as a ratio of the Winglet Root Chord length, CWroot.
2. The aircraft containing a pair of wings of claim 1 , wherein when viewing the winglet in developed profile (y′, x′ coordinate system), the winglet trailing edge curve incorporates a linear segment, which linear segment or extension thereof is used to define the intersection point on the winglet reference chord line.
3. The aircraft containing a pair of wings of claim 1 ,
wherein the developed winglet reference chord, (CW=x″-x′), is located at a the outer end of the winglet transition section, y′=y3′ or start of the winglet sail section, said sail section being defined as having a linear aft tapered leading edge profile.
4. The aircraft containing a pair of wings of claim 1 ,
wherein the winglet non-developed profile when projected onto a plane perpendicular to the winglet root chord line is a composite curve comprised of a lower curve segment having a constant radius connected and tangent to a linear segment curve.
5. The aircraft containing a pair of wings of claim 4 ,
wherein one or both arc segment are replaced by a b-spline curve segment where the end points locations and end point tangencies of the b-spline curve segment are identical to those of the arc segment being replaced wherein the radius of curvature of the inboard or lower b-spine curve decreases monotonically from the winglet root to the intersection point of the two profile curves, and the radius of curvature for the outboard or upper b-spline curve is either constant or increases monotonically outboard of the intersection point to the winglet tip.
6. The aircraft containing a pair of wings of claim 1 ,
wherein the winglet non-developed profile when projected onto a plane perpendicular to the winglet root chord line is a composite curve comprised of a lower rho conic curve segment connected and tangent to a linear segment curve.
7. The aircraft containing a pair of wings of claim 1 ,
wherein the winglet non-developed profile when projected onto a plane perpendicular to the winglet root chord line is a composite curve comprised of a lower curve segment having a. constantly increasing curvature connected and tangent to a linear segment curve.
8. The aircraft containing a pair of wings of claim 1 ,
wherein the winglet non-developed profile when projected onto a plane perpendicular to the winglet root chord line is a composite curve comprised of a lower rho conic curve segment connected and tangent to a constant radius segment curve.
9. The aircraft containing a pair of wings of claim 1 , wherein the winglet non-developed profile when projected onto a plane perpendicular to the winglet root chord line is composed of two arc segments wherein the radius defining the lower arc segment has a value less than the radius defining the outer arc segment.
10. The aircraft containing a pair of wings of claim 1 , each wing having a winglet attached to the end of the wing, wherein each of the wings' trailing edge, have a negative or forward sweep angle, gamma (γ), when viewing the shape of the winglet in developed profile (y′, x′ coordinate system), and wherein a curve defining the winglet non-developed profile when projected onto a plane perpendicular to the winglet root chord line contains a reflex in curvature.
11. The aircraft containing a pair of wings of claim 1 , wherein H=0.63.