[특허]Minimum drag wing configuration for aircraft operating at transonic speeds

Minimum drag wing configuration for aircraft operating at transonic speeds 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-005/08
출원번호	US-0862286 (1977-12-19)
발명자 / 주소	Ishimitsu Kichio K. (Mercer Island WA) Van Devender Neal R. (Renton WA)
출원인 / 주소	The Boeing Company (Seattle WA 02)
인용정보	피인용 횟수 : 38 인용 특허 : 0

초록 ▼

A wing extension or tip fin is disclosed wherein the tip fin is joined to an aircraft wing to form a nonplanar wing configuration which minimizes induced drag during both low speed and high speed operation of an aircraft. The tip fin which is of generally trapezoidal geometry, extends streamwise along the end of the aircraft wing and is canted to project upwardly and outwardly therefrom. Additionally, the tip fin is twisted to toe-out relative to the freestream direction with the angle of twist varying along the lower portion of the tip fin length. Viewed from the side, the tip fin has a sweep angle at least equal to the sweep angle of the aircraft wings with the leading edge of the tip fin intersecting the wing tip chord at a position aft of the wing leading edge. A strake which extends along the upper surface of the wing from the wing leading edge to the tip fin leading edge, forms a smooth transition between the wing and tip fin. To provide maximum aerodynamic efficiency, the length and cant angle of the tip fin are established to reduce the induced drag of the wing-tip fin combination below that exhibited by the wing alone or by a conventional wing of area and span equivalent to that of the combined wing-tip fin. Interference and compressibility drag of the combined wing-tip fin is minimized by controlling the chordwise position of the tip fin and by the strake which not only provides an aerodynamically smooth wing to tip fin transition, but establishes a vortical flow pattern that maintains boundary layer attachment under high speed flight conditions. Further, the area of the tip fin is established for minimum profile drag, the variation in tip fin thickness ratio further minimizing interference drag and the tip fin twist compensates for spanwise loading on the wing to reduce induced drag.

대표청구항 ▼

A tip fin mountable to the outboard end of an aircraft wing to form a nonplanar wing configuration for reducing induced drag relative to that exhibited by the wing alone, said tip fin having first and second boundary surfaces contoured to define an airfoil section including a leading edge, a trailing edge, a root chord and a tip chord, said tip fin leading edge extending between said tip fin root chord and said tip fin chord at a first predetermined angle, said tip fin trailing edge extending between said tip fin root chord and said tip fin tip chord at a second predetermined angle, said tip fin tip chord having a length dimension less than that of said tip fin root chord, said tip fin being mountable to said aircraft wing with said leading edge of said tip fin being positioned outboard of said tip fin trailing edge to define a predetermined angle of incidence between the freestream flow direction of said aircraft wing and said tip fin root chord, said tip fin being twisted over at least the lower portion of the distance between said tip fin root chord and said tip fin tip chord to gradually decrease the angle of incidence between said tip fin leading edge and said freestream flow direction within said lower portion of said distance between said tip fin root chord and said tip fin tip chord, said tip fin extending upwardly and outwardly at a predetermined cant angle from said outboard end of said aircraft wing when said tip fin is mounted thereto with said tip root chord extending streamwise relative to said end of said wing, said first boundary surface of said tip fin being contoured along said tip fin root chord to form a smoothly radiused transition between the upper surface of said wing and said tip fin first boundary surface, said second boundary surface of said tip fin being contoured along said tip fin root chord to form a smoothly radiused transition between the lower surface of said wing and said tip fin second boundary surface, said tip fin including a strake having an aerodynamically contoured leading edge extending at a third predetermined angle between said tip fin root chord and a point along said tip fin leading edge that is intermediate said tip fin root chord and said tip fin tip chord, said third predetermined angle being selected to establish airflow vortices for maintaining boundary layer attachment along said radiused transition between said upper surface of wing and said tip fin second boundary surface during flight of said aircraft, said strake having first and second boundary surfaces extending from said leading edge of said strake with said first and second boundary surfaces of said strake respectively terminating at and being contoured to form a smooth transition with said first and second boundary surfaces of said tip fin, said strake being dimensioned and arranged for extending streamwise along the upper surface of said wing when said tip fin is mounted to said aircraft wing.

이 특허를 인용한 특허 (38)

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Chaussee, Julien; Paumes, Camille; Wijker, Norman; Alexander, Stuart, Wing tip device attachment apparatus and method.
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Zaman, AbuMuhammed A., Wing tip device for an aircraft wing.
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Theurich, Frank; Himisch, Jan, Wing tip shape for a wing, in particular of aircraft.
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Roman, Dino L.; Vassberg, John C.; Friedman, Douglas M.; Malachowski, Adam P.; Vegter, Christopher A., Winglet system and method.
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Minimum drag wing configuration for aircraft operating at transonic speeds 원문보기

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Minimum drag wing configuration for aircraft operating at transonic speeds 원문보기

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