WO1992012049A1 - Plan de sustentation comprenant des parties a cambrures superieures et inferieures fixes et variables - Google Patents

Plan de sustentation comprenant des parties a cambrures superieures et inferieures fixes et variables Download PDF

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Publication number
WO1992012049A1
WO1992012049A1 PCT/US1991/000034 US9100034W WO9212049A1 WO 1992012049 A1 WO1992012049 A1 WO 1992012049A1 US 9100034 W US9100034 W US 9100034W WO 9212049 A1 WO9212049 A1 WO 9212049A1
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WO
WIPO (PCT)
Prior art keywords
airfoil
fixed
trailing edge
defining
edge
Prior art date
Application number
PCT/US1991/000034
Other languages
English (en)
Inventor
Larry Lee Smith
Original Assignee
Larry Lee Smith
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Larry Lee Smith filed Critical Larry Lee Smith
Priority to PCT/US1991/000034 priority Critical patent/WO1992012049A1/fr
Publication of WO1992012049A1 publication Critical patent/WO1992012049A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/44—Varying camber
    • B64C3/48—Varying camber by relatively-movable parts of wing structures
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • This invention relates to an airfoil having improved lift coefficients at operational angles of attack and more specifically the present inven ⁇ tion relates to an airfoil having upper camber portions that may be posi ⁇ tioned to form a single upper camber portion or several upper camber por ⁇ tions.
  • any airfoil design is two-fold; first to pro ⁇ quiz a greater amount of lift without adversely increasing drag and second to enable the airfoil to function at greater angles of attack without stalling.
  • a design suitable for producing substantial lift at ]ow air speeds inherently pro ⁇ depicts excessive drag at high air speeds and on the other hand a wing de- designed to fly with minimal drag at high air speeds generally fails to produce sufficient lift at low air speeds to maintain flight as during take-offs and landings. This latter condition results in the stalling of the wing as the angle of attack of the wing is increased in an effort to produce greater lift until the critical angle of attack is exceeded.
  • the prior art includes movable slots and/or flaps on the lead and trailing edges of the wing which change the cross sectional profile of the wing.
  • the slots and/or flaps may be adjusted during flight for optimum performance of the wing at various flight conditions. At high air speeds the slots and/or flaps are fully retracted to give the wing a relatively thin streamlined pro ⁇ file reducing the drag acting thereon. At lower air speeds the slots and/ or flaps are extended downward to produce a greater camber on the wing which permits the wing to develop greater lift along with greater drag.
  • slots and/or flaps thus increase the aircraft's operational angles of attack through which the aircraft can safely operate, but be ⁇ cause of L ⁇ e -l ⁇ c_t.-__. , JI_I U ili e en io.. oi ⁇ _he SIQLS and/or xla ⁇ * s is only advisable at relatively low air speeds and thus they are unable to improve the lift and stall characteristics of the wing at high cruising air speeds.
  • the present invention provides an airfoil with means of altering the upper surfaces thereof so as to optionally form a relatively thin stream ⁇ lined profile having a single continuously extending upper surface forming a positive upper camber portion and alternately forming a first upper sur ⁇ face extending rearwardly from the leading edge defining a positive upper camber portion and a second upper surface rearwardly of said first upper surface and defining a second variable upper camber portion.
  • FIG. 1 is a partial perspective view of an airfoil embodying the con ⁇ cept of the present invention shown in relation to the fuselage of a fixed- wing aircraft;
  • FIG. 2 is a cross section of the airfoil taken on line 2-2 of FIG. 1 and showing a portion of the airfoil in a first position;
  • FIG. 3 is a cross section of an airfoil with a step configuration and showing a portion of the airfoil in a second position; and, a member or variable flap from the lower camber.
  • FIG. 4 is a partial perspective view of an airfoil, a portion thereof being movable into and out of a cavity in the fuselage of a fixed-wing aircraft.
  • FIG. 5 is a cross section of an airfoil with a step configuration and showing another portion thereof in a second position.
  • An airfoil according to the concept of the present invention is dis ⁇ closed as an elongated wing member of a fixed wing aircraft and has a lead ⁇ ing edge and a trailing edge.
  • a laterally extending offset is formed in the upper surface of the airfoil so as to form first an second upper sm— faces, the first upper surface defining a generally positive upper camber portion and the second upper surface defining a generally negative camber portion.
  • a movable flap extends coextensively with the second upper sur ⁇ face and is movable above an uppermost position to below where it forms a continuation of the first upper surface definingan upper camber portion of the airfoil to a lowermost position where it forms a generally negative, positive, planar or variable upper camber portion.
  • FIG. 1 An airfoil according to the present invention is indicated generally by the numeral 10 in FIG. 1 illustrated as a wing member of a fixed-wing air ⁇ craft.
  • the airfoil generally includes a root section 11 by which it is secured to the fuselage 12 of the aircraft and a wing tip 13 defining the outer end of the wing member.
  • a leading edge 14 and a longi ⁇ tudinally displaced trailing edge 15 extend between the root section 11 and the wing tip 13 and together define the planform of the airfoil 10.
  • Control surfaces such as an aileron 16 and flap 17 may likewise be in ⁇ corporated in the airfoil 10.
  • a longitudinally extending offset 18 defined by a vertical surface is formed in the upper surface of the airfoil 10 and as illustrated it extends from the fuselage 12 to the wing tip 13 and it will be appreciated that it need not extend completely therebetween.
  • the airfoil incorporating the laterally extending offset 18 is described in US. Pat. No.4,606,519 issued Aug.
  • the airfoil of said patent disclosed first and second fixed upper sur ⁇ faces of the airfoil separated by an offset forwardly of the trailing edge of the airfoil so as to be positioned on different vertical elevations whereas the airfoil of the present invention, see FIG. 2, has a leading edge 14 and a first fixed upper surface 20 extending between the leading edge 14 and the offset 18 and a second upper surface 21 extending between the offset 18 and the trailing edge 15 of the airfoil.
  • a member or flap 19 extends between the offset 18 and the trailing edge 15 and is hingedly affixed to the airfoil at or adjacent the trailing edge 15, the member or flap 19 being movable in an arc based on the point of attachment thereof with the trailing edge 15 of the airfoil.
  • the airfoil is provided with means 22 which may be mechanical, hydraulic, or pneumatically actuated for moving the member or flap 19 vertically so that it may be positioned in a first upper position as shown in broken lines and the reference numeral 19 A where it forms s continuous extension of the first upper surface 20 of the airfoil as it extends therefrom to the trailing edge 15 and as the member or flap 19 may be bowed transversely, it may be bowed by mechani ⁇ cal, hydraulic or pneumatically actuated means to form an extension of the irst fixed upper surface of the airfoil to comprise a generally positive or generally negative, or planar, or variable upper camber portion or it may be pre-bowed.
  • flap 19 may be lowered by the means 22 to the position on the solid line 19 where if it is planar it will form a generall negative, positive, planar or var ⁇ iable upper camber portion of the airfoil. Alternately it may be positioned at various locations above and between said upper and lower positions.
  • FIG. 3 of the drawings a cross section of an airfoil similar to that of FIG. 2 may be seen and wherein a leading edge 23 and a trailing edge 24 define the width of the airfoil and a first upper section 25 extending rearwardly from the leading edge 23 forms a positive upper camber portion terminating at an offset stepped configuration 26 running longitudinally of the airfoil and incorporating a first vertical surface 27 and a second horizontally spaced vertical surface 28 connected by a trans ⁇ versely arched substantially horizontally disposed section 29.
  • the second vertical surface 28 is located at the forward edge of a second upper sur ⁇ face 30 which if bowed upwardly forms a second positive upper camber portion and if planar or bowed downwardly intermediate it edges, forms a negative upper camber portion.
  • a member or flap 31 is hingedly affixed to the airfoil adjacent the trailing edge 24 thereof and extends forwardly thereof and is movable from a lowermost portion adjacent the second upper surface 30 to an uppermost position shown in broken lines 31A where it forms a continuation of the first upper section 25 of the air ⁇ foil.
  • the member or flap 31 is hingedly affixed to the airfoil at the trailing edge 24 thereof and the horizontally dis ⁇ posed section 29 forms the middle step in a stepped configuration defined by the first vertical surface 27 and second vertical surface 28 .
  • the forward edge of the member or flap 31 may be retractable.
  • a vertically movable body may form the offset step 26 which is movable from the posi ⁇ tion shown in solid lines in FIG. 3 to the upper broken line 31A by mechan ⁇ ical, hydraulic, or pneumatically actuated means 32.
  • the member or flap 31 may be moved above 19A of FIG. 2 by -means 33 which may be mechanical, hydraulic, or pneumatically actuated.
  • the member or flap 32 in uppermost position extends the first upper surface 25 forming a positive upper camber portion, the offset step 26 wit i h arched middle portion there ⁇ of forming a second positive camber portion, and the second upper sur ⁇ face 30 if bowed upwardly forming a third positive upper camber por ⁇ tion or if planar or bowed downwardly intermediate its edges forming a negative upper camber portion.
  • a member or flap 36 is hingedly affixed to the airfoil adjacent or forward of the trailing edge 24 thereof and extends forwardly thereof and is movable in an arc from the trailingward surface defining a lower camber of the airfoil.
  • the airfoil is provided with means 37 which may be mechanical hydraulic or pneumatically actuated for moving the member or flap 36.
  • the improvement in airfoils as herein disclosed incorporates a substantial improvement in the aerodynamic characteristics thereof occasioned by the discontinuity generated by the offset in the upper surface of the airfoil and additionally and most importantly the ability of the structure of the present invention to directly control the degree of aerodynamic improvement and/or lift or unobstructed airflow with respect to such an airfoil through the use of the movable members or flaps positioned in the airfoil immediately rearwardly of the offset formed therein.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Plan de sustentation (10) dont les caractéristiques aérodynamiques ont été améliorées, comprenant un bord d'attaque (14) et un bord de fuite (15) espacés l'un de l'autre de manière longitudinale. Une surface inférieure continue du plan de sustentation (10) forme une cambrure inférieure s'étendant entre le bord d'attaque (14) et le bord de fuite (15) et comprenant un élément ou un volet situé à l'arrière (36). La surface supérieure du plan de sustentation (10) comporte une première surface supérieure fixe (20) s'étendant vers l'arrière depuis le bord d'attaque (14) et se terminant par un renfoncement (18), ainsi qu'une deuxième surface supérieure (21) qui s'étend vers l'arrière depuis ce renfoncement et qui est mobile entre une première position (19A) définissant une première partie de cambrure supérieure du plan de sustentation (10) et une deuxième position (19) définissant une deuxième partie de cambrure supérieure, au moyen d'un ensemble de paliers ou d'éléments à charnières.
PCT/US1991/000034 1991-01-02 1991-01-02 Plan de sustentation comprenant des parties a cambrures superieures et inferieures fixes et variables WO1992012049A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US1991/000034 WO1992012049A1 (fr) 1991-01-02 1991-01-02 Plan de sustentation comprenant des parties a cambrures superieures et inferieures fixes et variables

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US1991/000034 WO1992012049A1 (fr) 1991-01-02 1991-01-02 Plan de sustentation comprenant des parties a cambrures superieures et inferieures fixes et variables

Publications (1)

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WO1992012049A1 true WO1992012049A1 (fr) 1992-07-23

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000017046A1 (fr) * 1998-09-24 2000-03-30 Raimo Hirvinen Procede destine a modifier l'angle d'attaque maximum d'un profil
EP1558848A2 (fr) * 2002-06-21 2005-08-03 Darko Segota Procede et systeme de regulation de l'ecoulement de fluides externes et internes

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1194878A (en) * 1916-08-15 Aebofoixi
GB192568A (en) * 1922-01-03 1923-02-08 Albert Eustace Short Improvements in the wings and other aerofoils for aircraft
US1918897A (en) * 1932-05-16 1933-07-18 Colburn Lloyd Airplane wing
US2156403A (en) * 1937-03-13 1939-05-02 Cie Des Avions Hanriot Lateral control surfaces of airplanes
DE2361210A1 (de) * 1973-12-06 1975-06-12 Ball Brothers Res Corp Flugzeugtragfluegel
US4606519A (en) * 1984-08-06 1986-08-19 Fertis Demeter G Airfoil

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1194878A (en) * 1916-08-15 Aebofoixi
GB192568A (en) * 1922-01-03 1923-02-08 Albert Eustace Short Improvements in the wings and other aerofoils for aircraft
US1918897A (en) * 1932-05-16 1933-07-18 Colburn Lloyd Airplane wing
US2156403A (en) * 1937-03-13 1939-05-02 Cie Des Avions Hanriot Lateral control surfaces of airplanes
DE2361210A1 (de) * 1973-12-06 1975-06-12 Ball Brothers Res Corp Flugzeugtragfluegel
US4606519A (en) * 1984-08-06 1986-08-19 Fertis Demeter G Airfoil

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000017046A1 (fr) * 1998-09-24 2000-03-30 Raimo Hirvinen Procede destine a modifier l'angle d'attaque maximum d'un profil
EP1558848A2 (fr) * 2002-06-21 2005-08-03 Darko Segota Procede et systeme de regulation de l'ecoulement de fluides externes et internes
EP1558848A4 (fr) * 2002-06-21 2011-03-30 Darko Segota Procede et systeme de regulation de l'ecoulement de fluides externes et internes

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