WO1987001088A1 - Profil aerodynamique - Google Patents

Profil aerodynamique Download PDF

Info

Publication number
WO1987001088A1
WO1987001088A1 PCT/GB1986/000502 GB8600502W WO8701088A1 WO 1987001088 A1 WO1987001088 A1 WO 1987001088A1 GB 8600502 W GB8600502 W GB 8600502W WO 8701088 A1 WO8701088 A1 WO 8701088A1
Authority
WO
WIPO (PCT)
Prior art keywords
chord
aerofoil
wingsail
range
trailing
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/GB1986/000502
Other languages
English (en)
Inventor
John Graham Walker
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to FI880826A priority Critical patent/FI880826A0/fi
Priority to DE8686904896T priority patent/DE3676702D1/de
Publication of WO1987001088A1 publication Critical patent/WO1987001088A1/fr
Priority to NO871646A priority patent/NO163441C/no
Priority to DK202087A priority patent/DK202087A/da
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H9/00—Marine propulsion provided directly by wind power
    • B63H9/04—Marine propulsion provided directly by wind power using sails or like wind-catching surfaces
    • B63H9/06—Types of sail; Constructional features of sails; Arrangements thereof on vessels
    • B63H9/061—Rigid sails; Aerofoil sails

Definitions

  • This invention relates to aerofoils for wingsails.
  • Wingsails used to propel marine or terrestrial vessels, generally require to be capable of operation on port or starboard tack. This may be achieved by having complex folding arrangements of asymmetrical aerofoils the camber of which can be reversed by extension and folding of separate sections.
  • the present invention is preferably utilised in wingsail systems that comprise a plurality of symmetrical aerofoil sections which can be angled with respect to one another to give cambered and slotted configurations and also self-setting configurations.
  • Figure 1 is a schematic outline of an aerofoil according to the invention.
  • Figure 2 is a schematic outline of a slotted wing assembly according to the invention.
  • Figure 3 is a schematic outline of the wing of Figure 2 in a cambered configuration
  • Figure 4 is a schematic outline superimposing the aerofoil sections of Figures 1, 2 and 3.
  • the aerofoil shown has a chord length C and a maximum thickness of 0.291 C- with a leading edge radius of 6.489% of C.
  • the overall shape follows that of the table of ordinates Table 1.
  • the trailing element 3 shown in Figure 2 has a leading edge radius of 10.625% of its chord with a maximum thickness of 30.42% of its chord occurring at approximately 25% along the chord from the leading edge.
  • the table of ordinates for the profile is given in Table 3.
  • the aerofoil of Figure 1 may be regarded as a basic member of the preferred family of wingsail profiles. It comprises a relatively high leading edge radius when compared with aerofoils for aircraft, and thickens relatively rapidly to reach a 90% thickness zone that commences at about 20% of the chord and continues to about 40% of the chord, the aerofoil then narrowing into the trailing portion and curvature undergoing an inflexion.
  • the second member of the family, aerofoil 2 of Figure 2 has a leading edge curvature that matches with the leading edge of the aerofoil of Figure 1, but is modified into a more abrupt trailing edge with almost no curvature from about two thirds of the way along the chord.
  • the trailing edges are flat, in a more general case they may only be substantially flat and may have a slight curve or a slight inflexion. If reference is made to Figure 3 it will be observed that the trailing edge of the aerofoil 2 is provided with a slat 4 which acts to extend the trailing edge. In practice the trailing edge of the leading section may be truncated for the pivot mounting of the slat.
  • the 90% thickness zone extends over a range of approximately 17% to 33% of the chord, most preferably in the range of 23% to 27% of the chord.
  • the 90% thickness zone may commence in the range of 10% to 25% of the chord and be contained within the range of 10% to 55% of the chord from the leading edge, most preferably being within the range 17% to 45%.
  • the maximum thickness may lie in the range of 20% to 40% but preferably is in the range of 25% to 30% of the chord.
  • the leading edge radius is preferably in the range of 5.5% to 7.5% of the chord, but may be in the range 5.5% to 12%.
  • the leading section (disregarding any flaps or slats) preferably has a shortened tail section with no inflexion so that the 90% thickness zone starts at about 19% to 23% of the chord.
  • the trailing section of compound wings preferably has a leading edge radius that lies in the upper end of the range as defined for single aerofoils. Table 4 gives the approximate preferred ranges in terms of chord % for the three wingsail aerofoils described above. In compound wingsails it is possible to modify the curvature at the end that is adjacent another aerofoil, or to modify the overall curvature and compensate in the other aerofoil.
  • Thickness Max. Thickness LE range length position % radius
  • Figures 2 and 3 represent an especially preferred compound wingsail according to the invention.
  • the trailing element 3 is mounted on a boom or booms pivotable about an axis 5 on the chord of the leading element 2.
  • Each of the main aerofoils 2 and 3 preferably have the same maximum thickness (although differing thickness is possible, the trailing section preferably having the larger thickness) of .170 C TQT where C TO ⁇ is the total chord defined from the leading edge of the leading section to the trailing edge of the trailing section with the aerofoils aligned as in Figure 2.
  • the leading element is shorter having a chord of .432C TO ⁇ an ⁇ the trailing section having a chord of .560C Q r.
  • the slat 4 has a length .076C TQT and in the fully cambered position shown in Figure 3 is deflected through 25° with an adjustment facility of 5.5°.
  • the preferred fully cambered configuration deflects the trailing section through 42° with the pivot of the trailing section positioned about 2/3 of the way along the leading section: in Figure 3 it is .278c TOT from the leading edge.
  • a main upright pivot axis for the compound wing passes through the zone of the centre of pressure of the leading element 2 and the wing is trimmed to the wind by an auxiliary aerofoil, normally a tail vane, which also has an aerofoil section in accordance with the invention.
  • a tail vane is usually a single aerofoil and does not have slats or an adjacent aerofoil it preferably has the leading and trailing profiles shown in Figure 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Profil aérodynamique présentant une section possédant une épaisseur totale maximum comprise entre 20% et 40% de la corde totale et une zone d'épaisseur de 90% qui s'étend sur au moins 17% et au plus 33% de la corde totale et se situe entre 105 et 55% le long de la corde. Dans un profil alaire composite aussi bien les éléments d'attaque que les éléments de fuite présentent cette section de base, mais la section d'attaque présente un bord de fuite plus abrupt alors que la section de fuite possède un nez arrondi.
PCT/GB1986/000502 1985-08-22 1986-08-22 Profil aerodynamique Ceased WO1987001088A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FI880826A FI880826A0 (fi) 1985-08-22 1986-08-22 Vingprofil.
DE8686904896T DE3676702D1 (de) 1985-08-22 1986-08-22 Aerodynamisches profil.
NO871646A NO163441C (no) 1985-08-22 1987-04-21 Vingeseil-aerofoil samt sammensatt vingeseilenhet omfattende slik aerofoil.
DK202087A DK202087A (da) 1985-08-22 1987-04-21 Planprofil til vingesejl

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB8521085 1985-08-22
GB858521085A GB8521085D0 (en) 1985-08-22 1985-08-22 Aerofoil

Publications (1)

Publication Number Publication Date
WO1987001088A1 true WO1987001088A1 (fr) 1987-02-26

Family

ID=10584188

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1986/000502 Ceased WO1987001088A1 (fr) 1985-08-22 1986-08-22 Profil aerodynamique

Country Status (8)

Country Link
EP (1) EP0259344B1 (fr)
JP (1) JPS63501355A (fr)
AU (1) AU597904B2 (fr)
DE (1) DE3676702D1 (fr)
DK (1) DK202087A (fr)
FI (1) FI880826A0 (fr)
GB (1) GB8521085D0 (fr)
WO (1) WO1987001088A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2285960A (en) * 1994-01-31 1995-08-02 John Graham Walker Wingsail

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR940000045B1 (ko) * 1985-05-02 1994-01-05 쟝 마가렛 워커 날개형 돛 장치

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0061291A2 (fr) * 1981-03-19 1982-09-29 Walker Wingsail Systems plc Voile aérodynamique rigide
GB2102505A (en) * 1981-07-24 1983-02-02 United Technologies Corp Airfoil blade

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4432298A (en) * 1981-10-01 1984-02-21 Cudmore Patrick J Hydrofoil sailing craft
JPS59184096A (ja) * 1983-03-31 1984-10-19 Mitsui Eng & Shipbuild Co Ltd 複合帆

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0061291A2 (fr) * 1981-03-19 1982-09-29 Walker Wingsail Systems plc Voile aérodynamique rigide
GB2102505A (en) * 1981-07-24 1983-02-02 United Technologies Corp Airfoil blade

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
ABBOTT, Von DOENHOFF: "Theory of Wing Sections, Dover Publications, New York (US), pages 326, 327 see page 326, Naca 0021, columns 1, 2 page 327, Naca 0021, columns 1, 2 last but on line *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2285960A (en) * 1994-01-31 1995-08-02 John Graham Walker Wingsail
GB2285960B (en) * 1994-01-31 1998-02-04 John Graham Walker Monoplane and low thrust wingsail arrangements

Also Published As

Publication number Publication date
EP0259344B1 (fr) 1990-12-27
GB8521085D0 (en) 1985-09-25
DK202087A (da) 1987-05-20
FI880826A7 (fi) 1988-02-22
DK202087D0 (da) 1987-04-21
AU597904B2 (en) 1990-06-14
JPS63501355A (ja) 1988-05-26
EP0259344A1 (fr) 1988-03-16
DE3676702D1 (de) 1991-02-07
AU6280886A (en) 1987-03-10
FI880826L (fi) 1988-02-22
FI880826A0 (fi) 1988-02-22

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