CA2136000C - Wing with a wing grid as the end section - Google Patents
Wing with a wing grid as the end section Download PDFInfo
- Publication number
- CA2136000C CA2136000C CA002136000A CA2136000A CA2136000C CA 2136000 C CA2136000 C CA 2136000C CA 002136000 A CA002136000 A CA 002136000A CA 2136000 A CA2136000 A CA 2136000A CA 2136000 C CA2136000 C CA 2136000C
- Authority
- CA
- Canada
- Prior art keywords
- wing
- winglets
- grid
- main wing
- wing according
- 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.)
- Expired - Fee Related
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
- B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
- B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
- B64C23/076—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips the wing tip airfoil devices comprising one or more separate moveable members thereon affecting the vortices, e.g. flaps
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Wind Motors (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Prostheses (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Toys (AREA)
Abstract
The wing with the span (b) according to the invention has a main part (1), which has a substantially closed surface with respect to the flow (v) and is provided at its free end with an end section in the form of a wing grid. The wing grid has at least two parallel-staggered winglets (2). Such a wing grid as part of the wing span (b) takes over the intended profile cir-culation at the attachment point to the main part and subdiv-ides said circulation approximately uniformly over the winglets.
Thus, the same lift is produced in the end section with at least two winglets. Thus, for the wing the circulation distri-bution is more complete and the induced resistance is decreased.
An upper or lower limit for the action is obtained, as a function of whether as a result of the fixed wing grid for the entire wing a rectangular circulation distribution is produced or only for the part of the overall span replaced by the wing grid. Thus, for the wing with wing grid there is a correspon-ding reduction of the induced resistance as compared with a conventional wing without a wing grid for the same resulting aspect ratio.
Thus, the same lift is produced in the end section with at least two winglets. Thus, for the wing the circulation distri-bution is more complete and the induced resistance is decreased.
An upper or lower limit for the action is obtained, as a function of whether as a result of the fixed wing grid for the entire wing a rectangular circulation distribution is produced or only for the part of the overall span replaced by the wing grid. Thus, for the wing with wing grid there is a correspon-ding reduction of the induced resistance as compared with a conventional wing without a wing grid for the same resulting aspect ratio.
Description
21~6c~~~
WING WITH A WING GRID AS THE END SECTION
The invention relates to a wing, whose main part has a surface around which there is a flow. .
According to the invention such a wing 'has at the end of the main part a wing grid as an end section. At the end of the main part on a chord t is attached the wing grid, which prod-uces the same specific lift per length unit of the wing spread or span as the main part at the fixing point. The wing can e.g.
be the wing of an aircraft or a propeller, or the sail or centreboard or drop keel of a boat, etc.
The construction of wings is always a compromise between the strength, which prefers a small aspect :ratio, and the induced resistance, which requires a large aspect ratio of the wing and together with the profile resistance determines the lift-drag (L/D) ratio.
For theoretical reasons it would be desirable to recover part of the energy given off to the flow medium in the lateral turb-ulence at the free wing tip and which determines the induced resistance, or to completely avoid the delivery thereof.
Prior Art.
A recovery with a propeller is known. A partial reduction with suitably shaped end plates is known. the prior art also dis-closes various arrangements of individual winglets (e.g. DE-OS
3242584) or several such winglets in series with a negative setting angle or incidence with respect to the wing chord (DE-OS 3621800), whose function is to obtain from the wing tip turbulence useful propulsion and/or life: force by individually adapted partial deflection.
It is also known to use a split flap-like subdivision of pref-erably the outer third of the length of a wing for improving ~~~saoa the efficiency (EP 282 830) by subdividing the boundary layer running length into laminar portions.
It is also known to subdivide the wing into parallel, grid-like individual wings with varying length (P'R 7612470, published under No. 2349494) for a better control. of the wing action.
It is also known to use so-called air waffles, namely a Wing grid with overlapping winglets, as wings (DE 37 30 798), whose overall setting angle during flight and whilst maintaining the setting angle of the winglets is modified for changing the lift up to an end position in which the winglets are in overlapping contact.
The replacement of an aircraft wing by an overlapping wing grid over the entire span is also known (DE 2657714), which also brings about a rise in efficiency.
It is also known in a device by means of one or more spiral loops distributed uniformly over the main wing chord to take over the local profile circulation and deliver it at its outer end (Aviation Partners, Dr. Louis B. Gratzer, Seattle).
Invention.
The problem to be solved according to the invention is to so design or supplement the wing tip of a deep, short wing with a small aspect ratio that as a result lift-drag ratios can be obtained, which would otherwise only be achieveable with much more slender wings having a large aspect ratio, or to reduce the L/D ratios of an existing wing by reducing the induced resistance.
This problem is solved by the above-described wing with a wing grid and as defined as an invention in the claims.
2136~~~
WING WITH A WING GRID AS THE END SECTION
The invention relates to a wing, whose main part has a surface around which there is a flow. .
According to the invention such a wing 'has at the end of the main part a wing grid as an end section. At the end of the main part on a chord t is attached the wing grid, which prod-uces the same specific lift per length unit of the wing spread or span as the main part at the fixing point. The wing can e.g.
be the wing of an aircraft or a propeller, or the sail or centreboard or drop keel of a boat, etc.
The construction of wings is always a compromise between the strength, which prefers a small aspect :ratio, and the induced resistance, which requires a large aspect ratio of the wing and together with the profile resistance determines the lift-drag (L/D) ratio.
For theoretical reasons it would be desirable to recover part of the energy given off to the flow medium in the lateral turb-ulence at the free wing tip and which determines the induced resistance, or to completely avoid the delivery thereof.
Prior Art.
A recovery with a propeller is known. A partial reduction with suitably shaped end plates is known. the prior art also dis-closes various arrangements of individual winglets (e.g. DE-OS
3242584) or several such winglets in series with a negative setting angle or incidence with respect to the wing chord (DE-OS 3621800), whose function is to obtain from the wing tip turbulence useful propulsion and/or life: force by individually adapted partial deflection.
It is also known to use a split flap-like subdivision of pref-erably the outer third of the length of a wing for improving ~~~saoa the efficiency (EP 282 830) by subdividing the boundary layer running length into laminar portions.
It is also known to subdivide the wing into parallel, grid-like individual wings with varying length (P'R 7612470, published under No. 2349494) for a better control. of the wing action.
It is also known to use so-called air waffles, namely a Wing grid with overlapping winglets, as wings (DE 37 30 798), whose overall setting angle during flight and whilst maintaining the setting angle of the winglets is modified for changing the lift up to an end position in which the winglets are in overlapping contact.
The replacement of an aircraft wing by an overlapping wing grid over the entire span is also known (DE 2657714), which also brings about a rise in efficiency.
It is also known in a device by means of one or more spiral loops distributed uniformly over the main wing chord to take over the local profile circulation and deliver it at its outer end (Aviation Partners, Dr. Louis B. Gratzer, Seattle).
Invention.
The problem to be solved according to the invention is to so design or supplement the wing tip of a deep, short wing with a small aspect ratio that as a result lift-drag ratios can be obtained, which would otherwise only be achieveable with much more slender wings having a large aspect ratio, or to reduce the L/D ratios of an existing wing by reducing the induced resistance.
This problem is solved by the above-described wing with a wing grid and as defined as an invention in the claims.
2136~~~
According to the invention a partial span of the wing is replaced by a wing grid formed from at least two parallel, stag-gered winglets. This wing grid takes over the circulation around the wing profile fully on that side in which the wing passes into the fixed wing grid. The upper limit used as a basis is the circulation around the wing profile without any wing tip turbulence, which is replaced by the wing tip turbul-ence of the wing grid. The winglets of: the wing according to the invention are preferably twist-free and preferably the set-ting angles thereof are jointly or individually adjustable.
The solution of the problem according to the invention extends much further than the known solutions, in which by individually adapted winglets the wing tip turbulence is utilized and avoids the incomplete use of the effect according to known solutions with several fixed winglets.
Compared with a closer solution with a regular wing grid and at least three winglets, according to the preferred embodiment only at least two winglets are used, but must be staggered in parallel. The effect of the wing according to the invention could at best be achieved with a known split flap if the profiles and setting angles of the split flaps could be adap-ted over their length to a given degrees of splitting. The nega-tively acting, maximum grid spacing in known split flap ends is avoided with the parallel staggering of the winglets accor-ding to the invention.
The wing grid of the wing according to the invention with its parallel-staggered, at least two winglets can in the case of setting angle changes follow up the incident flow v as a whole, without having to modify the grid parameters and, particularly when there is no overlapping, can be effective without any follow-up for a large setting angle range. However, e.g. an air waffle, which represents the complete bearing surface of ~~3~a~4~
several individual wings, during its adjustment modifies the multiplane effect and the overlapping winglets lead to a narrow range of the setting angle usable for an adjustment. As oppo-sed to the wing according to the invention, with such a waffle it is not possible to achieve in the case of a wing with a small aspect ratio a smaller L/D ratio. The known, overlapping wing grid over the entire span, which i:n fact represents a multiplane with a small stagger, does not give a multiplane effect for the induced resistance, but instead a considerable increase in the profile resistance. The wind split up in grid-like manner and with a varying length o:E the individual wings also suffer from this disadvantage, because the individual wings also extend over the entire span. Compared with a wing with the known spiral loops for leading off the local profile circulation, the same effect is exerted by the wing according to the invention with a planar and therefore less cross-wind-sensitive and constructionally simpler arrangement.
If the at least two winglets of the wing according to the invention are connected with the aid of a retaining frame, there is an approximation to the action of a wing grid formed from several winglets without a retaining frame and a wing grid formed from at least three winglets is supplemented and exten-ded by an effective range.
As only the staggering of the winglets of the wing according to the invention must be in parallel, wherE~as the other grid para-meters regarding the circulation distribution to be removed can be adapted over the chord of the main part, a further optimiz-ation of the adaptation to the conditions of the main part is possible.
Embodiments of the wing according to the: invention are descr-ibed in greater detail hereinafter relative to the drawings, wherein show:
~_. 21.~G~aO
Fig. 1 The conventional force distribution in lift and resistance on the incident flow wing profile for defining the L/D ratio.
Fig. 2 The basic diagram of the wing according to the invention with a wing grid attached to the conven-tional main part as the bE~aring section with the same specific lift per length unit of the span at the attachment point to the main part.
Fig. 3 An exemplified embodiment of the wing grid with retaining frame.
Fig. 4 A wing grid, which can be extended from the main part .
Fig. 5 A use of the wing according to the invention on the main sail of a yacht.
Fig. 6 A use of the wing according to the invention on an aircraft.
Fig. 7 A sweepback of the wing grid to the flow direction, as required by high subsonic speeds.
Fig. 8 The designations of the grid parameters of a general wing grid in a vertical sectional representation.
Fig. 1 shows the incident flow v of a wing profile with finite span or wingspread, a lift A and a resistance W being obtained.
The ratio of these forces gives the L/D ratio according to the f ormu la L/D ratio = tg( pC) - W/A
in which W = W1 + Wr = induced resistance + frictional resistance.
~~~saao The wing according to the invention reduces the part WI of the induced resistance caused by the flow round the wing tips.
Fig. 2 shows a wing with a main part l, which begins at the symmetry plane in the centre. To the main part 1 is attached a portion of the total bearing wing span b with a wing grid com-prising winglets 2 of similar orientation and parallel stagg-ering. The winglets 2 are placed over the chord t.
The desired action for the design point. is obtained if the circulation in the profile sections S a.nd S' is of the same size and similar rotation axis and if the winglets form a wing grid, which zonally takes over the circulation along the chord of the main part. The attachment point of the wing grid is, as stated, constructed as a partition 3.
Fig. 3 shows an exemplified embodiment of the wing according to the invention, in which the outer ends of the winglets 2 are held in a retaining frame 4, which has the function of a clos-ing face for the flow distribution.
Fig. 4 is an exemplified embodiment of the wing according to the invention with an extendable wing grid, whose winglets are fixed to a plate 6 and are moved as an entire group. Embodi-ments are also conceivable with individually extendable wing-lets.
Fig. 5 shows as a use of the wing according to the invention a yacht 8 with a mast 7 and a mainsail 1, whose upper edge is provided with a wing grid (2, 4).
Fig. 6 shows an exemplified embodiment of the wing according to the invention with a wing grid constituted by winglets 2, part-ition 3 and retaining frame 4, the winglets being extendable as a group with the plate 6 from the main part 1 of a triangular aircraf t wing .
,r.~ 2~3fi0fl~
_, _ Fig. 7 shows the use of a swept back wing grid, such as is e.g.
used for high subsonic speeds. As a function of the design of the winglets 2, as a function of the setting angle and profile thickness of the winglets, the resulting sweepback designed for the same Mach number differs from the sweepback of the main wing part 1.
Fig. 8 shows the designations of the grid parameters of a wing grid for a wing according to the invention. The staggering direction 0 of the wing grid to the incident flow direction v can be chosen at random and what is decisive for the action is the setting angle j3, based on the chords, as shown in the drawing, and more specifically the zero incident flow angle of the winglets, the length of the chords c and the staggering s transversely to the incident flow direction v. The quantity g is the grid spacing in the staggering direction 0.
The solution of the problem according to the invention extends much further than the known solutions, in which by individually adapted winglets the wing tip turbulence is utilized and avoids the incomplete use of the effect according to known solutions with several fixed winglets.
Compared with a closer solution with a regular wing grid and at least three winglets, according to the preferred embodiment only at least two winglets are used, but must be staggered in parallel. The effect of the wing according to the invention could at best be achieved with a known split flap if the profiles and setting angles of the split flaps could be adap-ted over their length to a given degrees of splitting. The nega-tively acting, maximum grid spacing in known split flap ends is avoided with the parallel staggering of the winglets accor-ding to the invention.
The wing grid of the wing according to the invention with its parallel-staggered, at least two winglets can in the case of setting angle changes follow up the incident flow v as a whole, without having to modify the grid parameters and, particularly when there is no overlapping, can be effective without any follow-up for a large setting angle range. However, e.g. an air waffle, which represents the complete bearing surface of ~~3~a~4~
several individual wings, during its adjustment modifies the multiplane effect and the overlapping winglets lead to a narrow range of the setting angle usable for an adjustment. As oppo-sed to the wing according to the invention, with such a waffle it is not possible to achieve in the case of a wing with a small aspect ratio a smaller L/D ratio. The known, overlapping wing grid over the entire span, which i:n fact represents a multiplane with a small stagger, does not give a multiplane effect for the induced resistance, but instead a considerable increase in the profile resistance. The wind split up in grid-like manner and with a varying length o:E the individual wings also suffer from this disadvantage, because the individual wings also extend over the entire span. Compared with a wing with the known spiral loops for leading off the local profile circulation, the same effect is exerted by the wing according to the invention with a planar and therefore less cross-wind-sensitive and constructionally simpler arrangement.
If the at least two winglets of the wing according to the invention are connected with the aid of a retaining frame, there is an approximation to the action of a wing grid formed from several winglets without a retaining frame and a wing grid formed from at least three winglets is supplemented and exten-ded by an effective range.
As only the staggering of the winglets of the wing according to the invention must be in parallel, wherE~as the other grid para-meters regarding the circulation distribution to be removed can be adapted over the chord of the main part, a further optimiz-ation of the adaptation to the conditions of the main part is possible.
Embodiments of the wing according to the: invention are descr-ibed in greater detail hereinafter relative to the drawings, wherein show:
~_. 21.~G~aO
Fig. 1 The conventional force distribution in lift and resistance on the incident flow wing profile for defining the L/D ratio.
Fig. 2 The basic diagram of the wing according to the invention with a wing grid attached to the conven-tional main part as the bE~aring section with the same specific lift per length unit of the span at the attachment point to the main part.
Fig. 3 An exemplified embodiment of the wing grid with retaining frame.
Fig. 4 A wing grid, which can be extended from the main part .
Fig. 5 A use of the wing according to the invention on the main sail of a yacht.
Fig. 6 A use of the wing according to the invention on an aircraft.
Fig. 7 A sweepback of the wing grid to the flow direction, as required by high subsonic speeds.
Fig. 8 The designations of the grid parameters of a general wing grid in a vertical sectional representation.
Fig. 1 shows the incident flow v of a wing profile with finite span or wingspread, a lift A and a resistance W being obtained.
The ratio of these forces gives the L/D ratio according to the f ormu la L/D ratio = tg( pC) - W/A
in which W = W1 + Wr = induced resistance + frictional resistance.
~~~saao The wing according to the invention reduces the part WI of the induced resistance caused by the flow round the wing tips.
Fig. 2 shows a wing with a main part l, which begins at the symmetry plane in the centre. To the main part 1 is attached a portion of the total bearing wing span b with a wing grid com-prising winglets 2 of similar orientation and parallel stagg-ering. The winglets 2 are placed over the chord t.
The desired action for the design point. is obtained if the circulation in the profile sections S a.nd S' is of the same size and similar rotation axis and if the winglets form a wing grid, which zonally takes over the circulation along the chord of the main part. The attachment point of the wing grid is, as stated, constructed as a partition 3.
Fig. 3 shows an exemplified embodiment of the wing according to the invention, in which the outer ends of the winglets 2 are held in a retaining frame 4, which has the function of a clos-ing face for the flow distribution.
Fig. 4 is an exemplified embodiment of the wing according to the invention with an extendable wing grid, whose winglets are fixed to a plate 6 and are moved as an entire group. Embodi-ments are also conceivable with individually extendable wing-lets.
Fig. 5 shows as a use of the wing according to the invention a yacht 8 with a mast 7 and a mainsail 1, whose upper edge is provided with a wing grid (2, 4).
Fig. 6 shows an exemplified embodiment of the wing according to the invention with a wing grid constituted by winglets 2, part-ition 3 and retaining frame 4, the winglets being extendable as a group with the plate 6 from the main part 1 of a triangular aircraf t wing .
,r.~ 2~3fi0fl~
_, _ Fig. 7 shows the use of a swept back wing grid, such as is e.g.
used for high subsonic speeds. As a function of the design of the winglets 2, as a function of the setting angle and profile thickness of the winglets, the resulting sweepback designed for the same Mach number differs from the sweepback of the main wing part 1.
Fig. 8 shows the designations of the grid parameters of a wing grid for a wing according to the invention. The staggering direction 0 of the wing grid to the incident flow direction v can be chosen at random and what is decisive for the action is the setting angle j3, based on the chords, as shown in the drawing, and more specifically the zero incident flow angle of the winglets, the length of the chords c and the staggering s transversely to the incident flow direction v. The quantity g is the grid spacing in the staggering direction 0.
Claims (14)
- 7. A wing comprising the combination of a main wing part having a substantially closed surface, a distal end, a chord, a first predetermined span and a predetermined orientation and predetermined attack angle relative to incident fluid flow for producing lift; a tip portion at said distal end of said main wing part, said tip portion comprising a grid of at least two spaced-apart winglets having a second predetermined span, said grid being attached to said distal end of said main wing part and extending the same lift per span unit of undisturbed two-dimensional flow around the profile of the main wing at the attachment to the winglet nips of the grid, each of said winglets having substantially the same orientation relative to incident fluid flow as said main wing part, said second predetermined span being no greater than said first predetermined span, said winglets having an overlap ratio of winglet chord length to spacing from an adjacent winglet equal to less than one and a ratio of chord length to winglet spacing which is substantially constant along said winglet: span where said spacing is measured leading edge to leading edge, and said winglets being vertically staggered relative to each other along a line unidirectionally angularly separated from a plane containing the chord of the main wing part.
- 2. A wing according to claim 1 wherein said grid comprises four winglets.
- 3. A wing according to claim 1 wherein said line along which said winglets are staggered has an angle above a plane containing said chord of said main wing part substantially equal to or greater than a design angle of incidence of said main wing part.
- 4. A wing according to claim 1 wherein said winglets are twist-free.
- 5. A wing according to claim 1 and including means of extending and retracting said tip portion from and into said main wing part.
- 6. A wing according to claim 1 and including a retaining frame interconnecting distal ends of said winglets.
- 7. A wing according to claim 1 and including selectable individual parameters for individual ones of said winglets.
- 8. A wing according to claim 7 wherein said individual parameters for individual ones of said winglets include the length of each winglet chord, a flow angle for said winglets including zero incident flow angle, and staggering distance.
- 9. A wing according to claim 1 and including means for jointly varying the angle of fluid flow incidence to said winglets.
- 10. A wing according to claim 1 wherein said main wing part and said winglet grid have swept back leading edges, the sweep angles relative to an incident free stream direction being selected to allow subsonic operation at high subsonic Mach numbers, thereby avoiding drag divergence due to compressibility.
- 11. A wing according to claim 1 wherein said main wing part comprises a sail for a marine vessel and said tip portion is positioned at a top of said sail.
- 12. A wing according to claim 1 wherein said winglets have leading edges which are parallel with each other.
- 13. A wing according to claim 1 wherein said line along which said winglets are staggered is a straight line.
- 14. A wing according to claim 1 wherein said grid is attached to said main wing part with a connecting body having a flat surface facing said grid.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH1032/93-2 | 1993-04-05 | ||
| CH1032/93A CH684588A5 (en) | 1993-04-05 | 1993-04-05 | Wing with a wing grating as an end section in order to reduce the glide angle |
| CH3293/93-7 | 1993-11-02 | ||
| CH329393 | 1993-11-02 | ||
| PCT/CH1994/000067 WO1994022713A1 (en) | 1993-04-05 | 1994-03-30 | Wing with a wing grid as the end section |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2136000A1 CA2136000A1 (en) | 1994-10-13 |
| CA2136000C true CA2136000C (en) | 2001-10-30 |
Family
ID=25686435
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002136000A Expired - Fee Related CA2136000C (en) | 1993-04-05 | 1994-03-30 | Wing with a wing grid as the end section |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP0642440B1 (en) |
| AT (1) | ATE149933T1 (en) |
| CA (1) | CA2136000C (en) |
| DE (1) | DE59402023D1 (en) |
| WO (1) | WO1994022713A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ATE293565T1 (en) | 2000-11-10 | 2005-05-15 | Roche Ulrich La | WINGS WITH WING GRILLS AS END SECTIONS |
| DE102008027618A1 (en) * | 2008-06-10 | 2009-12-31 | Airbus Deutschland Gmbh | Device for forming aerodynamic vertebrae, as well as valve and wing with a device for forming aerodynamic vertebrae |
| DE102009011480A1 (en) | 2009-03-06 | 2010-09-09 | Thomas Dr. Gartner | Flexible high performance sail |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1466551A (en) * | 1921-12-06 | 1923-08-28 | Bristol Aeroplane Co Ltd | Aircraft, submarine, torpedo, and other totally immersed craft or structure |
| GB196410A (en) * | 1922-02-01 | 1923-04-26 | William Robert Douglas Shaw | Improvements in wings for aerial machines |
| GB846322A (en) * | 1956-08-24 | 1960-08-31 | Commw Of Australia Crown Solic | Lift augmenting means |
| FR2349494A1 (en) * | 1976-04-27 | 1977-11-25 | Ducout Marcel | Boat with sails formed of vertical panels - has vertical panels held to mast by horizontal ties and rotatable about longitudinal axes to give curved appearance to sail |
| US4671473A (en) * | 1984-11-08 | 1987-06-09 | Goodson Kenneth W | Airfoil |
-
1994
- 1994-03-30 EP EP94910313A patent/EP0642440B1/en not_active Expired - Lifetime
- 1994-03-30 AT AT94910313T patent/ATE149933T1/en not_active IP Right Cessation
- 1994-03-30 CA CA002136000A patent/CA2136000C/en not_active Expired - Fee Related
- 1994-03-30 DE DE59402023T patent/DE59402023D1/en not_active Expired - Fee Related
- 1994-03-30 WO PCT/CH1994/000067 patent/WO1994022713A1/en active IP Right Grant
Also Published As
| Publication number | Publication date |
|---|---|
| WO1994022713A1 (en) | 1994-10-13 |
| EP0642440A1 (en) | 1995-03-15 |
| EP0642440B1 (en) | 1997-03-12 |
| ATE149933T1 (en) | 1997-03-15 |
| DE59402023D1 (en) | 1997-04-17 |
| CA2136000A1 (en) | 1994-10-13 |
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