WO1994025340A1

WO1994025340A1 - Propulsive airfoil device with very high aerodynamic efficiency

Info

Publication number: WO1994025340A1
Application number: PCT/FR1993/000422
Authority: WO
Inventors: Félix RODENAS-SOLA
Original assignee: Rodenas Sola Felix
Priority date: 1993-04-29
Filing date: 1993-04-29
Publication date: 1994-11-10

Abstract

The airfoil device of the invention with very high aerodynamic efficiency has a lower surface with a continuous profile and an upper surface with a discontinuous profile which reverse when tacking occurs. This device includes a central element (1) extending from the leading edge (7) to the trailing edge (8) and a flap assembly (2) overlying each side of the foremost half of the central element. This assembly (2) comprises two angularly mobile flaps (3) spaced from the central element (1). The flap which is mounted on the lower surface side lies against the central element (1) so that they form together a laminar profile. The flap (3) which is mounted on the upper surface side is deflected by the depression and presents, together with the central element (1), a discontinuous profile that forms a projection (3A) at the rear edge of the flap (3), which produces a compressed turbulence area that greatly increases the lift and partially converts the drag resistance into a propulsive force, even at a high angle of incidence.

Description

PROPULSION VEHICLE DEVICE WITH VERY HIGH AERODYNAMIC EFFICIENCY.

The present invention relates to a propulsion wing device with very high aerodynamic efficiency, the lower surface and the upper surface are reversed at the change of tack.

The traditional profile of a wing or sail causes on the upper surface a swirling bubble, detrimental to the flow of air, which can only be reduced at a moderate angle of attack, by blowing or suction of the boundary layer, acceleration by cracking effect or mechanical modification of the profile.

The object of the present invention is to overcome this drawback.

To this end, the airfoil device according to the invention of propulsion with very high aerodynamic efficiency comprising a leading edge and a trailing edge and of which the lower surface and the upper surface are reversed at the tack is essentially characterized by what it includes:

a central element extending from the leading edge to the trailing edge of the wing, articulated around a geometric axis AA ′ extending transversely to the direction of flow of the wind on the lower surface,

a system of flaps covering on either side half of the central element, from the leading edge towards the trailing edge of the airfoil, the flap system comprising two flaps arranged on either side of The central element and each extending from the edge of attack towards the trailing edge, each flap being angularly movable, around an axis coincident with the axis AA 'or else spaced parallel to the latter and this between a first position according to which it is pressed against the central element and its external face forms a part of the lower surface of the airfoil and a second position according to which it is angularly separated from said central element and its external face forms a part of the upper surface of the airfoil whose profile is discontinuous and present at the level of the rear edge of the flap, a projection located substantially midway between the leading edge and the trailing edge, said flap being disposed in the second position under the effect of the depression prevailing on the upper surface of the sails.

Under the effect of the wind pressure exerted on the lower surface of the airfoil, the flap of the flap system placed along the lower surface is pressed against the central element and forms with said central element a lower surface with a continuous profile.

Under the effect of the depression exerted on the upper surface of the airfoil, the other flap of the flap system is detached from the central element and forms with the central element an extrados with discontinuous profile having a projection, which creates a compressed swirling area significantly increasing the lift and transforming part of the resistance due to the drag into a forward force even under a large angle of attack of the wing.

To limit the angular movement of spacing of the flap disposed along the upper surface are provided in a another characteristic of the connecting struts connected to the two flaps and engaged freely in the holes of the central element.

According to the configuration defined above, the two flaps of the flap system are movable simultaneously in reverse, that is to say, when one of them passes from the first position to the second position 1'autre flap goes from second to first position.

In addition, each component is sometimes part of the upper surface, sometimes part of the lower surface.

According to another embodiment, the flaps of the flap system are movable independently of one another. For this purpose, the central element and the flap system are rigid and the central element, between the flap system has a central core and two housings on either side of this central core which has, along its front edge, a profiled nose forming the leading edge of the airfoil, the two flaps, mounted on either side of the central core, are each secured by their front edge to the nose of the central core.

According to their first position, the flaps each come to be disposed entirely in their housing bearing on the central core.

Under the effect of the depression at the level of the upper surface, the corresponding flap is made to pivot about an axis passing through its front edge to come to be arranged in the second position. According to this position, the flap is moved away from its housing and from the central core of The central element.

According to an additional feature a stop member is associated é _* each flap and secured to central 1'âme to limit 1'écartement angular component compared to

The central element.

Other benefits, purposes and features of

The invention will appear on reading the description of preferred embodiments given by way of nonlimiting examples with reference to the appended drawings in which:

FIG. 1 is a sectional view of a first embodiment of the canopy device according to the invention,

FIG. 2 is a sectional view of a second embodiment of the canopy device according to the invention,

FIG. 3 is a sectional view of the device according to a third embodiment,

FIG. 3 bis shows a variant of the wing device according to the invention,

FIG. 4 is a sectional view of the device according to a fourth embodiment,

FIG. 5 is a sectional view of the device according to a fifth embodiment,

FIG. 6 is a sectional view of the device according to a sixth embodiment,

FIG. 7 is a sectional view of the device according to a seventh embodiment,

- Figure 8 is a sectional view of the device according to an eighth embodiment.

As shown in Figures 1 to 8, the device of wing according to the invention comprises a central element 1 articulated around a geometric axis AA ′ and a system 2 of flaps covering on either side half of the central element 1 from the leading edge 7 towards the trailing edge

8, this flap system comprising two flaps 3 arranged on either side of the central element 1.

The wing device is orientable relative to the apparent wind direction by pivoting around the axis

AA '. At least the external face of each flap 3 is arched in particular in the presence of wind so that said face, when the flap is arranged in the first position forms with the corresponding face of the central element a continuous, regular profile, conducive to ensuring laminar flow.

The pivot axis AA ′ may be located in front of the leading edge 7, along this leading edge 7 or else between the leading edge 7 and the trailing edge 8.

In FIGS. 1 to 3 and 3a are shown wing devices of which the central element 1 and the shutter system are flexible and are constituted by sails with elastic slats 4,5 mounted in sheaths integral with the sails. The slats 4 of the central element are rectilinear and are spaced from each other and extend in

The interval between the two flaps 3 perpendicular to the axis AA '. The slats 5 of the system 2 of flaps are rectilinear and are arranged in each of the flaps 3 spaced from one another and perpendicular to the axis AA '. Under the effect of external stresses such as wind pressure exerted on the flap 3 of the lower surface and depression exerted on the flap of the upper surface, the slats 5 of these flaps are caused to bend elastically and the concavity of the slats 5 of one and the other flap is facing the central element 1.

The two flaps 3 are held by their rear region which is spaced from one another by the flexible or rigid spacers 6, these spacers being rigidly fixed by their ends to one and the other flaps 3. Furthermore, these spacers are each freely engaged in a hole made in the sail with batten constituting the central element 1.

In Figures 1 and 2 we can see that the flap system is formed by a continuous sail surrounding the central element 1 to form two flaps 3 and a leading edge 7, the part of the sail forming the leading edge being free of slats.

In Figure 1 we can see that the slats 4 of the central element 1 and the slats 5 of the shutter system 2 are connected by their front end to cambers 9 th sliding contact with a vertical cylindrical mast 10 extending along 1 ' geometric axis AA ', the axis of this mast being coincident with said axis AA'. According to this embodiment, the continuous sail of the flap system 2 is wound in front of the mast around profiled, rounded parts 11, to form the leading edge 7 of the airfoil device. These parts 11 are in sliding contact with the mast and in combination with the cambers 9 constitute a guide bearing in rotation of the airfoil device around the mast 10. Each flap is angularly movable around the front end of their respective slats.

In FIG. 2, it can be seen that the slats 5 of the shutter system 2 and the slats 4 of the central element are always connected by their front ends to cams 12 whose front part is rounded. The sail constituting the flap system is wound on the front part of the cambers to form the leading edge 7. According to this embodiment the cambers 12 are each secured by an articulation piece 13 to a slide 14 mounted to slide. in the longitudinal groove of a vertical mast 15. The axis of the joints 13 is coincident with

The axis AA ′ and the wing device is pivotally mounted around the axis of the joints 15. The flaps are each angularly movable around the front end of their respective slats. Holes will be made in the continuous sail forming the system 2 of flaps at the leading edge to allow the attachment of the articulation parts 13 to the archers 12.

This wing device allows reefing and lowering.

In Figure 3 there is shown a device according to a third embodiment. According to this embodiment the system 2 of flaps is formed by two sails with slats 5, each flap 3 being formed by a veil with slats 5. The central element 1 and the two flaps 3, by the front end of their slats 4 or 5, are removably mounted in longitudinal grooves of a profiled vertical mast 16 forming the leading edge of the wing and arranged along the axis AA '. More specifically, the axis AA 'passes through the longitudinal groove for fixing the central element. The flaps 3 are angularly movable around the front end of their respective slats 5. The mast 16 can pivot around its longitudinal axis.

This wing device also makes it possible to take ris and to lower, these operations being able to relate only to at least one of the three sails constituting the central element 1 and the two flaps 3. Furthermore, the flap system may not have spacers 6.

In FIG. 3a, a variant of the airfoil device according to the invention is shown.

The shutter system 2 is formed by two sails with slats 5 each sail with slats forming a shutter. The central element 1 and the two flaps, by the front end of their respective slats, are removably mounted in the camber grooves 27 each fixed to a slide 29 engaged in the longitudinal groove of a vertical mast 30, profiled, to form the leading edge.

The hinge axis AA ′ passes through the mast, which can be pivotally mounted. The two flaps pivot around the front end of their respective slats. This device also allows reefing and lowering. In addition, the flap system may not include spacers 6.

It should be noted that the system of flaps of the airfoil device according to the embodiments previously described forms a thick profile.

In Figure 4, there is shown a device for wing structure of which the central element 1 and the system 2 of flaps are rigid. According to this embodiment, the system 2 of flaps always forms a thick profile and is formed by a rigid metal or other wall wound around profiled spacers 17 to form the two flaps 3 and the leading edge 7 of the airfoil device. .

The rigid wall is fixed by any known means to the spacers. The two flaps thus formed are bent and the concavity of one is directed towards the concavity of the other.

The shutter system 2 is mounted in a notch 18 of rectangular shape made in the front half of the central element and is articulated in the notch 18 to a shaft 19 located behind the leading edge 7 and arranged along the 'axis AA'. This shaft 19 engages in holes made in the profiled spacers 17 and in

The central element. The edge of the rear edge of the notch

18 is concave and penetrates freely into a notch, for example rounded, formed along the rear edge of each spacer 17.

The device according to the invention can pivot around the shaft 19.

The two flaps 3 of the flap system 2 pivot simultaneously around the shaft 19 and the angular pivoting movement of the flap system 2 is limited in one direction and in the other by contact between the edge of the notch of each spacer. 17 with the concave rear edge of the notch 18.

According to this embodiment, each component is always movable between the first position and the second position according to which a projection 3A is formed on the upper surface.

According to this fourth embodiment, the shutter system can be pivotally controlled around the axis AA ′ by connecting rods 20 integral with the spacers 17 and linked to a common control shaft parallel to the leading edge and to the trailing edge and passing through the canopy device substantially halfway between the leading edge 7 and the trailing edge 8. By controlling the rods 20, operated by rotation of the control shaft, the flap system can be moved in one direction or in the other and the projection 3A can be formed on the lower surface of the airfoil device.

Furthermore, the wing device can alternatively pivot around the control shaft.

Wing devices have previously been described, the flaps 3 of which are movable simultaneously. In FIGS. 5 to 8 are illustrated wing devices, the flaps 3 of the system 2 of flaps of which are angularly movable independently of one another.

In FIGS. 5 to 7 are shown wing devices of which the central element 1 and the system 2 of flaps are rigid. According to these embodiments, the central element 1 between the system 2 of flaps has a central core 21 and two housings 22 on either side of this central core which has, along its front edge, a profiled nose 23 forming a leading edge of the wing. The two flaps 3, mounted on either side of the central core 21, are each secured by their edge front of the nose 23.

This nose 23 along its entire length can be traversed right through by a hole in which a mast can be engaged. The drilling axis and the axis AA 'will be merged and the canopy device will be able to pivot around the mast.

According to these embodiments, the axis AA 'of pivoting of the airfoil device can be located between the leading edge and the trailing edge at mid-distance for example, between the latter but the axis AA' can occupy d 'other positions. A hole will be practical in the central element along the axis AA 'and a mast will be engaged in this hole. The wing device will be made to pivot around the mast. The central element can also be mounted on a pivot. Each flap 23 is caused to pivot about an axis passing through its front edge between the first position in which it is completely disposed in the housing and resting on the central core and the second position in which it is spaced from the central core and extracted from its housing. The external face of each flap will be convex so that said face, when the flap is arranged in its first position forms with the corresponding face of the central element a continuous profile allowing laminar flow.

Preferably, a stop member is associated with each flap and fixed to the central core to limit the angular spacing of each flap relative to the central element.

According to the preferred embodiment, the stop member is a flexible link 24 which is tensioned when the flap with which it is associated is disposed in the second position, which limits its angular spacing movement.

Other stop members may be used, these members will be rigid.

Preferably as illustrated in FIGS. 5 to 7, each flap 3 is connected by its front edge in an elastic manner to the nose 23 of the central core 21 and in the absence of any external stresses such as pressure or vacuum forces from the wind, the flap is held in its housing, in its first position, by the effect of internal elastic forces at the connection.

As a variant, each flap will be secured to the nose 23 by means of an articulation piece.

In Figures 5 and 7 we can see that each component 3 is rooted on the nose 23 and forms a block with the latter. In FIG. 6, it can be seen that each flap has a front flange for fixing to the nose 23, this front flange being obtained, for example, by folding.

As a variant, the flaps 3 can be pivoted by connecting rods secured to each of the flaps 3 and fixed to control shafts.

In Figure 8 there is shown another embodiment of the wing device according to the invention. According to this embodiment, the central element 1 and the system 2 of flaps are flexible. The central element is formed by a thin wall of metal or other material, linked by its front edge to a profiled spar 25. The shutter system is formed by a thin wall, of metal or other, wound around the front spar to form a leading edge 7 and two shutters 3 always arranged on either side of the front half of

The central element 1. This metal wall is fixed in a known manner to the front spar 25 which develops along the axis AA '.

The wing device can be oriented by rotation of the front spar.

According to this embodiment, the external face of each flap is convex for the reasons stated above.

In the absence of any external stresses, each flap by the effect of the internal elastic forces of the wall of the flap system is arranged in its first position.

May also be provided with abutment members such as flexible links 24 or others to limit the movement of

The spacing of the flaps 3.

Finally the wing devices according to the figures

4 to 8 may include control flaps 26 articulated to the central element 1 and arranged along the trailing edge of the airfoil.

Furthermore, these canopy devices may be abutted or associated with a known canopy device not comprising a system 2 of flaps.

This wing device as described applies mainly to windsurfing sails, sailboats, aircraft as well as to the keels of boats, rudders, fins, keels sails and blades.

Claims

CLAIMS:

1. Propulsion wing device with very high aerodynamic efficiency comprising a leading edge (7) and a trailing edge (8) and of which the lower surface and the upper surface are reversed at the tack, characterized in that it comprises :

- a central element (1) extending from the leading edge to the trailing edge (8) of the airfoil, articulated around a geometric axis AA ′ and extending transversely to the direction of flow of the wind on the lower surface,

- a system (2) of flaps covering on either side half of the central element (1) from the leading edge (7) towards the trailing edge (8) of the wing, the system (2 ) of flaps comprising two flaps (3) arranged on either side of the central element (1) and each extending from the leading edge (7) towards the trailing edge (8), each flap ( 3) being angularly mobile, around an axis coincident with the axis AA 'or separated from it in parallel, and this between a first position in which it is pressed against the central element (1) and its external face forms part of the lower surface of the airfoil and a second position according to which it is angularly separated from the said element (1) and its external face forms a part of the upper surface of the airfoil whose profile is discontinuous and present at the edge rear of the shutter a projection (3A) lying substantially midway between the leading edge and the trailing edge, said shutter (3) is both disposed in the second position under the effect of the depression prevailing on the upper surface of the wing.

2. Wing device according to claim 1 characterized in that the two flaps (3) of the system (2) of flaps are connected to each other, by connecting spacers (6), freely engaged in bores of the central element (1), the said spacers (6), when the flap (3) disposed along the lower surface is pressed against

The central element (1), having the function of limiting the angular movement of separation of the other flap (3) relative to the central element (1).

3. Wing device according to claim 2 characterized in that the central element (1) and the system (2) of flaps are flexible and are each constituted by a sail with elastic slats (4), (5), that the veil constituting the shutter system (2) is continuous and surrounds the central element (1) so as to form a leading edge (7) and two flaps (3), that the slats (4) of the central element (1) are rectilinear and extend in the interval between the two flaps (3) perpendicular to the axis AA and that the slats (5) of the flap system are arranged in each of the flaps (3) perpendicularly to the 'AA axis'.

4. Wing device according to claim 3 characterized in that the slats (4) of the central element and the slats (5) of the flaps of the system (2) of flaps, by their front end are connected to cambers (9 ) in sliding contact with a cylindrical mast (10) extending along the axis AA ', the continuous sail forming the flap system, winding in front of the mast around rounded pieces (11), profiled, in sliding contact with the mast (10), to form the leading edge (7) of the wing.

5. Wing device according to claim 3 characterized in that the slats (4) of the central element

(1) and the slats (5) of the flaps are linked to cams (12) secured by articulation parts (13) to sliders (14) mounted to slide in the groove of a mast (15), l 'axis AA' and the axis of the articulations (13) being combined and the sail constituting the flap system winding around the rounded front part of the cambers

(12) to form the leading edge (7) of the wing.

6. Wing device according to claim 2 characterized in that the central element (1) and the system

(2) of flaps are flexible, that the central element is constituted by a veil with slats (4), elastic that the flaps (3) of the system (2) of flaps are each constituted by a veil with slats (5) elastic , that the slats (4) of the central element (1) are rectilinear and extend in the interval between the flaps (3) and that the central element (1) and the two flaps (3) through 1 ' front end of their respective slats are mounted in grooves of a profiled mast (16) forming the leading edge (7) of the wing.

7. Wing device according to claim 2 characterized in that the element (1) and the system (2) of flaps are rigid, that the system (2) of flaps is formed by a rigid wall wound around profiled spacers (17) to form the two flaps (3) and the leading edge (7) of the airfoil device.

8. Wing device according to claim 7 characterized by rods (20) integral with the spacers (17) and linked to a control shaft.

9. Wing device according to claim 1 characterized in that the central element (1) and the system (2) of flaps are rigid, that the central element (1), between the flap system (2) has on either side of a central core (21) two housings (22), that this central core (21) has, along its front edge, a profiled nose (23) forming the leading edge (7) of the wing, that the two flaps (3), mounted on either side of the central core (21), are each secured by their front edge of the nose (23) of the central core (21) and each come in their first position in the corresponding housing (22) of the central core (21) while by pivoting around an axis passing through their front edge, they are arranged in their second position, the said flaps (3) in this second position are separated of their housing (22) and of the central core (21).

10. Wing device according to claim 9 characterized in that each flap (3) is connected by its front edge in an elastic manner to the nose (23) of the central core (21) and that it is maintained in its first position in particular by the effect of internal elastic forces at the level of the connection.

11. Wing device according to claim 9 or claim 10 characterized by abutment members associated with the flaps (3) and fixed to the central core (21) to limit the angular spacing of the flaps (3) relative to 1 'central element (1).

12. Wing device according to claim 1 characterized in that the central element (1) and the system (2) of flaps are flexible, that the central element (1) is formed by a thin wall connected by its front edge to a profiled spar (25) and that the flap system (2) is formed by a wall of small thickness wound around the front spar (25) to form a leading edge (7) and two flaps (3), said flaps (3) under the effect of their internal elastic force being maintained in their first position in The absence of any external requests.

13. Wing device according to any one of claims 1, 7, 8, 9, 10, 11,12 characterized by control flaps (26) articulated to the central element (1) and arranged along the trailing edge (8) of the wing.

14. Wing device according to any one of claims 2, 9, 10 characterized by control rods secured to each of the flaps and fixed to control shafts.

15. Wing device according to claim 1 or claim 2 characterized in that the central element (1) and the system (2) of flaps are flexible, that the central element (1) consists of a sail with slats (4) elastic, that the flaps (3) of the flap system each consist of a web with elastic slats (5), that the slats (4) of the central element are rectilinear and extend in the interval between the flaps 3, that the central element (1) and the flaps (3) engage by the front end of their respective slats in the camber grooves (27) each fixed to a slide (29) engaged in the groove longitudinal of a vertical mast 30 profiled leading edge of the airfoil device.