An airfoil having a main wing and a high-lift body, and an aircraft

Abstract

Disclosed and claimed is an airfoil and an aircraft, the airfoil including a main wing and a high-lift body. The high-lift body defines a recess. The airfoil further includes a sealing device having two sealing elements arranged in the recess. The sealing elements are plate-shaped, partially abut against the high-lift body and have side surfaces extending perpendicular to a common axis of rotation. When the high-lift body moves between a retracted position and a deployed position, the sealing elements rotate relative to the main wing and relative to each other such that: the overlap between the sealing elements is less when the high-lift body is in the deployed position than when the high-lift body is in the retracted position.

Description

Field of the Invention

[0001] The present invention relates to an airfoil for an aircraft. The airfoil includes: a main wing having a leading edge; and a high-lift body having a leading edge and a concave-convex cross-section transverse to its leading edge such that a recess is defined by the high-lift body and extends parallel to the leading edge of the high-lift body. The high-lift body is coupled to the main wing at a recessed portion provided in the leading edge of the main wing such that the recess faces the main wing. The high-lift body is selectively movable between a retracted position and a deployed position, wherein in the retracted position, the leading edge of the main wing and the leading edge of the high-lift body form a continuous common leading edge. The present invention also relates to an aircraft including such an airfoil. Background Art

[0002] DE 10 2011 105 912 A1 discloses an airfoil having a main wing, a high-lift body, and a coupling device. The high-lift body is movably arranged at the leading edge of the main wing and is movably coupled to the main wing by the coupling device. The coupling device includes several rods, and the high-lift body can be reversibly switched between a retracted position and a deployed position, for example, when a reduced flow velocity should be at least partially compensated.

[0003] It is known that the air flow passing through the airfoil not only causes lift force (lift) but also drag force (drag). The so-called "lift-to-drag ratio" (L / D) of the airfoil is particularly important. When the high-lift body is positioned in the deployed position, a gap is formed between the high-lift body and the main wing. It has been observed that air can flow through this gap between the high-lift body and the main wing along a direction substantially corresponding to the span direction of the main wing or parallel to the leading edge. Such a parallel flow increases the drag of the airfoil and does not contribute to the lift of the airfoil, that is, the lift-to-drag ratio is reduced due to the unexpected flow parallel to the leading edge of the main wing. Summary of the Invention

[0004] In view of the above problems, an object of the present invention is to improve the lift-to-drag ratio of an airfoil having a high-lift body.

[0005] This object is solved by an airfoil according to an embodiment of the present application. In addition, this problem is solved by an aircraft having such an airfoil as described in an embodiment of the present application.

[0006] In a first aspect, the problem is solved by an airfoil for an aircraft. The airfoil includes a main wing and a high-lift body, both the main wing and the high-lift body having leading edges. The high-lift body has a concave-convex cross-section transverse to its leading edge such that a recess is defined by the high-lift body. The recess extends parallel to the leading edge of the high-lift body. The high-lift body is coupled to the main wing at a recessed portion provided in the leading edge of the main wing such that the recess faces the main wing. The high-lift body is selectively movable between a retracted position and a deployed position, wherein in the retracted position, the leading edge of the main wing and the leading edge of the high-lift body form a continuous common leading edge. The airfoil further includes a sealing device having a first sealing element disposed in the recess defined by the high-lift body. The first sealing element is plate-shaped, rotatable relative to the main wing about a common axis of rotation, partially abuts against the high-lift body and has a side surface extending perpendicular to the common axis of rotation. The sealing device is coupled to the high-lift body such that: when the high-lift body moves between the retracted position and the deployed position, the first sealing element rotates relative to the main wing, wherein in the deployed position of the high-lift body, at least a portion of the gap formed between the main wing and the high-lift body in a plane extending perpendicular to the common axis of rotation is covered by the sealing device.

[0007] The deployed position of the high-lift body is the position to which the high-lift body is displaced from its retracted position. When the high-lift body is displaced or deployed from its retracted position or initial position, the high-lift body may sequentially pass through a number of different deployed positions or high-lift positions until it reaches the position of maximum displacement. In each of these deployed positions, the lift of the high-lift body is increased relative to the retracted state, which increases the overall lift of the airfoil.

[0008] The sealing device should be understood as a device that acts to prevent an air flow from passing along the spanwise direction of the main wing through the gap formed between the high-lift body and the main wing when the high-lift body is in the deployed space. In other words, the sealing device is arranged to prevent or at least reduce an air flow parallel to the leading edges of the main wing and the high-lift body from passing through the recess formed by the high-lift body.

[0009] For this purpose, the sealing device includes at least a first plate-shaped sealing element. The sealing element is disposed in the recess formed by the high-lift body. The sealing element is mounted to the main wing body such that the sealing element is rotatable relative to the main wing body about a common axis of rotation.

[0010] The sealing element is attached to the main wing such that the plane in which the sealing element extends, i.e., the plane in which the sealing element is plate-shaped, extends perpendicular to the common axis of rotation and is at least substantially perpendicular to the direction of extension of the leading edge of the high-lift body at the location where the sealing element contacts the high-lift body. In other words, the plate-shaped sealing element extends substantially perpendicular to the flow that flows through the gap between the main wing and the high-lift body in the spanwise direction or parallel to the leading edge of the main wing or the high-lift body.

[0011] In order to reduce or preferably prevent the parallel flow through the gap, the sealing device is functionally coupled to the high-lift body such that: when the high-lift body moves towards the deployed position, the sealing element moves with the high-lift body and blocks the flow path parallel to the leading edge of the main wing and the leading edge of the high-lift body or the high-lift device. Thereby the sealing element can block the entire gap between the high-lift body and the main wing. However, it may be sufficient that the gap is only partially blocked.

[0012] Unless explicitly stated to the contrary, the preferred embodiments of the airfoil described below can be combined with each other in any way.

[0013] In a preferred embodiment, the airfoil includes a guiding device that mechanically couples the high-lift body to the main wing, wherein a first sealing element is mechanically coupled to the guiding device. The guiding device is preferably rotatably coupled to the main wing, wherein the guiding device is adapted to rotate relative to the main wing about the common axis of rotation. In other words, the mechanical link between the high-lift body and the main wing, i.e., the guiding device, is coupled to the first sealing element such that the first sealing element follows the movement of the guiding device and thus the movement of the high-lift body.

[0014] It is further preferred to provide a connecting element that connects the first sealing element to the guiding device to drive the first sealing element. The connecting element preferably projects from the first sealing element in a direction extending parallel to the common axis of rotation.

[0015] In a preferred embodiment, the sealing device includes a second sealing element that is arranged in a recess defined by the high-lift body. The second sealing element is plate-shaped, capable of rotating relative to the main wing about the common axis of rotation and has a side surface extending perpendicular to the common axis of rotation. The first sealing element and the second sealing element are capable of rotating relative to each other about the common axis of rotation. The side surfaces of the sealing elements extend parallel to each other. When the high-lift body moves between the retracted position and the deployed position, the second sealing element rotates relative to the main wing, and the first sealing element and the second sealing element rotate relative to each other such that: when the first sealing element and the second sealing element are projected onto a plane extending perpendicular to the common axis of rotation, the overlapping portion between the first sealing element and the second sealing element is smaller when the high-lift body is in the deployed position than when the high-lift body is in the retracted position.

[0016] In other words, in a preferred embodiment, the sealing device comprises at least an additional second sealing element. The second sealing element is mounted to the main wing and is rotatable about the same common axis of rotation as the first sealing element. However, the second sealing element is rotatable not only relative to the main wing but also relative to the first sealing element. Thus, the first and second sealing elements can be arranged at different angles relative to each other. Preferably, the sealing elements are always in contact with each other such that there is no gap through which air can flow between the sealing elements. This contact can be formed, for example, by a seal which is fixedly attached to either the first or the second sealing element and which slides in contact with the other of the first and second sealing elements. Alternatively, two seals can be provided, each of which is fixedly mounted to one of the sealing elements and slides in contact with the other sealing element.

[0017] To reduce or preferably prevent the parallel flow through the gap, the sealing device is functionally coupled to the high-lift body such that when the high-lift body is moved to the deployed position, the sealing elements fan out and at least partially block the flow path parallel to the leading edge of the main wing and the leading edge of the high-lift body or high-lift device. The fanning out of the sealing elements is achieved by rotating both the first and second sealing elements about the common axis of rotation. However, since one of the sealing elements rotates through a greater angle than the other, a relative rotation of the sealing elements and fanning out of the elements occurs. Thus, the overlap between the first and second sealing elements is reduced, in particular the overlap of these sealing elements. Using a sealing device with at least two sealing elements which fan out when the high-lift body is moved from the retracted position to the deployed position advantageously allows reducing the space required for storing the sealing device when the high-lift body is in the retracted position.

[0018] It should be noted that the sealing elements can comprise more than two sealing elements as described above. All these sealing elements are rotatably attached to the main wing such that these sealing elements can rotate about a common axis of rotation or a common axis of rotation relative to the main wing device and relative to each other. Furthermore, the plurality of sealing elements can fan out such that when the high-lift body is moved to the deployed position, the overlap between the sealing elements is reduced. It should be noted that when more than two sealing elements are used, the overlap between two sealing elements which are not directly adjacent to each other can be reduced to zero without creating a gap between these sealing elements since the additional sealing elements can cover the gap.

[0019] In a preferred embodiment, the first sealing element and the second sealing element are connected via a first guiding track and a first connecting member guided in the first guiding track. The first guiding track preferably includes an upper end stop and a lower end stop, and the upper end stop and the lower end stop engage with corresponding first end stop bolts to limit the movement of the first sealing element and the second sealing element relative to each other. Preferably, when the first end stop bolt engages with either the upper end stop or the lower end stop of the first guiding track, the second sealing element is driven via the first end stop bolt. Thus, the first sealing element and the second sealing element can move relative to each other and are connected via the first guiding track, and the first connecting member is guided in the first guiding track. By providing end stops, the movement of the first sealing element or the second sealing element can be advantageously transmitted to the other of the first sealing element or the second sealing element to transmit the movement of one sealing element to the other sealing element. Thus, no additional drive means are required.

[0020] In an exemplary preferred embodiment, the first guiding track is fixedly attached to the second sealing element, and the first connecting member attaches the first sealing element.

[0021] Preferably, the first guiding track includes a second end stop that limits the movement of the first sealing element and the second sealing element relative to each other, wherein the second sealing element is preferably driven via the first connecting member when the first connecting member engages with the second end stop of the first guiding track. By providing two end stops, one of the sealing elements can be driven in two rotational directions about a common axis of rotation by the other sealing element.

[0022] Further preferably, a first seal is arranged on the first sealing element, wherein the first seal contacts the high-lift body, and / or a second seal is arranged on the second sealing element, wherein the second seal contacts the high-lift body. Thus, advantageously, a sealed engagement can be established between the sealing element and the high-lift body to further reduce unwanted and undesirable parallel flow. The seal is preferably attached to the sealing element. When the high-lift body moves between the retracted position and the deployed position, the sealing element slides along the surface of the high-lift body that bounds the sealing element towards the recess defined by the high-lift body. Disposing the seal on the sealing element reduces the effort required to correctly position the seal because it is not necessary to know the exact trajectory. In addition, shorter seals can be used because only the outer surface of the sealing element, rather than the entire trajectory of the sealing element on the inner surface of the high-lift body, needs to be covered with the seal.

[0023] In a further preferred embodiment, the second sealing element is connected to the main wing via a second guide track and a second connecting member guided in the second guide track, wherein the second guide track includes an upper end stop and a lower end stop, and the upper end stop and the lower end stop engage with corresponding second end stop bolts for restricting the movement of the second sealing element relative to the main wing. Using the guide track and the connecting member guide in the guide track connection between the second sealing element and the main wing, such as a guide block track connection, has the same advantages as using such a connection to connect the first sealing element and the second sealing element. Preferably, the second guide track is fixedly attached to the main wing, and the second connecting member is attached to the second sealing element.

[0024] In a preferred embodiment, the main wing includes a support surface perpendicular to the common axis of rotation and extending parallel to the second sealing element. The second sealing element is connected to the support surface via a second guide track and a second connecting member guided in the second guide track. When the second sealing element and the support surface are projected onto a plane extending perpendicular to the common axis of rotation, the overlap between the second sealing element and the support surface is smaller when the high-lift body is in the deployed position than when the high-lift body is in the retracted position. The support surface advantageously causes the sealing device to extend towards the main wing, thereby increasing the region of the gap between the main wing and the deployed high-lift body that is blocked from further flow. The support surface can be understood as extending the sector formed by the sealing elements of the sealing device. If the sealing device includes only the first sealing element, the first sealing element can be connected to the support surface via a second guide track and a second connecting member. In this case, the considerations regarding the connection of the second sealing element to the support surface also apply to the first sealing element.

[0025] Preferably, in the deployed position and the retracted position of the high-lift body, the second sealing element is in contact with the support surface of the main wing, and this contact is preferably provided by a third seal. Thus, the flow through the potential gap between the second sealing element and the support surface can be minimized.

[0026] In a further preferred embodiment, the airfoil includes a guiding mechanism for controlling the relative movement of the first sealing element and the second sealing element, the guiding mechanism including a guiding rod having two pivot points spaced apart from each other and from the mounting point, and the guiding rod is rotatably mounted to the main wing at the mounting point, wherein a first guiding link mechanically connects the first pivot point to the first sealing element, and wherein a second guiding link mechanically connects the second pivot point to the second sealing element. The guiding mechanism advantageously ensures that the first sealing element and the second sealing element rotate at different angles about the common axis of rotation and thus fan out.

[0027] Preferably, the guiding rod is rotatably mounted on the support surface.

[0028] According to another preferred embodiment, the high-lift body is a drooping nose. This embodiment has the advantage of increasing the lift generated when the high-lift body is in the deployed position.

[0029] On the other hand, the present invention provides an aircraft including an airfoil according to any one of the foregoing embodiments, by which the lift-to-drag ratio of the airfoil can be improved. Preferably, the high-lift body is arranged between the fuselage of the aircraft and the engine supported by the airfoil. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Other advantages of the airfoil and the aircraft according to the present invention and its preferred embodiments will become apparent from the accompanying drawings. These drawings schematically show in part:

[0031] Figure 1 is a perspective view of a preferred example of the airfoil, wherein the high-lift body is positioned in the deployed position,

[0032] Figure 2 is Figure 1 another perspective view of the example shown, but wherein the high-lift body is positioned in the retracted position,

[0033] Figure 3 is Figure 1 and Figure 2 another perspective view of the example shown, wherein the high-lift body is positioned in the deployed position,

[0034] Figure 4 is Figures 1 to 3 a side view of the details of the example shown, wherein the high-lift body is positioned in the retracted position,

[0035] Figure 5 is Figures 1 to 4 a side view of the details of the example shown, wherein the high-lift body is positioned in the deployed position,

[0036] Figure 6 In particular Figures 1 to 5 a perspective view of the sealing device of the example shown, wherein the high-lift body is positioned in the retracted position,

[0037] Figure 7 In particular Figures 1 to 6 a perspective view of the sealing device of the example shown, wherein the high-lift body is positioned in the deployed position,

[0038] Figure 8 is a perspective view of the sealing device of another exemplary embodiment, wherein the high-lift body is positioned in the retracted position,

[0039] Figure 9 is Figure 8 a perspective view of the sealing device of, wherein the high-lift body is positioned in the deployed position,

[0040] Figure 10 is a perspective view of an exemplary embodiment of an aircraft according to the present invention, and

[0041] Figure 11 is a perspective view of a second exemplary embodiment of a part of an airfoil according to the present invention. Detailed Description

[0042] Figures 1 to 9 shows different schematic perspective views of a preferred example of the airfoil 1. Although Figure 1 shows a schematic view of the airfoil 1 in the deployed state - many details are not shown in this schematic view, but Figures 2 to 9 shows the same airfoil 1 in more detail. As will be explained in more detail in the following paragraphs, not all elements of the airfoil 1 are shown in all figures. In some figures, some elements of the airfoil 1 are not shown to provide an unobstructed view of other elements of the airfoil 1.

[0043] The airfoil 1 generally includes a main wing 2 and a high-lift body 4, the high-lift body 4 being shown in Figures 1 to 3 in a semi-transparent manner such that components of the airfoil 1 located behind the high-lift body 4 are visible. The high-lift body 4 is shown in Figure 2 , Figure 4 , Figure 6 and Figure 8 in the retracted position and in Figure 1 , Figure 3 , Figure 5 , Figure 7 and Figure 9 in the deployed position. Figures 4 to 9 Only a limited number of elements of the main wing 2 are shown, and the high-lift body 4 is not shown in Figures 6 to 9 for easier understanding.

[0044] The high-lift body 4 is a droop nose known in the prior art. The high-lift body 4 has a concave-convex cross-section transverse to its leading edge, thereby defining a recess 30. The recess 30 faces the main wing 2. The high-lift body 4 is preferably supported in a sliding manner on a recessed portion 29 of the main wing 2.

[0045] The main wing 2 and the high-lift body 4 are coupled to each other by means of a support element or an interconnecting element 3 (see Figures 4 to 9 ) such that the high-lift body 4 can move relative to the main wing 2 between the retracted position shown in Figure 2 , Figure 4 , Figure 6 , Figure 8 and the Figure 1 , Figure 3 , Figure 5, Figure 7 , Figure 9 selectively move between the deployed positions shown. The high-lift body 4 is arranged at the leading edge of the main wing 2 and, as best seen in Figure 2 , the high-lift body 4 is arranged within a recess 29 provided in the main wing 2 such that the high-lift body 4 forms a continuous leading edge together with the main wing 2 when in the retracted position. In the deployed positions as shown in Figure 1 and Figure 3 , the high-lift body 4 is displaced relative to the main wing 2 such that the high-lift body 4 projects from the main wing 2. Thereby a gap is created between the high-lift body 4 and the main wing 2 into which air can enter in a direction parallel to the leading edge of the main wing 2 and the leading edge of the high-lift body (see the continuous arrow 28 in Figure 1 ). If a flow is generated by the air flowing through the gap in this direction, the drag of the wing increases without an additional increase in lift. Therefore, the lift-to-drag ratio decreases.

[0046] To overcome this adverse effect, the airfoil 1 has a sealing device 5 which includes a first plate-shaped sealing element 6 and a second plate-shaped sealing element 7, the first plate-shaped sealing element 6 and the second plate-shaped sealing element 7 being supported by a support element 3 in a manner rotatable about a common axis of rotation A. Both of the sealing elements 6, 7 can rotate about the common axis of rotation A relative to the main wing 2 and also relative to each other, wherein the support element 3 is fixedly attached to the main wing 2. The first sealing element 6 partly abuts against the high-lift body 4 and has a first side surface 8 extending perpendicular to the common axis of rotation A. The second sealing element 7 also partly abuts against the high-lift body 4 and has a second side surface 9 extending perpendicular to the common axis of rotation A. The first sealing element 6 and the second sealing element 7 can be stabilized using a web 17 and a recess 10 structure.

[0047] The sealing device 5 is arranged to prevent or at least significantly reduce the air flow through the gap in a direction 28 extending parallel to the leading edge of the high-lift body 4 and the leading edge of the main wing 2. For this purpose, the movement of the sealing elements 6, 7 is associated with the movement of the high-lift body 4 between the retracted position and the deployed position. This association is arranged such that when the high-lift body 4 moves, both of the sealing elements 6, 7 rotate about the common axis of rotation A relative to the main wing 2 and also relative to each other. Due to the relative movement of the sealing elements 6, 7 relative to each other, the sealing elements fan out and cover a larger area of the gap compared to the case where the sealing elements do not fan out. Therefore, it is advantageous that the sealing elements 6, 7 can block a larger gap and only require a small space to store the sealing elements 6, 7 when the high-lift body 4 is in the retracted position.

[0048] The sealing elements 6, 7 are arranged in the recesses 30 and are connected to the main wing 2 and the high-lift body 4 in such a way that the overlap between the sealing elements 6, 7 is smaller in the deployed position of the high-lift body 4 than in the retracted position of the high-lift body 4. The overlap between the sealing elements 6, 7 is the area covered by both sealing elements 6, 7 when the sealing elements 6, 7 are projected onto an imaginary plane extending perpendicularly to the common axis of rotation A.

[0049] The first sealing element 6 is sealingly engaged with the high-lift body 4 via a first seal 12 fixedly attached to the first sealing element 6. Likewise, the second sealing element 7 is sealed relative to the high-lift body 4 using a second seal 13. The second seal 13 is mounted to the second sealing element 7. Both seals 12, 13 are in sliding contact with the inner surface of the high-lift body, which inner surface is delimited by a recess 30 defined by the high-lift body 4. The first sealing element 6 and the second sealing element 7 overlap each other in both the retracted position and the deployed position of the high-lift body 4. In addition, a seal (not shown) is provided to seal a potential gap between the sealing elements 6, 7.

[0050] The high lift body 4 is provided with Figures 2 to 5 The guide device 18 shown in FIG. is connected to the main wing 2. Figures 6 to 9 , the guide device 18 is not shown in order to provide an unobstructed view of the sealing device 5. The guide device 18 is generally arranged to guide the high-lift body 4 between the retracted position and the deployed position. The guide device 18 is rotatably mounted to the main wing 2. The axis of rotation of the guide device 18 coincides with the common axis of rotation A of the sealing elements 6, 7. The details of the guide device 18 in terms of its guiding of the high-lift body 4 are not within the scope of the present invention.

[0051] In the present exemplary embodiment, the guide device 18 is additionally provided for driving the first sealing element 6. For this purpose, the sealing element 6 is connected to the guide device 18 via a connecting element 19. The connecting element 19 is Figures 4 to 9 As shown in each figure. Figures 6 to 9 As best seen in FIG. 1 , the connecting element 19 protrudes perpendicularly and parallel to the common axis of rotation from the first sealing element 6. Due to the connection of the guide 18 to the first sealing element 6, the first sealing element 6 rotates relative to the main wing 2 when the high-lift body 4 moves in either direction between the retracted position and the deployed position.

[0052] The relative movement between the first sealing element 6 and the second sealing element 7 is controlled by the guide mechanism 22. The guide mechanism 22 is only used for Figures 4 to 7In the exemplary embodiment shown, the guiding mechanism 22 includes a rotatable guiding rod 23 having two spaced-apart pivot points 24, 25. A first guiding link 26 is attached to the guiding rod 23 at the first pivot point 24 and connects the first sealing element 6 to the guiding rod 23. A second guiding link 27 connects the rotatable guiding rod 23 to the second sealing element 7. The second guiding link 27 is attached to the guiding rod 23 at the second pivot point 25. The two pivot points 24, 25 are spaced apart from each other and from the mounting point 31, and the guiding rod 23 is rotatably mounted to the main wing 2 at the mounting point 31. Since the pivot points 24, 25 are at different positions along the guiding rod 23, the guiding device 22 ensures that the first sealing element 6 and the second sealing element 7 rotate different angles about a common axis of rotation A when the high-lift body 4 moves between the retracted position and the deployed position. Due to the different rotations, the sealing elements 6, 7 fan out between the high-lift body 4 and the main wing 2 and cover the entire gap between the high-lift body 4 and the main wing 2.

[0053] Figures 4 to 9 First guiding tracks 14 and second guiding tracks 15 respectively provided on the second sealing element 7 and the support surface 20 are also shown. The first guiding tracks 14 are provided for coupling the first sealing element 6 and the second sealing element 7 by guiding a first connecting member 32, and the first connecting member 32 is only visible in Figures 6 to 9 The second guiding tracks 15 are provided for connecting the second sealing element 7 to the main wing 2, particularly to the support surface 20. A second connecting member 34 is mounted on the second sealing element 7, and the second connecting member 34 is guided in the second guiding tracks 15. The guiding tracks 14, 15 and the corresponding connecting members 32, 34 are provided for ensuring the relative positions of the sealing elements 6, 7 relative to each other and relative to the support surface 20, so as to prevent gaps between the sealing elements 6, 7 and other components of the airfoil 1.

[0054] In Figure 8 and Figure 9 In the exemplary embodiment shown, no guiding mechanism 22 is provided. In this embodiment, the lower end stop and the upper end stop 33, 35 of the guiding tracks 14 and the guiding tracks 15 and the corresponding first end stop bolt 36 and second end stop bolt 37 are provided for transmitting the movement of the first sealing element 6 to the second sealing element 7 and for restricting the movement of the sealing elements 6, 7. Each of the guiding tracks 14, 15 includes a lower end stop and an upper end stop 33, 35, in Figure 8 and Figure 9Only the upper end stop portions 33, 35 are visible. The lower end stop portions are respectively hidden behind the first sealing element 6 and the second sealing element 7. The first end stop bolt 36 is provided on the first sealing element 6 for engaging with the lower end stop portion and the upper end stop portion 33 of the second sealing element 7. Similarly, the second end stop bolt 37 is provided on the second end sealing element 7 for engaging with the lower end stop portion and the upper end stop portion 35 of the support surface 20.

[0055] The lower end stop portions and the upper end stop portions 33, 35, and the corresponding first end stop bolt 36 and second end stop bolt 37 are arranged to limit the movement of the first sealing element 6 and the second sealing element 7 relative to each other and relative to the main wing 2. In addition, the lower end stop portions and the upper end stop portion 33 on the second sealing element 7, and the corresponding first end stop bolt 36 are also used to transfer the movement of the first sealing element 6 to the second sealing element 7. For example, when the first sealing element 6 together with the high-lift body 4 moves from the deployed position to the retracted position, the first connecting member 32 slides along the first guiding track 14 until the first end stop bolt 36 engages the upper end stop portion 33 of the first guiding track 14. Only then is the movement of the first sealing element 6 transferred to the second sealing element 7 through the upper end stop portion 33 and the first end stop bolt 36. In the opposite direction, when the first sealing element 6 together with the high-lift body 4 moves towards the deployed position, the movement is transferred to the second sealing element 7 only after the first end stop bolt 36 has engaged the lower end stop portion on the second sealing element 7.

[0056] In addition to the guiding tracks 14, 15 and the guiding mechanism 22, the seals 12, 13 and 21 are arranged to seal any gaps between the high-lift body and the sealing elements 6, 7 and the support surface 20. The seals 12, 13 are respectively mounted on the sealing elements 6, 7, and the seal 21 is mounted on the support surface 20, and the seals 12, 13 and 21 are in sliding contact with the inner surface of the high-lift body, which is delimited by the recess defined by the high-lift body.

[0057] Figure 10 A perspective view of an exemplary embodiment of an aircraft 39 according to the present invention is shown. The aircraft 39 includes a fuselage 40 and two airfoils 1. Each of the airfoils 1 includes a main wing 2 and a jet engine 41. In addition, as an exemplary embodiment, each airfoil 1 includes a high-lift body 4 according to the present invention. The leading-edge high-lift body 4 is mounted on the fuselage 40 of the aircraft 39 and between the corresponding jet engines 41 on the respective airfoils 1. Positioning the high-lift body 4 at this location is particularly advantageous because the most significant cross-flow has been observed at this location. However, it is also conceivable that the remaining leading-edge devices 42 are exemplary embodiments of the above-described high-lift body.

[0058] Finally, Figure 11 an exemplary embodiment of the airfoil 1 according to the present invention is shown. Only the high-lift body 4 and the sealing device 5 in the airfoil 1 are partially shown. As can be readily appreciated from Figure 11 it, the sealing device 5 only includes a single first sealing element 6 connected to the high-lift body 4. When the high-lift body 4 is moved between a retracted position and a deployed position using the guiding device 18, the first sealing element 6 moves together with the high-lift body 4 and rotates relative to the main wing (not shown) about a common axis of rotation A. Thus, in the deployed position of the high-lift body 4, the gap formed between the main wing and the high-lift body 4 in a plane extending perpendicular to the common axis of rotation A is advantageously at least partially covered by the first sealing element 6 of the sealing device 5.

Claims

1. An airfoil (1) for an aircraft, the airfoil (1) comprising: a main wing (2) having a leading edge; and a high-lift body (4) having a leading edge and a concavo-convex cross-section transverse to the leading edge of the high-lift body (4), such that a recess (30) is defined by the high-lift body (4), the recess (30) extending parallel to the leading edge of the high-lift body (4), wherein the high-lift body (4) is coupled to the main wing (2) at a recessed portion (29) provided in the leading edge of the main wing (2), such that the recess (30) faces the main wing (2), and wherein the high-lift body (4) is selectively movable between a retracted position and a deployed position, wherein, in the retracted position, the leading edge of the main wing (2) and the leading edge of the high-lift body (4) form a continuous common leading edge, the airfoil (1) further comprising a sealing device (5) having a first sealing element (6) disposed in the recess (30) defined by the high-lift body (4), wherein the first sealing element (6) is plate-shaped, rotatable relative to the main wing (2) about a common axis of rotation (A), partially abuts against the high-lift body (4) and has a side surface (8) extending perpendicular to the common axis of rotation (A), wherein the sealing device (5) is coupled to the high-lift body (4) such that: when the high-lift body (4) moves between the retracted position and the deployed position, the first sealing element (6) rotates relative to the main wing (2), wherein, in the deployed position of the high-lift body (4), at least a portion of the gap formed between the main wing (2) and the high-lift body (4) in a plane extending perpendicular to the common axis of rotation is covered by the sealing device (5), characterized in that the sealing device (5) comprises a second sealing element (7) disposed in the recess (30) defined by the high-lift body (4), wherein the second sealing element (7) is plate-shaped, rotatable relative to the main wing (2) about the common axis of rotation (A) and has a side surface (9) extending perpendicular to the common axis of rotation (A), wherein the first sealing element (6) and the second sealing element (7) are rotatable relative to each other about the common axis of rotation (A), and wherein the side surface (8) of the first sealing element (6) and the side surface (9) of the second sealing element (7) extend parallel to each other, and Wherein, when the high-lift body (4) moves between the retracted position and the deployed position, the second sealing element (7) rotates relative to the main wing (2) and the first sealing element (6) and the second sealing element (7) rotate relative to each other such that: when the first sealing element (6) and the second sealing element (7) are projected onto a plane extending perpendicular to the common axis of rotation (A), the overlap between the first sealing element (6) and the second sealing element (7) is smaller when the high-lift body (4) is in the deployed position than when the high-lift body (4) is in the retracted position.

2. The airfoil according to claim 1, wherein the airfoil (1) comprises guiding means (18) for mechanically coupling the high-lift body (4) to the main wing (2), wherein, the first sealing element (6) is mechanically coupled to the guiding means (18).

3. The airfoil according to claim 2, wherein, the guiding means (18) is rotatably coupled to the main wing (2), wherein the guiding means (18) is adapted to rotate relative to the main wing (2) about the common axis of rotation (A).

4. The airfoil according to claim 2, wherein, a connecting element (19) connects the first sealing element (6) to the guiding means (18) to drive the first sealing element (6).

5. The airfoil according to claim 4, wherein, the connecting element (19) projects from the first sealing element (6) in a direction extending parallel to the common axis of rotation (A).

6. The airfoil according to claim 1, wherein, a first seal (12) is arranged on the first sealing element (6), wherein the first seal (12) contacts the high-lift body (4).

7. The airfoil according to claim 1, wherein, the first sealing element (6) and the second sealing element (7) are connected via a first guiding track (14) and a first connecting member (32) guided in the first guiding track (14).

8. The airfoil according to claim 7, wherein, the first guiding track (14) comprises an upper end stop (33) and a lower end stop, and the upper end stop (33) and the lower end stop of the first guiding track (14) are adapted to engage corresponding first end stop bolts (36) to limit the movement of the first sealing element (6) and the second sealing element (7) relative to each other.

9. The airfoil according to claim 8, wherein, the second sealing element (7) is driven via the first end stop bolt (36) when the first end stop bolt (36) engages either the upper end stop (33) or the lower end stop of the first guiding track (14).

10. The airfoil according to any one of claims 1 to 9, wherein, A second seal (13) is arranged on the second sealing element (7), wherein the second seal (13) contacts the high-lift body (4).

11. An airfoil according to any one of claims 1 to 9, wherein, the second sealing element (7) is connected to the main wing (2) via a second guide rail (15) and a second connecting member (34) guided in the second guide rail (15).

12. An airfoil according to claim 11, wherein, the second guide rail (15) includes an upper end stop (35) and a lower end stop, and the upper end stop (35) and the lower end stop of the second guide rail (15) are used to engage with corresponding second end stop bolts (37) to limit the movement of the second sealing element (7) relative to the main wing (2).

13. An airfoil according to claim 11, wherein, the main wing (2) includes a support surface (20) perpendicular to the common axis of rotation (A) and extending parallel to the second sealing element (7), wherein the second sealing element (7) is connected to the support surface (20) via the second guide rail (15) and a second connecting member (34) guided in the second guide rail (15), and wherein, when the second sealing element (7) and the support surface (20) are projected onto a plane extending perpendicular to the common axis of rotation (A), the overlap between the second sealing element (7) and the support surface (20) is smaller when the high-lift body (4) is in the deployed position than when the high-lift body (4) is in the retracted position.

14. An airfoil according to claim 13, wherein, in the deployed position and the retracted position of the high-lift body (4), the high-lift body (4) contacts the support surface (20) of the main wing (2).

15. An airfoil according to claim 14, wherein, the contact between the high-lift body (4) and the support surface (20) of the main wing (2) is provided by a third seal (21).

16. An airfoil according to any one of claims 1 to 9, comprising a guiding mechanism (22) for controlling the relative movement of the first sealing element (6) and the second sealing element (7), the guiding mechanism (22) including a guiding rod (23) having a first pivot point (24) and a second pivot point (25) spaced apart from each other and spaced apart from the mounting point (31), the guiding rod (23) being rotatably mounted to the main wing (2) at the mounting point (31), wherein, a first guiding link (26) mechanically connects the first pivot point (24) to the first sealing element (6), and a second guiding link (27) mechanically connects the second pivot point (25) to the second sealing element (7).

17. An airfoil according to claim 16, wherein, The main wing (2) includes a support surface (20) that is perpendicular to the common axis of rotation (A) and extends parallel to the second sealing element (7), and the guide rod (23) is rotatably mounted on the support surface (20).

18. An airfoil according to any one of claims 1 to 9, wherein, the high-lift body (4) is a drooping nose.

19. An aircraft (39) having an airfoil (1) according to any one of claims 1 to 18.

20. An aircraft according to claim 19, wherein, the high-lift body (4) is arranged between the fuselage (40) of the aircraft (39) and the engine (41) supported by the airfoil (1).

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