Winglet and aircraft wing

Abstract

The winglet comprises a transition section, one end of the transition section is assembled on the end face of a wingtip of the aircraft wing, the end face of the wingtip of the aircraft wing extends to form the transition section, the transition section is provided with a first arc-shaped section which is partially oval, one end of the first arc-shaped section is arranged on the end face of the other end of the transition section, and the other end of the first arc-shaped section is provided with a second arc-shaped section which is partially oval. The first arc-shaped section is arranged at one end of the wing tip, is tangent to the transition section and is provided with a second arc-shaped section which is partially elliptical, one end of the second arc-shaped section is assembled at the other end of the first arc-shaped section, and the wing tip, the transition section, the first arc-shaped section and the second arc-shaped section form a curved surface with continuous curvature. During design, the design parameters of the winglet are mainly the angle deflection difference value between the first ellipse and the second ellipse and the length of the semi-major axis a, compared with an existing curve winglet, the design process is simplified, meanwhile, the curvature change of the reverse guide line on the winglet can be more continuous, and the lift-drag ratio of the whole wing is increased.

Description

Technical Field

[0001] This application relates to the technical field of winglets, and in particular, to a winglet and an aircraft wing. Background Art

[0002] The initial winglets were simply wingtip devices in the form of "end plates" installed at the wingtips. Since their drag reduction effect was not ideal, they were rarely used in actual applications. Later, blended winglets, shark fin winglets, etc. were gradually developed.

[0003] The design of winglets is restricted by many factors. The determination of winglet parameters is one of them, mainly including the wingspan (i.e., height), aspect ratio, installation angle, twist angle, dihedral angle, root-to-tip ratio, leading edge sweep angle, and trailing edge sweep angle of the winglet. The influence degrees of these parameters on the wing drag coefficient are different. According to the research of relevant reference materials, it is found that the wingspan, inclination angle, and load are important factors affecting the induced drag. The design of winglets is mainly used to reduce the induced drag of the aircraft.

[0004] The leading line of the traditional upwardly-curved winglet is a straight line, and a curve is used between the winglet and the wing. Although this design can block the flow of the air on the lower surface of the wing from flowing upward to the upper surface and weaken the strength of the wingtip vortex, the lift-to-drag ratio of the wingtip of the wing is still not significant enough. At the same time, there are also winglets with a curved leading line that curves upward. Among them, the parameters involved in the upwardly-curved curve are numerous, the bending radius is fixed, the curvature is not continuous enough, and the design process is complex. Summary of the Invention

[0005] This application provides a winglet and an aircraft wing, which can solve the problems that when designing the upwardly-curved guiding line of the winglet, there are many design parameters, the radius is fixed, the curvature is not continuous enough, and the design process is complex.

[0006] The technical solution of this application is as follows: A winglet includes: A transition section, one end of the transition section is assembled on one end face of the wingtip of the wing, and the end face of one end of the transition section coincides with the shape of the end face of one end of the wingtip of the wing; A first arc section with a partial elliptical shape, one end of the first arc section is connected to the other end face of the transition section, the end face of one end of the first arc section coincides with the shape of the other end face of the transition section, the ellipse where the first arc section is located is defined as the first ellipse, the major axis a of the first ellipse is perpendicular to the quarter chord line c of the wingtip of the wing, and the shape curve of the first arc section satisfies the formula: Where x1 and y1 respectively represent the coordinate values of any point on the first ellipse on the local coordinate system x-axis and y-axis, a1 is the major axis length of the first ellipse, and b1 is the minor axis length of the first ellipse; A second arc segment having a partial elliptical shape, the second arc segment being connected to the other end of the first arc segment, the wing tip, the transition segment, the first arc segment and the second arc segment forming a continuously curved surface, the ellipse in which the second arc segment is located being defined as the second ellipse, the second ellipse having the same shape as the first ellipse, the center of the second ellipse being located on the major axis of the first ellipse, the second ellipse being tangent to the first ellipse, the tangent point being located at the connection between the second arc segment and the first arc segment, and the shape curve of the second arc segment satisfying the formula: Where x2 and y2 respectively represent the coordinate values of any point on the second ellipse on the x-axis and y-axis of the local coordinate system, a2 is the length of the major semi-axis of the second ellipse, and b2 is the length of the minor semi-axis of the second ellipse.

[0007] By adopting the above solution, by setting the first arc segment having a partial elliptical shape and connecting it to the end face of the wing tip through the transition segment, during design, since the first arc segment is tangent to the transition segment and its major semi-axis is perpendicular to the quarter chord line of the wing tip, the position angle of the first ellipse can be determined according to the shape of the wing tip, and thus the position and deflection angle of the first arc segment can be determined. At the same time, when designing the second arc segment, only need to deflect the second ellipse having the same shape as the first ellipse by an angle and ensure that its center can move along the major axis until it is tangent to the first ellipse. At this time, the tangent point position extends along the side away from the transition segment, and the extended arc surface shape is the second arc segment. Among them, the design parameters of the winglet are mainly the angle deflection difference between the first ellipse and the second ellipse and the length a of the major semi-axis. Compared with the existing curved winglet, while simplifying the design process, it can make the curvature change of the leading line of the winglet more continuous and improve the lift-drag ratio of the entire wing.

[0008] In one embodiment of the present application, the angle between the major axis of the first ellipse and the major axis of the second ellipse is defined as the inclination angle α, and the inclination angle α satisfies: 45° ≤ α ≤ 65°.

[0009] In the above technical solution, since the major semi-axis a of the first ellipse is always perpendicular to the quarter chord line c of the wing tip, the inclination angle of the first ellipse can be improved according to the shapes of different wing tips, so that the inclination angle of the first arc segment can be quickly determined. Furthermore, only by adjusting the inclination angle α, that is, the difference between the first arc segment and the second arc segment, the inclination angle of the second arc segment can also be quickly determined according to different types of wing tips, so that the two form a continuously curved surface. At the same time, the convenience of determining the second arc segment is improved. At the same time, by limiting the range of the inclination angle to adjust the relative inclination degree of the first arc segment and the second arc segment, the curvature change of the entire winglet is made smoother.

[0010] In one embodiment of the present application, the minor semi-axis b lengths of the first ellipse and the second ellipse are both 1 / 10 of the semi-span of the wing.

[0011] By adopting the above scheme, by defining the minor semi-axis b lengths of the first ellipse and the second ellipse, it can be customized according to the semi-span of different types of wings. Therefore, compared with the conventional winglet with a curved upper turning guide line, one design parameter feature is reduced, thus simplifying the design process.

[0012] In one embodiment of the present application, the end faces at both ends of the transition section form an intersection line s at the intersection, and the intersection line s is located on the leading edge or the trailing edge of the wing tip of the wing.

[0013] By adopting the above scheme, the present device can design transition sections with two different placement angles according to the requirements of the actual working conditions, thereby setting the angle deviation direction between the winglet and the wing in the xoy plane, changing the included angle between the winglet and the oncoming flow, reducing the wing tip vortex, and thus reducing the aerodynamic drag.

[0014] In one embodiment of the present application, the end faces at both ends of the transition section intersect with each other and form an installation angle β, and the installation angle β satisfies: 0° < β ≤ 3°.

[0015] By adopting the above scheme, the numerical range of the installation angle β of the transition section is set, thereby setting the angle deviation range between the winglet and the wing in the xoy plane, further optimizing the wing tip angle, and thus reducing the aerodynamic drag.

[0016] In one embodiment of the present application, the wing tip twist angle θ of the winglet satisfies: -3° ≤ θ ≤ 3°.

[0017] In one embodiment of the present application, the quarter-chord line sweep angle γ of the winglet satisfies: 39° ≤ γ ≤ 50°.

[0018] By adopting the above scheme, other parameters of the winglet are defined, so that the winglet can block the flow of the air on the lower surface of the wing upward to the upper surface during the flight of the wing, weaken the intensity of the wing tip vortex, and improve the lift-to-drag ratio of the wing.

[0019] In one embodiment of the present application, the transition section includes: A first fixing strip, fixedly assembled on the end face of the first arc section far from the second arc section; A second fixing strip, fixedly assembled on the end face of the wing tip of the wing. An elastic metal sheet is provided at one end of the second fixing strip close to the first fixing strip, and the elastic metal sheet is fixedly connected to the first fixing strip; The sliding block has a T-shaped slot on one side where the first fixing strip and the second fixing strip are close to each other, T-shaped sliding blocks that can slide inside the T-shaped slot are provided on both sides of the sliding block, and a clamping piece that can fix the sliding block is provided on the sliding block.

[0020] By adopting the above scheme, the transition section is designed as a component that can be opened and closed at an angle, so that when the device is in use, the installation angle β of the transition section can be adjusted according to the actual working conditions, thereby avoiding the trouble of making a transition section with a customized angle according to the working conditions, and improving the convenience of use and design of the device.

[0021] In one embodiment of the present application, the engaging member comprises: A clamping strip, wherein the sliding block is provided with a strip-shaped sliding groove extending toward the second fixed strip, and the clamping strip is slidably assembled inside the strip-shaped sliding groove; An elastic member is arranged inside the strip-shaped slide groove, and the elastic member is respectively connected and fixed to the inner wall of the clamping strip and the strip-shaped slide groove. A tooth groove extending along the length direction of the second fixing strip is provided on one side of the second fixing strip, and one end of the clamping strip can extend into the tooth groove and engage with the tooth groove.

[0022] By adopting the above solution, when the angle of the transition section is adjusted according to actual working conditions, the elasticity of the elastic part itself is used to continuously generate thrust on the clamping strip, so that one end of the clamping strip can engage with the inside of the tooth groove, thereby ensuring that the sliding block will not malfunction after the first fixed strip and the second fixed strip are stretched apart.

[0023] The present invention also relates to an aircraft wing, and its specific technical solution is as follows: an aircraft wing, including a winglet.

[0024] In summary, the present application includes at least one of the following beneficial technical effects: 1. By setting two first ellipses and a second ellipse of the same shape and changing the angle between the first ellipse and the second ellipse, the curvature of the two arc segments determined by the two ellipses is changed, so that when the two arc segments are connected, the radius of the arc surface changes continuously, and the curvature of the upper inverse characteristic curve of the entire winglet is more continuous and smooth, thereby reducing the air resistance.

[0025] 2. By setting two arc segments determined by two ellipses and using two ellipses whose parameters can be determined according to the wing type, by changing the deflection angle between the two, the arc surface shapes of the two arc segments are determined, and then the shape of the entire winglet can be determined. In this design scheme, the design parameters of the first arc segment and the second arc segment are determined according to the actual semi-span of the wing. Therefore, compared with the existing design scheme, one important design parameter is missing, thereby simplifying the design process.

[0026] 3. By setting a transition section and setting the included angle range of the two end faces of the transition section itself, since the transition section is set on the end face of the wing, the orientation of the wing end face is changed, thereby changing the included angle between the winglet and the oncoming flow, reducing the wing tip vortex, and thus reducing the aerodynamic drag of the winglet. 4. By setting a first fixing strip, a second fixing strip and a sliding block, by setting the first fixing strip and the second fixing strip that can be opened and closed with each other, the installation angle of the entire transition section is adjusted by the opening and closing of the first fixing strip and the second fixing strip, and then the angles between the first arc section and the second arc section and the oncoming flow are adjusted, so that the device can finely adjust the installation angle of the winglet according to the actual working conditions, avoiding the trouble of re - design and manufacturing, and saving the economic cost. Description of the Drawings

[0027] Figure 1 is the front view of the first ellipse and the second ellipse of a winglet provided in the first embodiment of the present application; Figure 2 is the front view of a winglet provided in the first embodiment of the present application when the intersection line is located at the leading edge of the wing tip; Figure 3 is the plan view of a winglet provided in the first embodiment of the present application when the intersection line is located at the leading edge of the wing tip; Figure 4 is the front view of a winglet provided in the first embodiment of the present application when the intersection line is located at the trailing edge of the wing tip; Figure 5 is the schematic plan view of a winglet provided in the first embodiment of the present application when the intersection line is located at the trailing edge of the wing tip; Figure 6 is the front view of the sweep angle of a winglet provided in the first embodiment of the present application; Figure 7 is the front view schematic diagram of a winglet provided in the first embodiment of the present application with or without a twist angle; Figure 8 is the front view schematic diagram of the first fixing strip and the second fixing strip of a winglet provided in the second embodiment of the present application; Figure 9 is the front - view cross - sectional view of the T - shaped chute of a winglet provided in the first embodiment of the present application; Figure 10 is Figure 8 the enlarged schematic diagram of part A in

[0028] Description of reference numerals: 1. Transition section; 11. First fixing strip; 111. Elastic metal sheet; 12. Slide block; 121. T-shaped slide block; 122. Engaging member; 1221. Engaging strip; 1222. Elastic member; 123. Strip-shaped chute; 13. Second fixing strip; 131. T-shaped chute; 2. First arc segment; 21. First ellipse; 3. Second arc segment; 31. Second ellipse; 4. Wing tip of the aircraft. Detailed implementation manners

[0029] The following further elaborates in detail on a winglet and an aircraft wing provided by this application in combination with the attached Figures 1-10 drawings.

[0030] Please refer to Figure 1 , which is a winglet provided in an embodiment of this application and is assembled on the end face of the wing tip 4 of the aircraft wing. It includes: a transition section 1, a first arc segment 2, and a second arc segment 3. One end of the transition section 1 is assembled on one end face of the wing tip 4 of the aircraft wing. The end face of one end of the transition section 1 is in conformity with the shape of the end face of one end of the wing tip 4 of the aircraft wing. The first arc segment 2 has a partial elliptical shape. One end of the first arc segment 2 is connected to the end face of the other end of the transition section 1. The end face of one end of the first arc segment 2 is in conformity with the shape of the end face of the other end of the transition section 1. The shape curve of the first arc segment 2 satisfies the formula: wherein, x1 and y1 respectively represent the coordinate values of any point on the first ellipse 21 on the x-axis and y-axis of the local coordinate system, a1 is the major semi-axis length of the first ellipse 21, and b1 is the minor semi-axis length of the first ellipse 21; The second arc segment 3 has a partial elliptical shape. The second arc segment 3 is connected to the other end of the first arc segment 2. The aircraft wing tip 4, the transition section 1, the first arc segment 2, and the second arc segment 3 form a continuously curved surface. The ellipse where the second arc segment 3 is located is defined as the second ellipse 31. The second ellipse 31 has the same shape as the first ellipse 21. The center of the second ellipse 31 is located on the major axis of the first ellipse 21. The second ellipse 31 is tangent to the first ellipse 21, and the tangent point is located at the connection between the second arc segment 3 and the first arc segment 2. The shape curve of the second arc segment 3 satisfies the formula: Among them, x2 and y2 respectively represent the coordinate values of any point on the second ellipse 31 on the x-axis and y-axis of the local coordinate system. a2 is the major semi-axis length of the second ellipse 31, and b2 is the minor semi-axis length of the second ellipse 31. By using two first ellipses 21 and second ellipses 31 with the same shape, the arc surface shapes of the first arc segment 2 and the second arc segment 3 are respectively determined, so that when the device is designed, by changing the angle between the ellipses where the two first arc segments 2 and the second arc segment 3 are located, the arc surface curvature of the first arc segment 2 and the second arc segment 3 can be changed, making the design more convenient. At the same time, the curvature change between the first arc segment 2 and the second arc segment 3 is more continuous, reducing air resistance.

[0031] Please refer to Figure 1 , define the angle between the major axis of the first ellipse 21 and the major axis of the second ellipse 31 as the tilt oblique included angle α, and the tilt included angle α satisfies: 45° ≤ α ≤ 65°. By adjusting the angle of the tilt included angle α, the relative tilt degree of the first arc segment 2 and the second arc segment 3 is adjusted. By changing the tilt included angle between the two ellipses, the relative tilt degree of the first arc segment 2 and the second arc segment 3 is changed, facilitating the parameter design of the wingtip. In the test session of controlling variables, it is also more convenient.

[0032] In this embodiment, by changing the value of the tilt included angle α and using the fluid dynamics (CFD) simulation software star-ccm+ for simulation, the obtained drag coefficient is used to determine the design parameters when the overall aerodynamic drag of the wing is minimized.

[0033] Please refer to Figure 1 , the length of the minor semi-axis b of the first ellipse 21 and the second ellipse 31 is 1 / 10 of the half-span length of the wing. By limiting the length of the entire winglet, the device can be limited in the length direction according to different types of wings, reducing the parameter design of the winglet.

[0034] Please refer to Figures 2-4 , the two end faces of the transition section 1 form an intersection line s at the intersection. The intersection line s is located on the leading edge or the trailing edge of the wingtip 4 of the wing. The two end faces of the transition section 1 form an intersection line s at the intersection. The intersection line s is located on the leading edge or the trailing edge of the wingtip 4 of the wing. By setting the transition section 1 that can be at a certain angle and setting it at the end face of the wingtip 4 of the wing, the angle between the winglet and the oncoming flow can be changed to a certain extent, optimizing the air resistance of the winglet.

[0035] The end faces at both ends of the transition section 1 intersect with each other and form an installation angle β, and the installation angle β satisfies: 0° < β ≤ 3°. The end faces at both ends of the transition section 1 form an intersection line s at the intersection, and the intersection line s is located on the leading edge or the trailing edge of the wing tip 4 of the aircraft wing. By setting the transition section 1 that can be at a certain angle and arranging it at the end face of the wing tip 4 of the aircraft wing, the angle between the winglet and the oncoming flow can be changed to a certain extent, and the air resistance of the winglet can be optimized.

[0036] In this embodiment, please refer to Figure 2 and Figure 3 , at this time, the installation angle orientation of the transition section 1 can be set so that the end faces at both ends of the transition section 1 intersect at the leading edge of the wing tip 4 of the aircraft wing. Please refer to Figure 4 and Figure 5 , at this time, the installation angle orientation of the transition section 1 can be set so that the end faces at both ends of the transition section 1 intersect at the trailing edge of the wing tip 4 of the aircraft wing, so that the winglet can be adjusted at two angles of orientation to adapt to different wings.

[0037] Please refer to Figure 7 , the wing tip twist angle θ of the winglet satisfies: -3° ≤ θ ≤ 3°. By limiting the wing tip twist angle of the winglet, the aerodynamic layout of the winglet can be further optimized.

[0038] Please refer to Figure 6 , the quarter-chord line position sweep angle γ of the winglet satisfies: 39° ≤ γ ≤ 50°. By limiting the sweep angle of the winglet, the air resistance between the winglet and the oncoming flow can be further reduced.

[0039] Embodiment 2 Please refer to Figure 8 、 Figure 9 and Figure 10, Embodiment 2 has the same basic structure as Embodiment 1, the difference being that: the transition section 1 includes: a first fixing strip 11, a second fixing strip 13 and a sliding block 12, fixedly assembled on the end face of the first arc section 2 away from the second arc section 3, fixedly assembled on the end face of the wing tip 4 of the aircraft wing, an elastic metal sheet 111 is provided at one end of the second fixing strip 13 close to the first fixing strip 11, the elastic metal sheet 111 is fixedly connected to the first fixing strip 11, T-shaped sliding grooves 131 are formed on the sides of the first fixing strip 11 and the second fixing strip 13 close to each other, T-shaped sliding blocks 121 that can slide inside the T-shaped sliding grooves 131 are provided on both sides of the sliding block 12, and a clamping member 122 for fixing the sliding block 12 is provided on the sliding block 12. By providing the first fixing strip 11 and the second fixing strip 13 that can be opened and closed with each other, and using the sliding block 12 to be assembled between the first fixing strip 11 and the second fixing strip 13, the first fixing strip 11 and the second fixing strip 13 can be made to open a certain angle and remain stable, so as to be able to quickly adjust the setting range of the installation angle β of the transition section.

[0040] Among them, the first fixing strip 11 and the second fixing strip 13 are wrapped with a skin. When the width 1 of the transition section needs to be changed, only the skin needs to be removed and replaced, and the installation angle β between the entire winglet and the wing tip of the aircraft wing can be quickly adjusted. Compared with the existing technology that requires re-design and fixed connection, the economic cost is lower.

[0041] Please refer to Figure 9 , the clamping member 122 includes: a clamping bar 1221 and an elastic member 1222. A strip-shaped sliding groove 123 extending towards the second fixing strip 13 is formed on the sliding block 12. The clamping bar 1221 is slidably assembled inside the strip-shaped sliding groove 123. The elastic member 1222 is arranged inside the strip-shaped sliding groove 123. The elastic member 1222 is fixedly connected to the clamping bar 1221 and the inner wall of the strip-shaped sliding groove 123 respectively. A tooth groove 131 extending along the length direction of the second fixing strip 13 is formed on one side of the second fixing strip 13. One end of the clamping bar 1221 can extend into the tooth groove 131 and engage with the tooth groove 131. By using the elastic member and the clamping bar inside the device, when the sliding block 12 moves to a specified position between the first fixing strip 11 and the second fixing strip 13, under the action of the force exerted by the elastic member 1222 on the clamping bar 1221, one end of the clamping bar 1221 penetrates into the tooth groove 131 and engages with the tooth groove 131, so that the sliding block 12 can be stably fixed after moving to the specified position.

[0042] The present invention also relates to an aircraft wing, and its technical solution is as follows: an aircraft wing includes a winglet.

[0043] In summary, the winglet can adjust the angle between the winglet and the incoming flow by first setting a transition section 1 at the end face of the wing tip 4 of the wing, which fits its shape and extends out, thereby improving the tip vortex of the winglet and reducing the drag on the entire wing. In the design, first set the first ellipse 21 according to the type and shape of the wing, so that the major axis of the first ellipse 21 is always perpendicular to the quarter chord line of the wing, thereby enabling the inclination angle of the first ellipse 21 to be determined quickly and conveniently. At the same time, since the minor axes of the first ellipse 21 and the second ellipse 31 can also be determined according to the semi-span of the wing, when designing the first ellipse 21 and the second ellipse 31, only the length of the major axis a of the two needs to be designed, and the inclination angle between the first ellipse 21 and the second ellipse 31 needs to be designed, so that the arc surface shape between the first arc segment 2 and the second arc segment 3 can be determined quickly. Compared with the existing design scheme of using the arcs of multiple circles for the winglet curve, the design parameters are fewer, and the radius change of the winglet is not fixed. The curvature change of the first arc segment 2 and the second arc segment 3 is more continuous, reducing the air flow resistance.

[0044] The above are all the preferred embodiments of this application, and the protection scope of this application is not limited accordingly. Therefore, all equivalent changes made according to the structure, shape, and principle of this application should be covered within the protection scope of this application.

Claims

1. A winglet, characterized in that: include: A transition section (1), one end of the transition section (1) being mounted on an end surface of a wing tip (4), and the shape of the end surface of the transition section (1) and the end surface of the wing tip (4) being consistent with each other; A first arc segment (2) having a partially elliptical shape, one end of the first arc segment (2) being connected to the other end face of the transition segment (1), the end face of one end of the first arc segment (2) being consistent in shape with the other end face of the transition segment (1), the ellipse in which the first arc segment (2) is located being defined as a first ellipse (21), the major semi-axis a of the first ellipse (21) being perpendicular to a quarter chord c of the wing tip (4), and the shape curve of the first arc segment (2) satisfying the formula: Wherein, x1 and y1 represent the coordinate values ​​of any point on the first ellipse (21) on the x-axis and y-axis of the local coordinate system, respectively; a1 is the length of the major semi-axis of the first ellipse (21); and b1 is the length of the minor semi-axis of the first ellipse (21); A second arc segment (3) having a partially elliptical shape, the second arc segment (3) being connected to the other end of the first arc segment (2), the wing tip (4), the transition segment (1), the first arc segment (2) and the second arc segment (3) forming a curved surface with a continuous curvature, the ellipse where the second arc segment (3) is located is defined as a second ellipse (31), the second ellipse (31) has the same shape as the first ellipse (21), the center of the second ellipse (31) is located on the major axis of the first ellipse (21), the second ellipse (31) is tangent to the first ellipse (21), the tangent point is located at the connection between the second arc segment (3) and the first arc segment (2), and the shape curve of the second arc segment (3) satisfies the formula: Wherein, x2 and y2 represent the coordinate values ​​of any point on the second ellipse (31) on the x-axis and y-axis of the local coordinate system respectively, a2 is the length of the major semi-axis of the second ellipse (31), and b2 is the length of the minor semi-axis of the second ellipse (31).

2. A winglet according to claim 1, characterized in that: The angle between the major axis of the first ellipse (21) and the major axis of the second ellipse (31) is defined as an inclined angle α, and the inclined angle α satisfies: 45°≤α≤65°.

3. A winglet according to claim 1, characterized in that: The lengths of the minor semi-axes b of the first ellipse (21) and the second ellipse (31) are both 1 / 10 of the half span of the wing.

4. A winglet according to claim 2, characterized in that: The end surfaces at both ends of the transition section (1) form an intersection line s at the intersection, and the intersection line s is located on the leading edge or the trailing edge of the wing tip (4).

5. The winglet according to claim 1, characterized in that: The end faces at both ends of the transition section (1) intersect each other and form a mounting angle β, wherein the mounting angle β satisfies: 0°<β≤3°.

6. A winglet according to claim 5, characterized in that: The wingtip twist angle θ of the winglet satisfies: -3°≤θ≤3°.

7. A winglet according to claim 5, characterized in that: The sweep angle γ of the winglet at the quarter chord position satisfies: 39°≤γ≤50°.

8. The winglet according to claim 1, characterized in that: The transition section (1) comprises: A first fixing strip (11) is fixedly mounted on an end surface of the first arc segment (2) away from the second arc segment (3); A second fixing strip (13) is fixedly mounted on the end surface of the wing tip (4), an elastic metal sheet (111) is provided at one end of the second fixing strip (13) close to the first fixing strip (11), and the elastic metal sheet (111) is connected and fixed to the first fixing strip (11); A sliding block (12), wherein a T-shaped sliding groove (131) is provided on one side where the first fixing strip (11) and the second fixing strip (13) are close to each other, T-shaped sliding blocks (121) which can slide inside the T-shaped sliding groove (131) are provided on both sides of the sliding block (12), and a locking member (122) which can fix the sliding block (12) is provided on the sliding block (12).

9. A winglet according to claim 8, characterized in that: The engaging member (122) comprises: A clamping strip (1221), wherein the sliding block (12) is provided with a strip-shaped sliding groove (123) extending toward the second fixed strip (13), and the clamping strip (1221) is slidably assembled inside the strip-shaped sliding groove (123); An elastic member (1222), wherein the elastic member (1222) is arranged inside the strip-shaped slide groove (123), and the elastic member (1222) is respectively connected and fixed to the inner wall of the clamping strip (1221) and the strip-shaped slide groove (123), and a tooth groove (131) extending along the length direction of the second fixing strip (13) is provided on one side, and one end of the clamping strip (1221) can extend into the tooth groove (131) and engage with the tooth groove (131).

10. An aircraft wing, characterized in that: Comprising the winglet according to any one of claims 1-9.

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