Trailing edge flap spanwise outer side wing face structure
By setting airfoils on the outer lower surface of the trailing edge flap, the flow field is optimized, and the flow separation and noise problems during the deflection of the trailing edge flap is solved, and the lift lift and noise reduction effects are achieved.
Patent Information
- Application Number
- CN202422510270.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-16
- Publication Date
- 2025-07-25
- Estimated Expiration
- 2034-10-16
AI Technical Summary
The existing trailing edge flaps tend to cause the flow separation and fall vortex of the surface layer when deflected, resulting in increased noise at the edge of the flap. The conventional design is limited by the size of the main wing, making it difficult to improve the flow field.
The airfoil plate is provided on the outer lower surface of the trailing edge flap. The airfoil plate extends out when the flap is opened and fits with the recovery groove on the lower surface of the main wing when it is closed, optimizing the flow field and reducing shedding vortex and reducing noise.
Without changing the flap shape, improve the flow field, improve the lift coefficient, reduce the fall vortex, reduce the flap edge noise, and improve aerodynamic performance.
Smart Images
Figure CN223148680U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to a structure of the outboard wing surface in the span direction of a trailing edge flap for improving the flow field at the edge of the flap. Background Art
[0002] With the continuous development of the new generation of high-performance commercial aircraft, the performance requirements for the takeoff and landing of the aircraft are continuously improved. At the same time, the control of the flap edge noise in the aircraft noise is also an important part of suppressing the aircraft noise. In addition, the lift augmentation device is a component used to meet the lift requirements in various low-speed flight stages. Therefore, the design of the lift augmentation device is an indispensable part of the aircraft design.
[0003] As the main component of the lift augmentation device, by deflecting the trailing edge flap,
[0004] the camber effect of the wing can be effectively increased and the area of the wing can be enlarged. However, when the deflection angle of the trailing edge flap is relatively large, the boundary layer flow separation is likely to occur on the flap surface, resulting in partial loss of lift, possible vibration of the trailing edge flap, and the generation of shedding vortices at the flap edge, thus increasing the noise at the flap edge.
[0005] In most cases, the lift augmentation device is only arranged at limited positions on the wing. The spanwise length of the existing conventional trailing edge flap is affected by the size of the main wing. If the deflection angle of the trailing edge flap is relatively large, there will be boundary layer separation in some areas.
[0006] Therefore, how to design a structure of the outboard wing surface in the span direction of the trailing edge flap to improve the flow field at the flap edge and reduce the noise at the flap edge has become an urgent technical problem to be solved. Summary of the Utility Model
[0007] The utility model is made to solve various technical problems existing in the prior art, and its purpose is to provide a structure of the outboard wing surface in the span direction of the trailing edge flap, which can improve the boundary layer state on the wing surface of the trailing edge flap and reduce the separation degree without changing the flap shape of the existing trailing edge flap, so as to improve the flow field at the flap edge.
[0008] In addition, the purpose of the utility model is also to provide a structure of the outboard wing surface in the span direction of the trailing edge flap to reduce the size of the shedding vortices at the flap edge of the trailing edge flap and reduce the noise at the flap edge.
[0009] To achieve the above object, the present utility model provides a trailing edge flap spanwise outer wing surface structure. The trailing edge flap spanwise outer wing surface structure is the wing surface structure on the outer side in the extension direction of the trailing edge flap in the flap of the main wing of an aircraft. Its characteristics are that on the outer lower surface in the extension direction of the trailing edge flap, there is a wing profile plate extending along the outer edge of the trailing edge flap. When the trailing edge flap is opened relative to the main wing, the wing profile plate extends out relative to the trailing edge flap and the main wing.
[0010] Preferably, on the lower surface of the main wing, there is a recovery groove for accommodating the wing profile plate.
[0011] When the trailing edge flap is retracted to the cruise configuration relative to the main wing, the wing profile plate extending in the span direction from the trailing edge flap fits with the recovery groove on the lower surface of the main wing.
[0012] More preferably, one end of the wing profile plate is arranged near the installation part where the trailing edge flap is installed on the main wing.
[0013] At this time, the chord length of the wing profile plate is shorter than the chord length of the trailing edge flap.
[0014] In addition, the span length of the wing profile plate is determined according to the flow separation area on the trailing edge flap.
[0015] According to the above composition, without changing the surface shape of the original trailing edge flap, by adding a trailing edge flap spanwise outer wing surface structure, the flow field on the upper and lower surfaces of the trailing edge flap can be optimized, the lift coefficient of the linear segment can be effectively improved, and the shedding vortex generated at the flap edge can be reduced, and the noise at the flap edge can be lowered.
[0016] In addition, when the trailing edge flap is retracted to the cruise configuration relative to the main wing, the wing profile plate fits with the recovery groove on the lower surface of the main wing, so as to ensure that the aerodynamic shape in the original cruise configuration is not affected. Brief Description of the Drawings
[0017] FIG. 1(a) and FIG. 1(b) are schematic diagrams of the trailing edge flap spanwise outer wing surface structure of the present utility model near the trailing edge flap. Among them, FIG. 1(a) shows the local structure of the upper surface of the flap in the trailing edge flap spanwise outer wing surface structure of the present utility model, and FIG. 1(b) shows the local structure of the lower surface of the flap in the trailing edge flap spanwise outer wing surface structure of the present utility model.
[0018] FIG. 2(a) and FIG. 2(b) are schematic diagrams for comparing the flow fields on the lower surface of the flap in the outboard wing surface structure of the trailing edge flap before and after improvement. Among them, FIG. 2(a) shows the flow field on the lower surface of the flap in the outboard wing surface structure of the trailing edge flap before improvement, and FIG. 2(b) shows the flow field on the lower surface of the flap in the outboard wing surface structure of the trailing edge flap of the present invention after improvement.
[0019] FIG. 3(a) and FIG. 3(b) are schematic diagrams for comparing the pressure distributions on the upper surface of the flap in the outboard wing surface structure of the trailing edge flap before and after improvement. Among them, FIG. 3(a) shows the pressure distribution on the upper surface of the flap in the outboard wing surface structure of the trailing edge flap before improvement, and FIG. 3(b) shows the pressure distribution on the upper surface of the flap in the outboard wing surface structure of the trailing edge flap of the present invention after improvement.
[0020] FIG. 4(a) and FIG. 4(b) are schematic diagrams for comparing the spatial vortex size distributions at the flap edge in the outboard wing surface structure of the trailing edge flap before and after improvement. Among them, FIG. 4(a) shows the spatial vortex size distribution at the flap edge in the outboard wing surface structure of the trailing edge flap before improvement, and FIG. 4(b) shows the spatial vortex size distribution at the flap edge in the outboard wing surface structure of the trailing edge flap of the present invention after improvement. Detailed implementation manners
[0021] Hereinafter, with reference to FIGS. 1(a) and 1(b), the trailing edge flap structure of the present invention will be described in detail. Among them, FIGS. 1(a) and 1(b) are schematic diagrams of the outboard wing surface structure of the trailing edge flap of the present invention near the trailing edge flap. Among them, FIG. 1(a) shows a partial structure of the upper surface of the flap in the outboard wing surface structure of the trailing edge flap of the present invention, and FIG. 1(b) shows a partial structure of the lower surface of the flap in the outboard wing surface structure of the trailing edge flap of the present invention.
[0022] The outboard wing surface structure of the trailing edge flap of the present invention is the wing surface structure on the outboard side in the extension direction (spanwise) of the trailing edge flap 200 in the flap installed on the main wing 100 of the aircraft. At the end position of the outer lower surface of the existing trailing edge flap 200, there is a section of airfoil plate 210 extending along the outer edge of the trailing edge flap 200. On the lower surface of the existing main wing 100, there is a recovery groove 110 for accommodating the airfoil plate 210. When the trailing edge flap 200 is opened relative to the main wing 100, the airfoil plate 210 extends relative to the trailing edge flap 200 and the main wing 100 to improve the aerodynamic characteristics. When the trailing edge flap 200 is retracted relative to the main wing 100 to the cruise configuration, the airfoil plate 210 extending in the spanwise direction from the trailing edge flap 200 fits with the recovery groove 110 on the lower surface of the main wing 100, so as to ensure that the aerodynamic shape in the original cruise configuration is not affected.
[0023] In addition, preferably, one end of the airfoil plate 210 is disposed near the installation site where the trailing edge flap (200) is installed on the main wing 100. At this time, the chord length L3a of the airfoil plate 210 is shorter than the chord length L2a of the trailing edge flap 200.
[0024] In addition, the other end of the airfoil plate 210 is disposed at the outermost chordwise position of the trailing edge flap (200). And similarly at this time, the chord length L3a of the airfoil plate 210 is shorter than the chord length L2a of the trailing edge flap 200.
[0025] In addition, the spanwise length L3b of the airfoil plate 210 is not unique and can be determined according to the flow separation region on the trailing edge flap 200.
[0026] In the present utility model, due to the provision of the airfoil plate 210, the boundary layer separation in some regions on the trailing edge flap 200 can be effectively reduced, and the flow field at the flap edge can be improved. As shown in FIGS. 2(b) and 3(b), compared with the original configuration of the trailing edge flap 200 without the airfoil plate shown in FIGS. 2(a) and 3(a), the flow field on the lower surface of the flap and the pressure distribution on the upper surface of the flap in the outboard wing surface structure of the trailing edge flap in the spanwise direction have been significantly improved. The linear segment of the lift coefficient can be effectively increased by about 0.02, and the lift-to-drag ratio has been increased by 0.07 - 0.14.
[0027] In addition, in the present utility model, due to the provision of the airfoil plate 210, the shedding vortices generated at the flap edge can be reduced, and the noise at the flap edge can be lowered. As shown in FIG. 4(b), compared with
[0028] (a) the original configuration of the trailing edge flap 200 without the airfoil plate, the size distribution of the spatial vortices at the flap edge has been significantly improved, and the noise at the flap edge has been significantly reduced.
[0029] Those skilled in the art will readily think of other advantages and modifications. Therefore, in its broader sense, the present utility model is not limited to the specific details and representative embodiments shown and described herein. Therefore, modifications can be made without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.
Claims
1. A trailing edge flap outboard wing surface structure, the trailing edge flap outboard wing surface structure being a wing surface structure on the outer side in the extension direction of a trailing edge flap (200) in a flap of a main wing (100) of an aircraft, characterized in that, On the outer lower surface in the extension direction of the trailing edge flap, there is provided a wing profile plate (210) extending along the outer edge of the trailing edge flap (200). When the trailing edge flap (200) is opened relative to the main wing (100), the wing profile plate (210) projects relative to the trailing edge flap (200) and the main wing (100).
2. The trailing edge flap outboard wing surface structure according to claim 1, characterized in that, On the lower surface of the main wing (100), there is provided a recovery groove (110) for receiving the wing profile plate (210). When the trailing edge flap (200) is retracted relative to the main wing (100) to the cruise configuration, the wing profile plate (210) extending in the span direction from the trailing edge flap (200) fits with the recovery groove (110) on the lower surface of the main wing (100).
3. The trailing edge flap outboard wing surface structure according to claim 1 or 2, characterized in that, One end of the wing profile plate (210) is provided near the installation position where the trailing edge flap (200) is installed on the main wing (100).
4. The trailing edge flap outboard wing surface structure according to claim 3, characterized in that, The chord length (L3a) of the wing profile plate (210) is shorter than the chord length (L2a) of the trailing edge flap (200).
5. The trailing edge flap outboard wing surface structure according to claim 3, characterized in that, The span length (L3b) of the wing profile plate (210) is determined according to the flow separation region on the trailing edge flap (200).