Aircraft wing components

Abstract

Aircraft wing assembly. An aircraft and an aircraft wing assembly for an aircraft. The wing assembly includes a wing body assembly, the wing body assembly including a wing body; and at least one projection connected to the wing body. The projection extends rearward from the rear side of the wing body assembly, the leading edge of the wing body assembly defines a leading edge line, the trailing edge of the wing body assembly defines a trailing edge line extending between an inner end and an outer end, the trailing edge includes the trailing edge of the projection, the trailing edge line is a smooth line, a chord distance is defined from the leading edge line to the trailing edge line in the longitudinal direction, and the chord distance at the center of the projection is greater than the chord distance inside the projection and outside the projection.

Description

Technical Field

[0001] The present technology generally relates to aircraft and aircraft wing assemblies. Background Art

[0002] In some aircraft, a nacelle extending downward from the wing assembly provides propulsion for the aircraft. However, the presence of a pylon supporting and connecting the nacelle to the wing assembly locally reduces lift, changes span loading across the aircraft, and increases drag on the wing assembly.

[0003] One way to counteract these disadvantages is to reshape the wing airfoil near the pylon to restore local lift. This approach may be limited by the separation of the airflow along the trailing edge caused by local changes in the airfoil.

[0004] To compensate for the shortcomings of this solution, an additional "carrot" fairing was added. This fairing was added at the junction of the wing trailing edge and the pylon in order to at least partially recover from the airflow separation caused by the reshaped wing. Therefore, multiple changes / additions to the wing were required to deal with the interference caused by the nacelle pylon.

[0005]

[0006] Therefore, a wing assembly that addresses some of the above-mentioned inconveniences is desired. Summary of the invention

[0006] The purpose of the present technology is to improve at least some of the inconveniences existing in the prior art.

[0007] In some aspects of the present technology, a wing body assembly for an aircraft is provided, the wing body assembly including a generally smooth / integrally formed protrusion to provide local additional lift. The protrusion produces a local increase in the chord length of the wing body, which can improve air load distribution, reduce drag, and increase the flutter margin. For example, this can be used to compensate for the pylon supporting the nacelle. Compared with adding a fairing or trailing edge extension, one or more integrally formed protrusions are smoothly connected to other parts of the wing. In this way, vortices or airflow interruptions can be at least partially reduced. The local extension provided by the protrusion further maintains the streamlined characteristics of the wing, rather than adding volume at the top or below the airfoil.

[0008] On the one hand, an aircraft wing assembly for an aircraft is provided, the wing assembly including a wing body assembly, the wing body assembly including: a wing body; and at least one protrusion connected to the wing body, the at least one protrusion extending generally rearward from the rear side of the wing body assembly, the leading edge of the wing body assembly defining a leading edge line connecting the frontmost points of the wing body assembly and extending between the inner end and the outer end of the wing body assembly, the trailing edge of the wing body assembly defining a trailing edge line connecting the rearmost points of the wing body assembly, the trailing edge extending between the inner end and the outer end, the trailing edge including the trailing edge of the at least one protrusion, the trailing edge line being a smooth line from the outer end to the inner end, a chord distance being defined from the leading edge line to the trailing edge line in a longitudinal direction defined by the aircraft, the chord distance at the center of the at least one protrusion being greater than the chord distance at at least a first point of the trailing edge line on the inner side of the at least one protrusion and at least a second point of the trailing edge line on the outer side of the at least one protrusion.

[0009] In some embodiments, the chord distance at any point within the at least one protruding portion is greater than the chord distance at the first point and the chord distance at the second point.

[0010] In some embodiments, the at least one protrusion has a generally curved form. In some cases, it may be a sinusoidal form.

[0011] In some embodiments, a nominal trailing edge line is defined from a point on the trailing edge line immediately inboard of at least one protrusion to a point on the trailing edge line immediately outboard of at least one protrusion; a nominal chord distance is defined from the leading edge line to the nominal trailing edge line at a given point aligned with a lateral center of at least one protrusion; and the chord distance at the given point is at least 2% greater than the nominal chord distance at the given point.

[0012] In some embodiments, the chord distance at a given point is no more than 20% greater than the nominal chord distance at the given point.

[0013] In some embodiments, the aircraft wing assembly further comprises a pylon connected to the wing body, the pylon being adapted to support the nacelle; and wherein the at least one protrusion is at least partially laterally aligned with the pylon.

[0014] In some embodiments, the wing body includes at least one flap and at least one flap fairing; the at least one protruding portion is connected to the at least one flap; and the at least one protruding portion is at least partially laterally aligned with the at least one flap fairing.

[0015] In some embodiments, the wing body includes at least one aileron; and the at least one protruding portion is connected to the at least one aileron.

[0016] In some embodiments, a top camber of the wing body assembly including the at least one protruding portion is continuous.

[0017] In some embodiments, the bottom curved surface of the wing body assembly including the at least one protruding portion is continuous.

[0018] In some embodiments, the width of the wing is defined as the distance from the wing tip to the wing root; and the at least one protruding portion has a maximum lateral width greater than 5% and less than 40% of the wing width.

[0019] In another aspect of the present technology, an aircraft is provided, which includes a fuselage; and two wing assemblies arranged in opposite directions. Each wing assembly includes a wing body assembly, the wing body assembly including: a wing body; and at least one protrusion connected to the wing body, the at least one protrusion extending generally rearward from the rear side of the wing body assembly, the leading edge of the wing body assembly defines a leading edge line connecting the frontmost points of the wing body assembly and extending between the inner and outer ends of the wing body assembly, the trailing edge of the wing body assembly defines a trailing edge line connecting the rearmost points of the wing body assembly, the trailing edge extending between the inner and outer ends, the trailing edge including the trailing edge of the at least one protrusion, the trailing edge line being a smooth line from the outer end to the inner end, a chord distance being defined from the leading edge line to the trailing edge line in a longitudinal direction defined by the aircraft, the chord distance at the center of the at least one protrusion being greater than the chord distance at at least a first point of the trailing edge line inside the at least one protrusion and at least a second point of the trailing edge line outside the at least one protrusion.

[0020] In some embodiments, the at least one protruding portion of each wing assembly has a maximum lateral width greater than 5% of the wing width and less than 40% of the wing width.

[0021] In some embodiments, for each wing assembly: a nominal trailing edge line is defined from a point on the trailing edge line immediately inboard of the at least one protruding portion to a point on the trailing edge line immediately outboard of the at least one protruding portion; a nominal chord distance is defined from the leading edge line to the nominal trailing edge line at a given point aligned with a lateral center of the at least one protruding portion; and the chord distance at the given point is at least 2% greater than the nominal chord distance at the given point.

[0022] In some embodiments, for each wing assembly, the chord distance at a given point is no more than 20% greater than the nominal chord distance at the given point.

[0023] In some embodiments, each wing assembly further comprises a pylon connected to the wing body and a nacelle connected to the pylon; and the at least one protruding portion of a corresponding one of the wing assemblies is at least partially laterally aligned with the pylon.

[0024] In some embodiments, for each wing assembly: the wing body includes at least one flap and at least one flap fairing; the at least one protrusion is connected to the at least one flap; and the at least one protrusion is at least partially laterally aligned with the at least one flap fairing.

[0025] In some embodiments, for each wing assembly: the wing body includes at least one aileron; and the at least one protruding portion is connected to the at least one aileron.

[0026] In some embodiments, for each wing assembly, a top curved surface of the wing body assembly including the at least one protruding portion is continuous.

[0027] In some embodiments, for each wing assembly, a bottom curved surface of the wing body assembly including the at least one protruding portion is continuous.

[0028] For the purposes of this application, terms related to spatial orientation (such as top and bottom) should be understood in the reference frame of the aircraft. Unless otherwise specified in this application, when describing or referring to components or subassemblies of an aircraft separately from the aircraft, terms related to spatial orientation should be understood as they should be understood when these components or subassemblies are installed on the aircraft.

[0029] The embodiments of the present technology each have at least one of the above-mentioned purposes and / or aspects, but not necessarily all of them. It should be understood that some aspects of the present technology generated by attempting to achieve the above-mentioned purpose may not meet the purpose, and / or may meet other purposes not specifically listed herein.

[0030] Additional and / or alternative features, aspects, and advantages of embodiments of the present technology will become apparent from the following description, drawings, and appended claims. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] For a better understanding of the present technology and other aspects and further features thereof, reference is made to the following description used in conjunction with the accompanying drawings, in which:

[0032] Figure 1 is a top plan view of an aircraft according to the present technology;

[0033] Figure 2 yes Figure 1 A top plan view of a wing main assembly of an aircraft;

[0034] Figure 3 yes Figure 2 A partial close-up view of the main wing assembly;

[0035] Figure 4 It is along Figure 2 The line 4-4 is intercepted Figure 2 a cross-sectional view of a portion of a wing body of a wing body assembly;

[0036] Figure 5 It is along Figure 2 The line 5-5 is intercepted Figure 2 a cross-sectional view of a portion of a wing body of a wing body assembly;

[0037] Figure 6 is a top plan view of another embodiment of a wing body assembly according to the present technology; and

[0038] Figure 7 is a bottom plan view of yet another embodiment of a wing body assembly according to the present technology.

[0039] It should be noted that the drawings are not necessarily drawn to scale. DETAILED DESCRIPTION

[0040] The present technology will now be described in more detail with reference to the accompanying drawings.While the present technology is generally described with reference to an aircraft in which the engines are connected to the wings, at least some aspects of the present technology are also applicable to wings of an aircraft in which the engines are connected to the fuselage.

[0041] refer to Figure 1 , an aircraft 10 according to the present technology is shown. The aircraft 10 defines a longitudinal direction 12 that is generally aligned with a forward direction of travel of the aircraft 10. A lateral direction 14 is defined perpendicular to the longitudinal direction 12. The aircraft 10 includes a fuselage 50 that contains various portions of the aircraft 10, including a cockpit, a passenger area, storage areas, etc. Additional aspects of the fuselage 50 will not be described in detail herein.

[0042] The aircraft 10 also includes two oppositely disposed wing assemblies 90 connected to the fuselage 50. Each wing assembly 90 includes a wing body assembly 100 and a pylon 70 (described further below). In some embodiments, the wing assembly 90 may include components in addition to the wing body assembly 100 described herein, however, the details herein will generally be limited to the wing body assembly 100. Since the wing body assemblies 100 are mirror images of each other, for simplicity, only the right wing body assembly 100 will be described herein. In some embodiments, the two wing body assemblies 100 may be different. The wingspan 15 of the aircraft 10 is defined as from the wing tip 104 of the left wing body assembly 100 to the wing tip 104 of the right wing body assembly 100. It is contemplated that the wingspan 15 may be larger or smaller relative to the size of the fuselage 50, depending on the particular embodiment.

[0043] Reference Figures 2 to 5 , the right wing body assembly 100 will be described in more detail. The wing body assembly 100 has an inboard end 102, also referred to as a wing root 102, where the wing body assembly 100 is connected to the fuselage 50. At the end opposite the inboard end 102, the wing body assembly 100 has an outboard end 104, also referred to as a wing tip 104 (mentioned above). Figure 2 As shown, a width 108 of the wing body assembly 100 is defined as measured from the wing root 102 to the wing tip 104 along the lateral direction 14 .

[0044] The wing body assembly 100 includes a wing body 110. The wing body 110 is formed in part by a body 105. The body 105 provides the primary structure and form of the wing body assembly 100. The body 105 includes a structural frame (not shown) covered with an upper skin and a lower skin to provide smooth travel through the air. Although shown as an integrally connected body, in some embodiments, it is contemplated that the body 105 may include multiple components connected together. The structure and skin of the wing body 110 are manufactured using an aluminum alloy, but the wing body 110 may be manufactured from a variety of materials, including but not limited to various metal alloys and composite materials.

[0045] In the present embodiment, the wing body 110 includes two flaps 150 that are movably connected to the body 105. Depending on the embodiment, it is contemplated that the wing body 110 may include more or fewer flaps 150. Each flap 150 is movable between at least two positions: a retracted position, in which the top side, bottom side, and rear side of the flap 150 are generally aligned with the body 105; and a deployed position, in which the flap 150 is at least displaced rearwardly relative to the body 105. It is contemplated that the flap 150 may be moved to another position relative to the body 105.

[0046] The wing body 110 is also partially formed by an aileron 160, which is pivotally connected to the body 105 outboard of the flap 150. Depending on the embodiment, it is contemplated that the wing body 110 may include more ailerons 160 or no ailerons 160. The aileron 160 can move between several positions, including at least the following two positions: a retracted position in which the aileron 160 lies flat on the body 105 (generally matching the upper curvature of the body 105); and a deployed position in which the aileron 160 is hinged upward or downward relative to the body 105 (thereby changing the upper curvature of the wing body 110).

[0047] The wing body 110 in the figures is only an illustrative, non-limiting embodiment of a wing body according to the present technology. In some embodiments, the wing body 110 may also include one or more slats and / or winglets.

[0048] The form of the wing body assembly 100 is generally described by its leading edge, trailing edge, chord distance, upper curved surface and lower curved surface; each of these is described below. It should be noted that the particular form and dimensions of the wing assembly 100 shown are only one possible embodiment of the wing.

[0049] The leading edge 112 of the wing body assembly 100 defines a leading edge line 122 connecting the forward-most points of the wing body assembly 100, which extends between the inboard end 102 and the outboard end 104. The trailing edge 114 of the wing body assembly 100 similarly defines a trailing edge line 124 connecting the rearward-most points of the wing body assembly 100, which extends between the inboard end 102 and the outboard end 104.

[0050] The chord distance is measured in a straight line from the leading edge line 122 to the trailing edge line 124 in the longitudinal direction 12 across the wing body assembly 100. Since the leading edge line 122 and the trailing edge line 124 of the wing body assembly 100 are not parallel, the chord distance varies laterally across the wing body assembly 100. Figure 4 and Figure 5 , the cross section of the wing body assembly 100 further illustrates an upper curved surface 192 and a lower curved surface 194 at two different laterally separated locations on the wing body assembly 100. The upper curved surface 192 describes the curvature of the top surface of the wing body assembly 100; similarly, the lower curved surface 194 describes the curvature of the lower surface of the wing body assembly 100.

[0051] from Figure 2As can be seen schematically in the figure, and as mentioned above, the wing assembly 90 also includes a pylon 70 connected to the wing body 110, and in particular to the underside of the body 105 (shown in phantom). The pylon 70 supports and is connected to a nacelle 75 for supporting an engine for propelling the aircraft 10. In some embodiments, the wing body 110 may include a plurality of pylons 70 and nacelles 75. It is also contemplated that the wing assembly 90 may not include any pylon / nacelle combination, and that propulsion of the aircraft 10 may be achieved in different ways, including, for example, fuselage-mounted engines.

[0052] According to the present technology, the wing body assembly 100 further includes a protruding portion 130 connected to the wing body 110 and forming a smooth surface with the wing body 110 .

[0053] In the illustrated embodiment, the projection 130 is integrally formed with the body 105. As will be seen below with reference to the accompanying drawings, different embodiments of the projection may be integrally formed with different portions of the wing body 110. As can also be seen from the other figures, the wing body assembly 100 may include more than one projection 130.

[0054] The projection 130 generally extends rearwardly from the rear side of the wing body 110. As such, the trailing edge 114 of the wing body assembly 100 includes the trailing edge of the projection 130. In the present embodiment, the projection 130 has a generally curved form as viewed from the top side of the aircraft 10, but different forms are contemplated, including, for example, a sinusoidal form.

[0055] Although formed smoothly with the surface of the wing body 110, the protruding portion 130 may generally be better understood if the form of the wing body 110 is considered excluding the protruding portion 130. For example, referring to Figure 3 , a nominal trailing edge line 126 may be defined, formed by inserting the trailing edge line 124 through the protruding portion 130 to connect the substantially straight trailing edge 114 of the wing body 110 on both sides of the protruding portion 130. Figure 3 As shown by the dashed line in FIG, a nominal trailing edge line 126 is defined from a point 125 on the trailing edge line 124 immediately inboard of the protruding portion 130 to a point 127 on the trailing edge line immediately outboard of the protruding portion 130. The protruding portion 130 can then be considered as the portion of the wing body assembly 100 extending behind the nominal trailing edge line 126.

[0056] The protrusion 130 may also be understood in terms of the chord distance of the wing body assembly 100 transverse to the protrusion 130, as compared to the chord distance of the wing body assembly 100 inboard and outboard of the protrusion 130. Figure 3As shown, the nominal chord distance 128 is defined from the leading edge line 122 to the nominal trailing edge line 126, transverse to the lateral center of the protruding portion 130. The chord distance 132 at the center of the protruding portion 130 is the actual chord distance of the wing body assembly 100 at this lateral location. The chord distance 132 is greater than the nominal chord distance 128 at the same point, and the difference between the two is the longitudinal length of the protruding portion 130. The chord distance 132 at the center of the protruding portion 130 is also greater than the chord distance at points 125, 127 of the trailing edge lines 124 inboard and outboard of the protruding portion 130. In this embodiment, any chord distance transverse to the protruding portion 130 is greater than the chord distance at points 125, 127, but this may not always be the case depending on the specific shapes of the wing body 110 and the protruding portion 130.

[0057] It is contemplated that the chord distance 132 may be less than the illustrated embodiment, but the chord distance 132 through the center of the protruding portion 130 is at least about 2% greater than the nominal chord distance 128. Similarly, it is contemplated that the chord distance 132 may be greater than the illustrated embodiment, but the chord distance 132 through the center of the protruding portion 130 is no more than about 20% greater than the nominal chord distance 128 at the same point.

[0058] The protruding portion 130 has a width 135, which is defined as the lateral distance between points (represented herein as points 125 and 127) at which the protruding portion 130 is generally offset from the nominal trailing edge line 126. The protruding portion 130 may be wider or narrower than shown, but has a maximum lateral width that is less than about 40% of the width 108 of the wing body assembly 100. The width 135 of the protruding portion 130 should be at least 5% of the width 135 of the wing body assembly 100.

[0059] As at least Figure 2 As can be seen in FIG. 1 , the trailing edge line 124 is a generally smooth line from the outboard end 104 to the inboard end 102, wherein the flaps 150 and the ailerons 160 are in their retracted positions. Specifically, the trailing edge line 124 is a smooth line along the protrusion 130 and the portion of the wing body 110 adjacent to the protrusion 130. For example, in the case where the protrusion 130 is smoothly formed with the surface of the wing body 110, the smooth line along and around the protrusion 130 has no kinks or discontinuities, so as to minimize the generation of vortices and help minimize drag.

[0060] As from Figure 4 and Figure 5As can be seen in FIG. 1 , the projection 130 smoothly integrated with the wing body 110 also allows for smooth continuation of the top and bottom surfaces from the wing body 110 to the projection 130. The upper and lower curved surfaces 192, 194 of the wing body assembly 100 are continuous at the portion including the projection 130. By comparison Figure 4 and Figure 5 It can be seen that the airfoil of the wing body assembly 100 generally maintains a streamlined character with and without the projection 130, but in some embodiments the airfoil may be more significantly modified by the projection 130. Similarly, for the smooth trailing edge 124, the continuous top and bottom curved surfaces 192, 194 help minimize vortex generation and airflow disruption.

[0061] In the present embodiment, the projection 130 is partially laterally aligned with the pylon 70. It is contemplated that the projection 130 may be more or less aligned with the pylon 70 than shown. The projection 130 provides a localized increase in lift to help compensate for the loss of lift caused by the pylon 70 so as to help ensure a smooth spanwise load distribution. It is contemplated that one or more projections 130 may be included to balance uneven lift loading across a given wing assembly, including situations where the load distribution is not necessarily directly caused by a protruding feature (such as the pylon 70). The projection 130 may also allow the designer of the wing assembly 100 to also reduce the lift coefficient of a portion of the wing assembly 100 while maintaining overall lift and smooth spanwise wing loading.

[0062] refer to Figure 6 , shows another non-limiting example embodiment of a wing body assembly 200 according to the present technology.

[0063] The wing body assembly 200 includes a wing body 210 having a body 205. The wing body 210 includes an aileron 260 pivotably connected to the body 205. The wing body 210 also includes a projection 230. In this embodiment, the projection 230 is integrally connected to the aileron 260. It is contemplated that more than one projection 230 may be integrally connected to the aileron 260. It is also contemplated that the wing body assembly 200 may include additional projections, in addition to the projection 230, that are integrally connected to different portions of the wing body 210. The arrangement of the projection 230 in this embodiment helps to generate additional localized lift to offset at least some of the drag generated by the aileron 260.

[0064] refer to Figure 7 , shows yet another embodiment of a wing assembly 300 according to the present technology.

[0065] The wing assembly 300 includes a wing body 310. The wing body 310 also includes three flaps 350. Depending on the specific circumstances of a given embodiment, the wing body 310 can include more or less flaps 350. Each flap 350 includes a flap fairing 320 below the flap 350 and extending backward from it (when the flap 350 is in the retracted position). In some embodiments, one or more of the flaps 350 can each include a plurality of fairings 320.

[0066] In this embodiment, each flap 350 includes an integrally connected protruding portion 330. Each protruding portion 330 is generally aligned laterally with a corresponding flap fairing 320. It is contemplated that more than one protruding portion 330 may be integrally connected to a given flap 350. It is also contemplated that, in addition to the protruding portion 330, the wing body assembly 300 may also include additional protruding portions integrally connected to different portions of the wing body 310. The arrangement of the protruding portion 330 in this embodiment helps to generate additional local lift to offset at least some of the lift losses generated by the flap fairing 320, particularly when the flap 350 is in the retracted position.

[0067] Modifications and improvements to the above-described embodiments of the present technology may become apparent to those skilled in the art.The foregoing description is intended to be illustrative, rather than limiting.

Claims

1. An aircraft wing assembly for an aircraft, the wing assembly comprising: A wing body assembly, the wing body assembly comprising: a wing body including at least one flap and at least one flap fairing; and at least one projection connected to the wing body and extending generally rearwardly from a rear side of the wing body assembly, the at least one protruding portion being connected to the at least one flap, the at least one protruding portion being at least partially laterally aligned with the at least one flap fairing; The leading edge of the wing body assembly defines a leading edge line connecting the forward-most points of the wing body assembly and extending between an inboard end and an outboard end of the wing body assembly; The trailing edge of the wing body assembly defines a trailing edge line, the trailing edge line connecting the rearmost points of the wing body assembly, the trailing edge extending between the inboard end and the outboard end, the trailing edge including the trailing edge of the at least one projection, the trailing edge line being a smooth line from the outboard end to the inboard end, A chord distance is defined from the leading edge line to the trailing edge line in a longitudinal direction defined by the aircraft, A chord distance at a center of the at least one protruding portion is greater than a chord distance at at least a first point of the trailing edge line inside the at least one protruding portion and at least a second point of the trailing edge line outside the at least one protruding portion.

2. The aircraft wing assembly according to claim 1, wherein: A chord distance at any point within the at least one protruding portion is greater than the chord distance at the first point and the chord distance at the second point.

3. The aircraft wing assembly according to claim 1, wherein: The at least one protruding portion has a generally curved shape.

4. The aircraft wing assembly of claim 1, wherein: defining a nominal trailing edge line from a point on the trailing edge line immediately inboard of the at least one protruding portion to a point on the trailing edge line immediately outboard of the at least one protruding portion; defining a nominal chord distance from the leading edge line to the nominal trailing edge line at a given point aligned with a lateral center of the at least one protruding portion; and The chord distance at the given point is at least 2% greater than a nominal chord distance at the given point.

5. The aircraft wing assembly according to claim 4, wherein: The chord distance at the given point is no more than 20% greater than the nominal chord distance at the given point.

6. The aircraft wing assembly of claim 1, wherein: The wing body includes at least one aileron; and The at least one protruding portion is connected to the at least one flap.

7. The aircraft wing assembly according to claim 1, wherein: The top curved surface of the wing body assembly including the at least one protruding portion is continuous.

8. The aircraft wing assembly of claim 1, wherein: The bottom curved surface of the wing body assembly including the at least one protruding portion is continuous.

9. The aircraft wing assembly of claim 1, wherein: The width of the wing is defined as the distance from the wing tip to the wing root; and The maximum lateral width of the at least one protruding portion is greater than 5% and less than 40% of the width of the wing.

10. An aircraft, comprising: body; and Two wing assemblies arranged in opposite directions, each wing assembly comprising: A wing body assembly, the wing body assembly comprising: a wing body including at least one flap and at least one flap fairing; and at least one projection connected to the wing body, the at least one projection extending generally rearwardly from a rear side of the wing body assembly, the at least one projection connected to the at least one flap, the at least one projection at least partially laterally aligned with the at least one flap fairing; The leading edge of the wing body assembly defines a leading edge line connecting the forward-most points of the wing body assembly and extending between an inboard end and an outboard end of the wing body assembly; The trailing edge of the wing body assembly defines a trailing edge line, the trailing edge line connecting the rearmost points of the wing body assembly, the trailing edge extending between the inboard end and the outboard end, the trailing edge including the trailing edge of the at least one projection, the trailing edge line being a smooth line from the outboard end to the inboard end, defining a chord distance from the leading edge line to the trailing edge line in a longitudinal direction defined by the aircraft, A chord distance at a center of the at least one protruding portion is greater than a chord distance at at least a first point of the trailing edge line inside the at least one protruding portion and at least a second point of the trailing edge line outside the at least one protruding portion.

11. The aircraft of claim 10, wherein the maximum lateral width of the at least one protruding portion of each wing assembly is greater than 5% and less than 40% of the width of the wing.

12. The aircraft according to claim 10, wherein: For each wing assembly: defining a nominal trailing edge line from a point on the trailing edge line immediately inboard of the at least one protruding portion to a point on the trailing edge line immediately outboard of the at least one protruding portion; defining a nominal chord distance from the leading edge line to the nominal trailing edge line at a given point aligned with a lateral center of the at least one protruding portion; and The chord distance at the given point is at least 2% greater than a nominal chord distance at the given point.

13. The aircraft according to claim 12, wherein: For each wing assembly, the chord distance at the given point is no more than 20% greater than the nominal chord distance at the given point.

14. The aircraft according to claim 10, wherein: For each wing assembly: The wing body includes at least one aileron; and The at least one protruding portion is connected to the at least one flap.

15. The aircraft of claim 10, wherein: For each wing assembly, the top curved surface of the wing body assembly including the at least one protruding portion is continuous.

16. The aircraft of claim 10, wherein: For each wing assembly, the bottom curved surface of the wing body assembly including the at least one protruding portion is continuous.

Images