JP2011162154A - High lift force-generating device, wing and slat - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a high lift force-generating device and a wing, which can suppress generation of aerodynamic noise while suppressing increase in body weight. <P>SOLUTION: A recess and projection part 20 is formed in a bottom plate 7 extending rearward in a lower surface of a slat 3, so that a position in which air flow flowing along the surface of the slat 3 is exfoliated from the bottom plate 7 to generate a vortex is made uneven in the air flow direction. Thereby, the vortex generated in a recess 20A and the vortex generated in a projection 20B are short in correlation with each other, and the vortices are hardly connected to each other, and becomes the independent vortexes, so that the generated vortex is weak in strength, which can reduce the pressure fluctuation on a body surface, and suppress generation of the aerodynamic sound. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to a high lift generator, wing, and slat suitable for suppressing generation of aerodynamic noise in an aircraft.

  Noise generated when an aircraft takes off and landing is a major problem for the environment around the airport. Examples of such noise include engine noise generated from the engine, aerodynamic noise generated from a high lift device (for example, slats and flaps) and legs.

  The high lift device, which is one of the above noise sources, is a device for obtaining the aerodynamic characteristics required for takeoff and landing of aircraft, so it has been designed with an emphasis on aerodynamic characteristics while considering noise reduction. The design was not made.

  However, since noise is a major problem as described above, efforts have been made to reduce noise for high lift devices. For example, a technique for reducing noise generated from a slat, which is a high lift device, has been proposed (see, for example, Patent Document 1).

  Patent Document 1 describes a technique in which a balloon that can be inflated and deflated is disposed in a recess facing a main wing in a slat. By doing so, when the slat is deployed (separated) from the main wing, the balloon is inflated to fill the recess, thereby suppressing the generation of aerodynamic noise due to the flow disturbance caused by the recess. The concave portion described above is for forming a space that avoids interference with the tip of the main wing when the slat is accommodated in the main wing (in contact with the main wing).

US Pat. No. 6,394,396

  However, in the technique described in Patent Document 1, in addition to the mechanism for moving the slat closer to and away from the main wing, the mechanism for inflating and contracting the balloon described above needs to be arranged inside the slat or the main wing. . There is little space in the interior of the slat or main wing, and there is a structural (spatial) problem in arranging such a mechanism.

In particular, in order to inflate the above-mentioned balloon, it is necessary to send high-pressure air into the balloon. In order to secure this high-pressure air, it was necessary to provide a dedicated compressor or a pipe for guiding the high-pressure air from the engine. In order to arrange such a mechanism, there is a problem in structure (spatial).
Furthermore, there is a problem that the weight of the aircraft increases by adding these mechanisms.

  Further, in the state in which the slats are stored, a space for accommodating the balloon between the main wing and the slats is necessary, but it is difficult to secure such a space particularly in a small machine and a medium machine.

  The present invention has been made to solve the above-described problem, and even in a small machine or a medium-sized machine, the high lift that can suppress the generation of aerodynamic noise while suppressing an increase in the weight of the machine. It aims at providing a generator and a wing | blade.

For this purpose, the high lift generator of the present invention is arranged along the front edge of the main wing, and has a position close to the front edge of the main wing and a position spaced forward from the front edge. A slat that is movable between the slat and the bottom plate of the slat, and is integrally provided continuously and extends rearward, and when the slat is close to the front edge of the main wing, Aerodynamic sound suppression that suppresses aerodynamic noise caused by vortices that are formed at the rear end of the plate body and flow from the front to the rear in the traveling direction along the lower surface of the slat And the aerodynamic sound suppression unit makes the vortex separation position from the rear end of the plate member non-uniform in the wing width direction where the front edge of the main wing is continuous to make a vortex with a short correlation , A convex part projecting rearward from the plate provided on the lower surface of the slat, and the convex part A recess is concave in front, characterized in that it is formed alternately in the spanwise direction.
Here, the convex portion and the concave portion can be any one of a semicircular shape, a rectangular shape, and a triangular shape. Of course, other shapes can be used.
In addition, a strip-shaped strip portion extending rearward at the rear end portion of the plate body may be arranged at intervals in the wing width direction to form a concave portion and a convex portion.
In this way, by alternately forming convex portions projecting rearward from the plate provided on the lower surface of the slat and concave portions that are concave forward with respect to the convex portions in the blade width direction, The vortex separation position from the rear end portion of the plate body in the blade width direction where the edges are continuous can be made nonuniform between the convex portion and the concave portion, and the vortex having a short correlation can be obtained. As a result, the strength of the vortex generated by the airflow flowing from the front to the back in the traveling direction along the lower surface of the slat is weakened, and the pressure fluctuation on the plate surface is reduced. With such an effect, it is possible to suppress aerodynamic noise generated by the airflow flowing from the front to the rear in the traveling direction along the lower surface of the slat.

The present invention also provides a slat that is disposed along the front edge of the main wing and is movable between a position close to the front edge of the main wing and a position spaced forward from the front edge. And a plate body provided integrally with the lower surface plate of the slat and extending rearward, and in a state where the slat is close to the front edge of the main wing, provided to close the space between the slat and the main wing, An aerodynamic sound suppression unit that is formed at the rear end portion of the plate body and suppresses aerodynamic noise caused by vortices generated by an airflow flowing from the front to the back in the traveling direction along the lower surface of the slat; A high lift generator characterized in that it has an airflow passage section that passes through the top and bottom of the plate body and allows a part of the airflow flowing along the slats and the bottom surface of the plate body to pass above the plate body. You can also.
The airflow passage portion can be a plurality of holes or slits formed in the plate.
According to such a configuration, a part of the airflow that flows along the slats and the lower surface of the plate passes through the airflow passage and flows above the plate. As a result, the shear force of the boundary layer is reduced, the strength of the vortex generated by the airflow flowing from the front to the back in the traveling direction along the lower surface of the slat is weakened, and the pressure fluctuation on the plate surface is reduced. With such an effect, it is possible to suppress aerodynamic noise generated by the airflow flowing from the front to the rear in the traveling direction along the lower surface of the slat.

  Moreover, this invention can also be made into a wing | blade characterized by including a main wing | blade and the high lift generator as described in any one of Claim 1-6.

  The present invention provides a slat that is disposed along the front edge of a main wing of an aircraft and is movable between a position close to the front edge of the main wing and a position spaced forward from the front edge. The slat is formed integrally with the bottom plate of the slat so as to extend rearward and close the space between the slat and the main wing when the slat is close to the front edge of the main wing. An aerodynamic sound suppression unit that is formed at the rear end of the plate body and suppresses aerodynamic noise caused by vortices generated by an airflow flowing from the front to the back in the traveling direction along the lower surface of the slat. The sound suppression part protrudes backward from the slats in order to make the vortex separation position from the rear end of the plate body non-uniform and to have a short correlation in the blade width direction where the front edge of the main wing continues. Convex parts and concave parts that are concave forward with respect to the convex parts alternate in the span direction That it is formed it may also be characterized.

  The present invention provides a slat that is disposed along the front edge of a main wing of an aircraft and is movable between a position close to the front edge of the main wing and a position spaced forward from the front edge. The aerodynamic sound suppressing member mounted on the slat is formed integrally with the lower surface plate of the slat and extends rearward, and when the slat is close to the front edge of the main wing, the slat and the main wing In order to suppress aerodynamic noise caused by the vortex generated in the airflow flowing from the front to the back in the direction of travel along the lower surface of the slat, In the wing width direction in which the edge portion is continuous, a convex portion that protrudes rearward from the slat and makes the vortex separation position different from the rear end portion of the plate body, and a concave portion that is concave forward with respect to the convex portion, Aerodynamic noise suppression characterized by being formed alternately in the span direction It can also be a wood.

According to the present invention, the aerodynamic sound suppressing portion formed at the rear end portion of the plate body reduces the strength of the vortex generated by the airflow flowing from the front to the back in the traveling direction along the lower surface of the slat. The pressure fluctuations at the bottom are also reduced, and the generation of aerodynamic noise is suppressed.
Such an aerodynamic sound suppression part can be realized by forming the aerodynamic sound suppression part on a plate constituting a part of the existing lower surface plate without providing a new addition to the slat. It does not affect strength, maintainability, reliability, etc., and is low cost.

It is sectional drawing which shows the structure of the wing | blade in this Embodiment. It is a perspective view of a slat. It is a figure which shows the some example of the uneven | corrugated | grooved part with which the slat was equipped. It is a figure which shows the generation | occurrence | production state of the vortex in the slat without an uneven | corrugated | grooved part, (a) is sectional drawing, (b) is the figure of the state which looked at the slat from the downward direction. It is a figure which shows the generation | occurrence | production state of the vortex in the slat in 1st embodiment, (a) is sectional drawing, (b) is the figure of the state which looked at the slat from the downward direction. It is a figure which shows the some example of the airflow passage part with which the slat in 2nd embodiment was equipped. It is a figure which shows the generation | occurrence | production state of the vortex in the slat of 2nd embodiment, (a) is sectional drawing, (b) is the figure of the state which looked at the slat from the downward direction. It is sectional drawing which shows the structure of the wing | blade provided with the sealing member on the lower surface board. It is sectional drawing which shows the structure of the wing | blade provided with the anti-icing mechanism of the slat.

Hereinafter, the present invention will be described in detail based on embodiments shown in the accompanying drawings.
[First embodiment]
As shown in FIG. 1, a wing 1 of an aircraft is provided with a mother wing 2 and a slat (high lift generating device) 3. In FIG. 1, the left side is the flight direction (traveling direction) of the aircraft, and the left side is the front and the right side is the back.

The slat 3 is disposed along the front edge 2 a of the main wing 2. A drive mechanism (not shown) for storing and deploying the slats 3 is provided inside the main wing 2.
In addition, the wing 1 may be composed only of the above-described main wing 2 and slat 3, or another high lift generating device such as a flap may be disposed on the rear edge of the main wing 2, and is not particularly limited. Absent.

When the aircraft equipped with the wing 1 is in a cruising state, the slat 3 is housed in the main wing 2 as shown in FIG. In the state in which the slat 3 is housed, the slat 3 is close to the front edge 2a of the main wing 2, and the main wing 2 and the slat 3 are substantially integrated to form the wing 1.
When the aircraft equipped with the wings 1 enters a landing posture, the slats 3 are deployed from the main wings 2 as shown in FIG. 1B in order to realize the aerodynamic characteristics required at the time of landing. Specifically, the slats 3 are deployed so as to increase the angle of attack at which the wing 1 causes a stall, that is, not to a large angle of attack. When the slat 3 is deployed, the slat 3 descends obliquely forward from the front edge 2 a of the main wing 2, and a space is formed between the main wing 2 and the slat 3. Note that the degree to which the slats 3 are deployed differs between takeoff and landing, and the slats 3 may be deployed larger when landing compared to takeoff.

Such a slat 3 is formed of an outer skin 4 and a COVE (concave portion) 5.
The outer skin 4 is formed with an upper surface 4b and a lower surface 4c that flow along the airflow, continuous to the front edge 4a that is the upstream end of the airflow. The upper surface 4b is a surface smoothly connected from the front edge 4a, and is formed so as to protrude and extend to the main wing 2 side from the lower surface 4c. The lower surface 4c forms a surface smoothly connected to the front edge 4a, and a lower surface plate (plate body) 7 protruding toward the downstream side is integrally formed at the downstream end portion.

  The COVE 5 is a recess formed in a region of the slat 3 that faces the main wing 2, and is a portion in which the front edge 2 a of the main wing 2 is stored when the slat 3 is stored. The surface 5 a is orthogonal to the upper surface of the main wing 2, and is opposed to the upper surface 4 b of the outer skin 4. The COVE 5 is not limited to the above-described configuration, and may be configured from a single curved surface, and is not particularly limited.

  The lower surface plate 7 is a plate-like member extending toward the main wing 2 from the ridge line portion 13 where the lower surface 4c and the COVE 5 intersect, and is formed in a fixed state integrally with the outer skin 4 continuously to the lower surface 4c. The lower surface plate 7 can be formed of, for example, an aluminum alloy, CFRP, GFRP, stainless steel, or the like.

  Now, as shown in FIG. On the rear edge side of the lower surface plate 7, an uneven portion (aerodynamic sound suppressing portion, aerodynamic sound suppressing member) 20 that is continuous in the direction in which the front edge portion 2 a of the main wing 2 continues is formed. For example, as shown in FIG. 3A, semicircular concave portions 20A and semicircular convex portions 20B are alternately and continuously formed along the direction in which the front edge portion 2a of the main wing 2 continues. Thus, the concavo-convex portion 20 is configured.

In such an uneven | corrugated | grooved part 20, there exist the following effects.
That is, as shown in FIG. 4A, in the case of the conventional slat 100 without the concavo-convex portion 20, when an air flow flows along the surface of the slat 100 when the slat is deployed, a boundary layer is formed on the lower surface. The airflow separated at the downstream end of the lower surface plate 7 generates a vortex corresponding to the thickness of the boundary layer. At this time, as shown in FIG. 4B, the generated vortex becomes a two-dimensional one having a long correlation in the entire span direction of the slat 100 (direction in which the main wing 2 is continuous). Such a long-correlation vortex is strong and induces large pressure fluctuations on the surface of the object, generating aerodynamic sound (noise).
Further, the vortex generated on the lower surface of the slat 100 enters between the slat 100 and the main wing 2 from between the rear end of the slat 100 and the main wing 2, and when the vortex collides with the COVE 5 of the slat 100. Deforms or collapses to induce pressure fluctuations, particularly on the facing surface 5b of the COVE 5, and generate aerodynamic sound.

  On the other hand, as shown in FIG. 5, when the concavo-convex portion 20 is provided, the airflow flowing along the surface of the slat 3 is separated at the downstream end of the lower surface plate 7 during the slat deployment, and a vortex corresponding to the thickness of the boundary layer is generated. Although it produces | generates, the position which peels from the lower surface board 7 according to the uneven | corrugated | grooved part 20, and produces | generates a vortex becomes uneven in the direction of an airflow. As the vortex A generated at the downstream end of the concave portion 20A and the vortex B generated at the downstream end of the convex portion 20B have different vortex generation positions, the correlation between the vortices is short and the vortices are not easily connected to each other. Become. As a result, the strength of the vortex is weak, pressure fluctuation on the object surface is reduced, and generation of aerodynamic sound is suppressed. Further, since the generation of vortices on the downstream side of the lower surface plate 7 can be suppressed in this way, the vortex can be prevented from entering between the slat 3 and the main wing 2 from between the rear end of the slat 3 and the main wing 2. Further, generation of aerodynamic sound generated when colliding with the COVE 5 of the slat 3 can be suppressed.

Thus, the uneven portion 20 that is very effective for reducing aerodynamic noise can be realized by merely forming the uneven portion 20 on the existing lower surface plate 7 without providing a new addition to the slat 3. The function, strength, maintainability, reliability, etc. of the slat 3 are not affected, and the cost is low. Further, when the slat 3 is stored, the uneven portion 20 does not collide with the main wing 2, and there is no need to change the operation structure of the slat 3.
Moreover, the slat 3 provided with such a concavo-convex portion 20 can be easily attached to the wing 1 of an existing aircraft by exchanging the slat 3, and the above effect can be obtained at low cost.

The concavo-convex portion 20 may have a shape other than that shown in FIG.
For example, as shown in FIG. 3B, by providing a plurality of triangular convex portions in succession, the concave and convex portions 20 may be configured by alternately continuing the triangular concave portions 20C and the convex portions 20D. it can.
In addition, as shown in FIG. 3C, the concave and convex portion 20 can be configured by alternately continuing rectangular concave portions 20E and convex portions 20F.
As shown in FIG.3 (d), the uneven | corrugated | grooved part 20 can also be formed by arranging the comb-tooth-like processus | protrusion (strip part) 20G extended along an airflow direction for every fixed space | interval in a wing width direction. it can.

  Furthermore, the protrusions 20B, 20D and 20F, the protrusion dimensions of the protrusions 20G, and the depth dimensions of the recesses 20A, 20C and 20E are not necessarily uniform in the blade width direction, and may be different from each other.

[Second Embodiment]
Next, a second embodiment of the present invention is shown. Here, the difference between the second embodiment described below and the first embodiment is only the bottom plate 7, and other configurations of the blade 1 are common to the first embodiment. Therefore, in the following, only the configuration of the lower surface plate 7 in the present embodiment will be described, and the description of the configuration common to the first embodiment will be omitted.

As shown in FIG. 6, at the rear end of the lower surface plate 7 extending rearward from the lower edge of the slat 3, a shear force suppressing portion (aerodynamics) that suppresses the shear force in the boundary layer of the airflow flowing along the lower surface of the lower surface plate 7. A sound suppression part, an aerodynamic sound suppression member) 30 is formed.
As shown in FIG. 6A, as the shear force suppressing portion 30, a mesh portion (airflow passage portion) 31 having a large number of holes penetrating the upper and lower sides of the lower surface plate 7 is provided at the rear end portion of the lower surface plate 7. Can be formed. The mesh portion 31 can be a mesh material formed by assembling a large number of wire rods in a net shape.
In addition, as shown in FIG. 6B, instead of the mesh portion 31, a so-called punching metal material 32 in which a large number of holes (airflow passage portions) 32 a penetrating the top and bottom of the lower surface plate 7 are arranged in the plate material 32 b. Can also be provided as the shear force suppressing portion 30.
In addition, as shown in FIG. 6C, a large number of wires (airflow passage portions) 33 extending along the airflow direction are arranged at regular intervals in the direction in which the front edge portion 2a of the main wing 2 is continuous. The shear force suppression part 30 can also be comprised by setting it as a brush shape.
As shown in FIG. 6 (d), a slit portion 34 having a large number of slits (airflow passage portions) 34 a penetrating the upper and lower sides of the lower surface plate 7 can be formed at the rear end portion of the lower surface plate 7.

  As shown in FIGS. 7A and 7B, in such a shear force suppressing portion 30, the mesh portion 31, the punching metal material 32, the wire material 33, and the slit portion 34 are moved from the lower surface to the upper surface of the lower surface plate 7. As a result, a part of the airflow passes through, so that the shearing force in the boundary layer of the airflow flowing along the lower surface of the lower surface plate 7 is reduced.

  When the slat 3 is deployed, the airflow flowing along the surface of the slat is separated at the downstream end of the lower surface plate 7 to generate a vortex corresponding to the thickness of the boundary layer. The shearing force in the boundary layer of the airflow flowing along the lower surface of can be suppressed. As a result, the strength of the generated vortex is weak, the pressure fluctuation on the object surface is reduced, and the generation of aerodynamic sound is suppressed.

  As described above, the shear force suppression unit 30 that is very effective for reducing aerodynamic noise can be obtained by forming the shear force suppression unit 30 on the existing lower surface plate 7 without providing a new addition to the slat 3. Since it can be realized, the function, strength, maintainability, reliability, etc. of the slat 3 are not affected, and the cost is low. Further, even when the slat 3 is retracted, the shearing force suppression unit 30 does not collide with the main wing 2, and there is no need to change the operation structure of the slat 3.

  In the first and second embodiments described above, the concavo-convex portion 20 and the shear force suppressing portion 30 are formed on the lower surface plate 7, but as shown in FIG. When the seal member 40 that narrows the gap between the lower surface plate 7 and the main wing 2 is provided, the uneven portion 20 and the shear force suppressing portion 30 can be formed on the seal member 40. The seal member 40 can be formed of, for example, a rubber material, CFRP, GFRP, stainless steel, aluminum alloy, or the like. The seal member 40 formed of such a material can be attached to the existing slat 3 later.

  In the above, a plurality of specific examples have been shown as the concavo-convex portion 20 and the shear force suppressing portion 30, but configurations other than those described above can be adopted as long as the same function can be exhibited.

The slat 3 can also be provided with an anti-icing mechanism for preventing the slat 3 from icing. An example of the anti-icing mechanism is shown in FIG. The anti-icing mechanism shown in FIG. 9 includes a tube 50 for supplying warm air inside the slat 3. The tube 50 feeds air heated by a heat source in the blade width direction of the slat 3 and blows out air from a plurality of blowing holes 51 provided at intervals toward the inside of the front edge of the slat 3. It is. The blown air needs to flow outside. In the anti-icing mechanism as shown in FIG. 9, the exhaust port 52 is provided in the facing surface 5 b of the COVE 5 of the slat 3, and the air is provided between the slat 3 and the main wing 2. The space between the bottom plate 7 and the main wing 2 of the slat 3 flows out to the outside.
For the slats 3 provided with this anti-icing mechanism, the concavo-convex portion 20 and the shear force suppressing portion 30 of the above-described embodiment of the present invention can also function as part of the air outflow path. Then, it is not necessary to provide a separate air discharge port.

  In addition to this, as long as it does not depart from the gist of the present invention, the configuration described in the above embodiment can be selected or changed to another configuration as appropriate.

  DESCRIPTION OF SYMBOLS 1 ... Wing | wing, 2 ... Mother wing | wing, 2a ... Front edge part, 3 ... Slat (high lift generator), 4 ... Outer skin, 4a ... Front edge, 4b ... Upper surface, 4c ... Lower surface, 5 ... COVE (recessed part), 7 ... bottom plate (plate body), 13 ... ridge line part, 20 ... uneven part (aerodynamic sound suppressing part, aerodynamic sound suppressing member), 20A, 20C, 20E ... concave part, 20B, 20D, 20F ... convex part, 20G ... protrusion ( Strip part), 30 ... shear force suppression part (aerodynamic sound suppression part, aerodynamic sound suppression member), 31 ... mesh part (airflow passage part), 32 ... punching metal material, 32a ... hole (airflow passage part), 33 ... wire (Airflow passage part), 34 ... slit part, 34a ... slit (airflow passage part), 100 ... slat

Claims (9)

A slat disposed along the front edge of the main wing and movably provided between a position close to the front edge of the main wing and a position spaced forward from the front edge;
The slat is integrally formed continuously with the lower surface plate of the slat, extends rearward, and closes between the slat and the main wing when the slat is close to the front edge of the main wing. A plate body provided in
An aerodynamic sound suppression unit that is formed at the rear end of the plate body and suppresses aerodynamic noise caused by vortices generated in the airflow flowing from the front to the back in the traveling direction along the lower surface of the slat;
The aerodynamic noise suppression unit protrudes rearward from the slat in order to make the separation position of the vortex from the rear end of the plate member non-uniform in the blade width direction in which the front edge of the main wing is continuous. The high-lift generating device is characterized in that convex portions that are concave and concave portions that are concave forward with respect to the convex portions are alternately formed in the wing span direction.   The high lift generating device according to claim 1, wherein the convex portion and the concave portion are any one of a semicircular shape, a rectangular shape, and a triangular shape.   A strip-shaped strip portion extending rearward is arranged at the rear end portion of the plate body so as to be spaced apart from each other in the blade width direction, whereby the concave portion and the convex portion are formed. The high lift generator according to claim 1. A slat disposed along the front edge of the main wing and movably provided between a position close to the front edge of the main wing and a position spaced forward from the front edge;
The slat is integrally formed continuously with the lower surface plate of the slat, extends rearward, and closes between the slat and the main wing when the slat is close to the front edge of the main wing. A plate body provided in
An aerodynamic sound suppression unit that is formed at the rear end of the plate body and suppresses aerodynamic noise caused by vortices generated in the airflow flowing from the front to the back in the traveling direction along the lower surface of the slat;
The aerodynamic sound suppression unit includes an airflow passage unit that passes through the upper and lower sides of the plate body and allows a part of the airflow flowing along the lower surface of the slat and the plate body to pass above the plate body. A high lift generator characterized by that.   5. The high lift generating device according to claim 4, wherein the airflow passage portion is a plurality of holes formed in the plate body.   5. The high lift generating device according to claim 4, wherein the air flow passage portion is a plurality of slits formed in the plate body. With mother wings,
The high lift generator according to any one of claims 1 to 6,
Wings characterized by comprising. A slat disposed along a front edge of a main wing of an aircraft and provided to be movable between a position close to the front edge of the main wing and a position spaced forward from the front edge; There,
The slat is integrally formed continuously with the lower surface plate of the slat, extends rearward, and closes between the slat and the main wing when the slat is close to the front edge of the main wing. A plate body provided in
An aerodynamic sound suppression unit that is formed at the rear end of the plate body and suppresses aerodynamic noise caused by vortices generated in the airflow flowing from the front to the back in the traveling direction along the lower surface of the slat;
The aerodynamic noise suppression unit protrudes rearward from the slat in order to make the vortex separation positions different from the rear end of the plate body in the blade width direction in which the front edge of the main wing is continuous. The slat characterized by the convex part and the recessed part which becomes concave ahead with respect to the said convex part being alternately formed in the said wing span direction. A slat disposed along a front edge of a main wing of an aircraft and provided to be movable between a position close to the front edge of the main wing and a position spaced forward from the front edge. An aerodynamic sound suppressing member to be installed,
The slat is integrally formed continuously with the lower surface plate of the slat, extends rearward, and closes between the slat and the main wing when the slat is close to the front edge of the main wing. In order to suppress aerodynamic noise caused by the vortex generated in the airflow flowing from the front to the back in the traveling direction along the lower surface of the slat, the front edge of the main wing is In the continuous blade width direction, a convex portion that protrudes rearward from the slat and makes the vortex separation position different from the rear end portion of the plate body, and a concave portion that is concave forward with respect to the convex portion. The aerodynamic sound suppressing member is formed alternately in the blade width direction.

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