JP4831337B2 - Vortex generator - Google Patents

Description

  The present invention suitably suppresses separation of the airflow flowing on the upper surface of the movable wing when the rudder angle of the movable wing such as a flap is large, and is fixed when the rudder angle of the movable wing such as a flap is small. The present invention relates to a vortex generator configured by a simple mechanism that does not resist airflow flowing over the upper surface of a wing and a movable wing.

For example, when the airflow flowing on the upper surface of the flap of the aircraft is separated from the upper surface of the flap, the flap effect is reduced, resulting in an increase in air resistance, a decrease in lift and a deterioration in the lift-drag ratio. A vortex generator is widely known as a peeling suppression device that suppresses such peeling. A vortex generator is a so-called vortex generator that is placed in an airflow to generate a vertical vortex, and provides momentum to the airflow flowing through the boundary layer of the wing to suppress separation. As a result, the separation point can be moved further downstream, but the vortex generator becomes resistant to the airflow when there is no flap steering as in cruising. In other words, the vortex generator is effective when flying at a high angle of attack such as during takeoff and landing, or when steering a flap that is a type of high lift device, but in a flight state that does not involve flow separation such as during cruise. There is a demerit that becomes resistance to the flow and increases drag that is very important in aerodynamic performance (see Non-Patent Document 1, for example).
By the way, several devices (ideas) for eliminating the disadvantage of increased resistance by a vortex generator during flight (cruising) without flow separation are known. For example, a vortex generator (long axis) that can move in the axial direction is placed perpendicular to the flow, and when separation of the flow is detected by the sensor, the vortex generator is driven by the driving means to generate air current. On the other hand, it projects vertically and generates a vertical vortex. There is known a flow separation control device in which the vertical vortex supplies momentum to an airflow flowing in the vicinity of a boundary layer of a blade so that the separation of the flow is suppressed (see, for example, Patent Document 1). With this device, when the vortex generator is not driven, the vortex generator will not protrude from the surface of the wing and will not resist the airflow flowing through the wing boundary layer, but it will detect the wing boundary layer flow. Sensors that always protrude from the outer surface of the wing and resist the airflow flowing through the boundary layer of the wing. This device also requires a mechanism and energy to drive the vortex generator, increasing the weight of the aircraft and reducing performance. Therefore, this device is a device that reduces the amount of demerit at the time of flight without flow separation, and is not a device that completely eliminates the amount of demerit.
There are also some known methods of eliminating the above disadvantages by placing a vortex generator in the main wing during cruising without flow separation. In one example, when the control surface is steered, an extension arm that extends away from the control surface with respect to the hinge line is attached to its tip by driving the engaged sliding stud. A vortex generator configured to project a vortex generator perpendicularly to an airflow is known (see, for example, Patent Document 2). However, this device is mechanically complex, and it is considered that there are greater demerits such as increased weight due to the complexity of the mechanism than the merit of aerodynamic performance improvement obtained by the vortex generator.

JP-A-5-16892 US Pat. No. 4,039,161 R.H.Barnard and D.R.Philpott, "Aircraft Flight 2nd edition pp77-78, Longman Scientific & Technica1"

As described above, when the object surface is bent sharply from the hinge line like an aircraft flap, the airflow flowing on the upper surface of the flap is separated from the upper surface of the flap in the vicinity of the hinge line. Conventional vortex generators that suppress this separation phenomenon, such as the flap of an aircraft during cruising, when the upper surface of the main wing and the upper surface of the flap connect smoothly, the protrusion of the vortex generator increases the air resistance. Will be invited. Therefore, there is a technique for avoiding an increase in resistance by placing the vortex generator inside the flap when cruising when a vortex generator is not required.
However, the technology for accommodating the vortex generator inside the flap has a problem that the mechanism is complicated, so that the weight of the control mechanism is increased and the effect of the vortex generator is counteracted.
Therefore, the problem to be solved by the present invention has been made in view of the above-mentioned problems of the prior art, and when the rudder angle of a movable blade such as a flap is large, it is preferable to separate the airflow flowing on the upper surface of the movable blade. Another object of the present invention is to provide a vortex generator configured by a simple mechanism that does not resist the airflow flowing through the upper surfaces of the fixed wing and the movable wing when the steering angle of the movable wing such as a flap is small.

The vortex generator according to claim 1, wherein the vortex generator according to claim 1 has a top portion protruding from a hinge line that steers the movable blade at a movable blade side joint portion of the movable blade that joins the fixed blade, and overlaps the fixed blade. serrations are formed by projections of the triangle, and the hinge line is disposed across said sawtooth, the protrusion of the triangle forming the movable blade-side joint part in accordance with the steering angle of the movable vanes are raised up fixed An airflow that protrudes from the outer surface of the blade and flows in the vicinity of the boundary layer of the fixed blade is configured to collide with the protrusion.
In the vortex generator, when the movable wing is steered by the action of the hinge line when the movable wing is steered, such as during takeoff and landing of an aircraft, the movable wing side joint of the movable wing is The sawtooth-shaped protrusion rises and the sawtooth-shaped protrusion protrudes from the outer surface of the fixed wing and hits the airflow flowing on the upper surface of the fixed wing. As a result, a vertical vortex equivalent to the leading edge separation vortex generated in the delta wing shape is generated. By generating and supplying momentum to the airflow that flows in the vicinity of the hinge line of the movable blade whose momentum is small, the occurrence of separation of the airflow flowing on the upper surface of the movable blade is suitably suppressed. On the other hand, when the movable wing is not steered as during cruising, the sawtooth shape of the joint portion on the movable wing side is joined to the upper surface of the fixed wing, and does not become a resistance against the airflow flowing on the upper surface of the fixed wing. In addition, this vortex generator is composed of an extremely simple mechanism in which the movable blade side joint of the movable blade facing the fixed blade is formed in a sawtooth shape, and the hinge line is arranged across the sawtooth shape. This eliminates the need for a storage mechanism for storing these in the wing when not in use, as found in conventional vortex generators, and is lighter than conventional vortex generators.
In addition, the height of the protruding part that protrudes from the outer surface of the fixed wing changes depending on the steering angle of the movable wing, so when the probability of separation is high, the effect as a vortex generator is large, conversely When the probability of occurrence of peeling is small, the effect as a vortex generator is reduced.

In the vortex generator according to claim 2, the fixed blade side joint portion joined to the movable blade and the movable blade side joint portion form a pair of stepless combined portions formed in a sawtooth shape by the triangular protrusions. And a hinge line for steering the movable wing is disposed across the joint portion, and the triangular protrusion that forms the joint portion rises in accordance with the steering angle of the movable wing and rises from the outer surface of the fixed wing. The air flow that protrudes and flows in the vicinity of the boundary layer of the fixed blade is configured to collide with the protrusion.
In the vortex generator, as described above, similarly to the vortex generator according to claim 1, the occurrence of separation of the airflow flowing on the upper surface of the movable wing is suitably suppressed during takeoff and landing where the movable wing is steered. However, during cruises where the movable wing is not steered, the movable wing side joint and the fixed wing side joint are smoothly joined without any step, and as a result, the joint is resistant to the airflow flowing over the upper surface of the fixed wing and the movable wing. Thus, an increase in air resistance is suitably suppressed.

The vortex generator of claim 3, when the apex angle of the triangle and theta, was that it is configured such that 20 ° ≦ θ ≦ 50 °.
In the vortex generator, the above configuration increases the leading edge receding angle (= (π−θ) / 2) with respect to the protrusion, and as a result, is equivalent to the leading edge separation vortex generated in the delta wing shape. Longitudinal vortices are preferably generated.

According to the vortex generator of the present invention, the movable blade side joint to be joined to the fixed blade is formed in a sawtooth shape, and the hinge line is disposed across the sawtooth shape. The serrated projection on the movable blade side joint protrudes from the outer surface of the fixed wing, and the airflow flowing on the upper surface of the fixed wing hits the projection, resulting in the generation of a vertical vortex that is the hinge of the movable wing. Momentum is given to the airflow flowing in the vicinity of the line, and the occurrence of airflow separation at the hinge line of the movable blade is suitably suppressed. On the other hand, when the movable wing is not steered, the movable wing side joint is joined to the upper surface of the fixed wing, and the saw-tooth-shaped protrusion falls down and does not protrude from the outer surface of the fixed wing. No resistance to airflow. As a result, an increase in air resistance during non-steering of the movable blade is suitably suppressed.
In particular, the fixed wing side joint portion of the fixed wing to be joined to the movable wing and the movable wing side joint portion form a pair of stepless joints formed in a sawtooth shape, and the hinge line is arranged across the joint portion. When the movable wing is not steered, the joint between the fixed wing and the movable wing smoothly joins without any step, and the resistance to the air current flowing near the boundary layer between the fixed wing and the movable wing does not become a resistance. As a result, an increase in air resistance during non-steering of the movable blade is more preferably suppressed.
The vortex generator according to the present invention has a very simple mechanism in which the movable blade side joint to be joined to the fixed blade is formed in a sawtooth shape and the hinge line is disposed so as to cross the sawtooth shape. This eliminates the need for a storage mechanism for storing these in the wing when not in use, as found in conventional vortex generators, and is lighter than conventional vortex generators.
In addition, the height of the protruding part that protrudes from the outer surface of the fixed wing changes depending on the steering angle of the movable wing, so when the probability of separation is high, the effect as a vortex generator is large, conversely When the probability of occurrence of peeling is small, the effect as a vortex generator is reduced.

  Hereinafter, the present invention will be described in more detail with reference to embodiments shown in the drawings.

  FIG. 1 is an explanatory diagram illustrating an example in which the vortex generator 100 according to the first embodiment is applied to the trailing edge flap 20. 1A is a perspective view of an actual machine to which the vortex generator 100 is applied, and FIG. 1B shows the vortex generator 100 during cruising in which the trailing edge flap 20 is not steered. c) shows the vortex generator 100 during take-off and landing where the trailing edge flap 20 is steered.

  As will be described later, in the vortex generator 100, when the trailing edge flap 20 is not steered, the joint between the main wing 10 as a fixed wing and the trailing edge flap 20 as a movable wing has no pair of steps. And a hinge line 40 that further bends the trailing edge flap 20 downward is disposed across the valley of the saw blade as viewed from the trailing edge flap 20 side. Is bent around the hinge line 40, the sawtooth protrusion on the trailing edge flap side is configured to protrude from the outer surface of the main wing.

  As shown in FIG. 1B, during cruising when the trailing edge flap 20 is not steered, the main blade 10 and the sawtooth joint 30 of the trailing edge flap 20 are smoothly joined without any step. As a result, the air flow F flowing in the vicinity of the boundary layer between the main wing 10 and the trailing edge flap 20 flows while adhering to the surface, so that the air resistance in the vortex generator 100 does not increase.

  On the other hand, as shown in FIG. 1C, when the trailing edge flap 20 is steered, for example, during takeoff and landing, the trailing edge flap 20 is bent downward with the hinge line 40 as the rotation center. The trailing edge flap side saw-tooth part 32 as a joint part rises and protrudes from the outer surface of the main wing 10. As a result, the airflow F flowing in the vicinity of the boundary layer of the main wing 10 collides with the protrusions, and a leading edge separation vortex is generated. This leading edge separation vortex imparts momentum to the airflow F flowing near the hinge line 40 of the trailing edge flap 20, and as a result, the occurrence of separation of the airflow F flowing near the boundary layer of the trailing edge flap 20 is suitably suppressed. Become. Therefore, the function of the trailing edge flap 20 is not impaired.

  FIG. 2 is a three-sided view showing the sawtooth joint 30 between the main wing 10 and the trailing edge flap 20. 2A shows a top view, FIG. 2B shows a front view, and FIG. 2C shows a side view.

  As shown in FIG. 2A, a so-called jagged sawtooth joint 30 between the main wing 10 and the trailing edge flap 20 is composed of a main wing side sawtooth 31 as a fixed wing side joint and a rear as a movable wing side joint. This is a pair of stepless joints with the edge flap side sawtooth portion 32. The hinge line 40 is disposed along the valley portion 32a of the trailing edge flap side sawtooth portion.

  In general, the hinge line 40 is preferably disposed between the valley portion 31a of the main wing side sawtooth portion and the valley portion 32a of the trailing edge flap side sawtooth portion, but from the valley portion 32a of the trailing edge flap side sawtooth portion. It may be arranged on the downstream side. Further, it is desirable that the leading edge receding angle Λ of the trailing edge flap side saw-tooth portion 32 is 65 ° to 80 °.

  As shown in FIG. 2B, when the trailing edge flap 20 is steered, the trailing edge flap side sawtooth portion 32 rises and protrudes from the outer surface 10s of the main wing, and flows in the vicinity of the boundary layer of the main wing. The air current hits the trailing edge flap side saw-tooth portion 32 to generate a leading edge separation vortex. Thereby, momentum is supplied to the airflow flowing in the vicinity of the hinge line 40 of the trailing edge flap 20, and separation of the airflow flowing on the upper surface of the trailing edge flap 20 is suitably suppressed.

  Further, as shown in FIG. 2C, the height at which the trailing edge flap side saw-tooth portion 32 protrudes from the outer surface 10s of the main wing changes according to the steering angle of the trailing edge flap 20. When the trailing edge flap 20 is not steered, the main wing 10 and the trailing edge flap 20 are joined without a step, and the trailing edge flap side sawtooth portion 32 does not protrude from the outer surface 10 s of the main wing, and the boundary layer between the main wing 10 and the trailing edge flap 20. It becomes no resistance to the air current flowing in the vicinity.

FIG. 3 is an explanatory view showing an application shape example of the leading edge flap 50 or the trailing edge flap 20.
In FIG. 3A, the thickness of the trailing edge flap side saw-tooth portion 32 is constant with respect to the longitudinal direction, while FIG. 3B shows the thickness of the trailing edge flap side saw-tooth portion 32 with respect to the longitudinal direction. The so-called wedge shape expands. FIG. 6C shows a shape example in which the vortex generator 100 is applied to the leading edge flap 50.

  According to the vortex generator 100, since the joint between the main wing 10 and the trailing edge flap 20 forms a so-called serrated joint 30, the trailing edge flap 20 is steered as during takeoff and landing. When viewed from the main wing 10, a jagged sawtooth protrudes from the outer surface 10 s of the main wing, and utilizes the characteristics of the wing having a large receding angle, and this suitably functions as a vortex generator. On the other hand, when the trailing edge flap 20 is not steered as during cruising, the serrated joint 30 between the main wing 10 and the trailing edge flap 20 is smoothly joined without a step, and thus does not function as a vortex generator. It becomes no resistance to the airflow flowing through the boundary layer between the main wing 10 and the trailing edge flap 20. As a result, if the steering angle of the flap is large, such as during take-off and landing, the occurrence of separation of the airflow flowing over the upper surface of the flap is suitably suppressed, and if the steering angle of the flap is small, such as during cruising, the air resistance of the upper surface of the flap Is suitably suppressed. In addition, the vortex generator 100 is configured by a very simple mechanism in which the joint between the main wing 10 and the trailing edge flap 20 is formed by a pair of serrated joints 30 having a stepped shape. This eliminates the need for a storage mechanism for storage inside, and is extremely light compared to conventional vortex generators.

FIG. 4 is an explanatory diagram illustrating a vortex generator 200 according to the second embodiment. In addition, (a) of FIG. 4 is a perspective view, (b) is an A arrow view.
The vortex generator 200 is configured by arranging the VG piece 60 on the upper surface of the trailing edge flap 21 so that the top of the VG piece 60 formed in a triangular shape protrudes from the hinge line 40 and overlaps the main wing 11. Has been.

  In the vortex generator 100 according to the first embodiment, the joint between the main wing 10 and the trailing edge flap 20 forms a pair of stepless sawtooth joints 30 composed of the main wing side sawtooth part 31 and the trailing edge flap side sawtooth part 32. However, in this vortex generator 200, a so-called jagged sawtooth shape is formed by the VG piece 60 at the joint between the trailing edge flap 21 and the main wing 11. Therefore, similarly to the vortex generator 100, when the trailing edge flap 21 is steered and the trailing edge flap 21 is bent downward with the hinge line 40 as the rotation center, the VG piece 60 rises, and the protrusion of the VG piece 60 is the main wing. 11 protrudes with respect to the outer surface. As a result, the airflow F flowing in the vicinity of the boundary layer of the main wing 11 collides with the protrusions, and a leading edge separation vortex is generated. This leading edge separation vortex imparts momentum to the airflow F flowing in the vicinity of the hinge line 40 of the trailing edge flap 21, and as a result, the occurrence of separation of the airflow F flowing in the vicinity of the boundary layer of the trailing edge flap 21 is suitably suppressed. Become. On the other hand, at the time of cruise when the trailing edge flap 21 is not steered, the VG piece 60 is joined to the upper surface of the main wing 11, so that the airflow F flowing in the vicinity of the boundary layer between the main wing 11 and the trailing edge flap 21 adheres to the surface. As a result, the air resistance in the vortex generator 200 does not increase.

  FIG. 4B shows a state in which the trailing edge flap 21 at the time of takeoff and landing is bent downward. The top (projection) of the VG piece 60 hits the airflow flowing on the upper surface of the main wing 11 to generate a leading edge separation vortex, and the momentum is supplied to the airflow flowing on the upper surface of the trailing edge flap 21 by the vortex. Thus, the separation of the airflow flowing through the upper surface of 21 is suitably suppressed.

  In the steering surface (aileron, rudder, elevator) that controls the attitude of the aircraft, the separation of the flow on the suction surface side is suppressed as in the case of application to the trailing edge flap, and the performance of the steering surface is improved and the resistance is reduced. Improve the performance of all aircraft. When not steering, the resistance is not increased.

  Make the leading edge of the steering surface of the ship jagged. When the steering surface is steered greatly because the ship turns significantly, the separation of the flow on the suction side of the steering surface is suppressed, the steering performance is improved, and the resistance of the ship is also reduced.

  The vortex generator of the present invention can be applied not only as a method for suppressing separation at the leading and trailing edge flaps of an aircraft wing, but also as a method for suppressing separation in a flow having a hinge line and causing separation. is there. For example, suitable for preventing ship steering surface, automotive rear separation suppression, aerodynamic steering surface in rockets and spacecrafts, suppression of separation at non-operating points in internal flow of engines and pumps, or preventing increase in resistance at operating points Is possible.

It is explanatory drawing which shows an example which applied the vortex generator which concerns on Example 1 to the trailing edge flap. It is a three-plane figure which shows the sawtooth junction part of a main wing and a trailing edge flap. It is explanatory drawing which shows the example of an application shape of a front edge flap or a rear edge flap. It is explanatory drawing which shows an example which applied the vortex generator which concerns on Example 2 to the trailing edge flap.

Explanation of symbols

10 fixed wing 20 trailing edge flap 30 sawtooth joint 40 hinge line 50 leading edge flap 60 VG piece 100,200 vortex generator

Claims (3)

The movable blade-side joint portion of the movable blade to be bonded to the fixed blades, serrations are formed by projections of the triangular top portion overlaps the fixed blade projects from the hinge line to steer the movable blades and the hinge line the sawtooth The triangular protrusion that forms the movable blade side joint portion rises according to the steering angle of the movable blade, protrudes from the outer surface of the fixed blade, and flows in the vicinity of the boundary layer of the fixed blade Is configured to collide with the protrusion. A fixed wing side joint joined to the movable wing, and the movable wing side joint constitute a pair of stepless joints formed in a sawtooth shape by the triangular projections , and a hinge line for steering the movable wing Is disposed across the joint portion, and the triangular projection portion that forms the joint portion rises according to the steering angle of the movable blade, protrudes from the outer surface of the fixed blade, and near the boundary layer of the fixed blade. The vortex generator according to claim 1, wherein the flowing airflow is configured to collide with the protrusion. When the apex angle of the triangle and θ, 20 ° ≦ θ ≦ 50 ° and so as vortex generator according to claim 1 or 2 is constructed.

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