CN106564585B - High-performance deep stall wing structure and aircraft - Google Patents

Abstract

The invention provides a high-performance deep-stall wing structure and an aircraft, which belong to the technical field of aviation equipment. The high-performance deep-stall wing structure includes: a wing body and a plasma exciter, the plasma exciter is attached to the rear edge of the wing body, and the shape of the front edge of the wing body is a preset waveform. The high-performance deep-stall wing structure and the aircraft provided by the invention improve the aerodynamic performance of the aircraft in the range of the full angle of attack.

Description

High performance deep stall wing structure and aircraft

technical field

The invention relates to the technical field of aviation equipment, in particular to a high-performance deep-stall wing structure and an aircraft.

Background technique

In the field of aviation, improving the aerodynamic performance of aircraft has always been the focus of attention. Among them, the separation and stall of the wing body at high angles of attack will affect the aerodynamic performance of the aircraft, thereby endangering the safety of passengers.

In the prior art, in order to solve the problem of separation and stall of the wing body at a large angle of attack, a conceptual design scheme is to transform the smooth leading edge of the original wing body into a bumpy leading edge, so that when the airflow flows through the wing At the leading edge of the wing body, a vortex will be rolled up from the concave to the convex. The vortex is elongated by the airflow in the flow direction and extends downstream. At the same time, it rotates with the flow direction as the axis, gradually forming a turbulent flow with a higher degree of flow mixing. , so that the high-speed flow away from the surface of the wing body is involved in the low-speed flow close to the surface of the wing body, so that the kinetic energy of the airflow near the surface of the wing body increases, thereby improving the ability of the boundary layer to resist flow separation, so as to eliminate the Phenomena of body separation and stall.

However, in the prior art, although the uneven leading edge of the wing body eliminates the phenomenon of separation and stall of the wing body at a large angle of attack and improves the aerodynamic performance of the aircraft at a large angle of attack, this method will make the aircraft The maximum lift force of the wing body and the lift force decrease at medium and small angles of attack, resulting in poor aerodynamic performance of the aircraft at medium and small angles of attack.

Contents of the invention

The invention provides a high-performance deep-stall wing structure and an aircraft to improve the aerodynamic performance of the aircraft in the range of the full angle of attack.

Embodiments of the present invention provide a high-performance deep-stall wing structure, including:

A wing body and a plasma exciter, the plasma exciter is attached to the rear edge of the wing body, and the shape of the front edge of the wing body is a preset waveform.

In an embodiment of the present invention, the shape of the pre-wave is a triangular waveform, a sine waveform or a cosine waveform.

In an embodiment of the present invention, the plasma actuator includes a covering electrode, an insulating medium and an exposed electrode.

In an embodiment of the present invention, the covered electrode and the exposed electrode are asymmetrically attached to both sides of the insulating medium, the covered electrode is attached to the rear edge of the wing body, and the covered electrode The first end of the exposed electrode is flush with the lower surface at the trailing edge of the wing body, and the first end of the exposed electrode is flush with the upper surface at the trailing edge of the wing body.

In an embodiment of the present invention, the distance between the straight line where the second end of the covered electrode is located and the straight line where the second end of the exposed electrode is located is M millimeters, where M is greater than or equal to 0 and less than or equal to 1.5.

In an embodiment of the present invention, the length of the covered electrode is equal to the length of the exposed electrode, and is less than or equal to the length of the wing body in the span direction, and the length of the insulating medium is greater than the length of the covered electrode The width of the covered electrode and the exposed electrode is less than or equal to N microns, the width of the insulating medium is less than or equal to S microns, and the height of the covered electrode and the exposed electrode is the average aerodynamic chord of the wing body T times longer, the height of the insulating medium is greater than or equal to the sum of the height of the covered electrode, the height of the exposed electrode, and the distance between the second end of the covered electrode and the second end of the exposed electrode; wherein, N is greater than or equal to 0 and less than or equal to 15, S is greater than or equal to 0 and less than or equal to 250, T is greater than or equal to 0.3% and less than or equal to 1%, and the height of the plane at the rear edge of the wing body is greater than or equal to the height of the insulating medium.

In an embodiment of the present invention, the amplitude of the preset shape is P times the average aerodynamic chord length of the wing body, and the wavelength of the preset shape is Q times the average aerodynamic chord length of the wing body, Wherein, said P is greater than or equal to 0.03 and less than or equal to 0.11, and Q is greater than or equal to 0.11 and less than or equal to 0.43.

In an embodiment of the present invention, both the covered electrode and the exposed electrode are made of metal.

The embodiment of the present invention also provides an aircraft, including:

Airframe and the high-performance deep-stall wing structure described in any one of the above-mentioned embodiments.

The high-performance deep-stall wing structure and the aircraft provided by the embodiments of the present invention, the high-performance deep-stall wing structure comprises: a wing body and a plasma exciter, the plasma exciter is attached to the trailing edge of the wing body, and the wing The shape of the leading edge of the body is a preset waveform. It can be seen that, in the embodiment of the present invention, by attaching the plasma exciter to the trailing edge of the wing body, under the drive of the high-voltage and high-frequency AC power supply, the surface of the plasma exciter will periodically generate The direction of the covered electrode, and the wall jet from the direction of the covered electrode to the exposed electrode scour the recirculation area downward, which can increase the lift of the wing body, thereby improving the aerodynamic performance of the aircraft at medium and small angles of attack. In addition, by moving the wing body forward The shape of the edge is a preset waveform, which can increase the kinetic energy of the airflow close to the surface of the wing body, thereby improving the ability of the boundary layer to resist flow separation, and then improving the aerodynamic performance of the aircraft at a large angle of attack, that is, through the implementation of the present invention The high-performance deep-stall wing structure provided by the example improves the aerodynamic performance of the aircraft in the range of the full angle of attack.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description These are some embodiments of the present invention. For those skilled in the art, other drawings can also be obtained according to these drawings without any creative effort.

Fig. 1 is the structural representation of a kind of high-performance deep-stall airfoil structure provided by the embodiment of the present invention;

Fig. 2 is a top view of the leading edge of a wing body provided by an embodiment of the present invention;

Fig. 3 is the structural representation of another kind of high-performance deep-stall airfoil structure provided by the embodiment of the present invention;

Fig. 4 is a schematic structural diagram of a plasma actuator provided by an embodiment of the present invention;

Fig. 5 is a schematic diagram of the electron flow of a high-voltage high-frequency sinusoidal AC signal in the negative half cycle provided by the embodiment of the present invention;

Fig. 6 is a schematic diagram of electron flow in a positive half cycle of a high-voltage high-frequency sinusoidal AC signal provided by an embodiment of the present invention;

Fig. 7 is a relationship diagram between an angle of attack and a lift coefficient provided by an embodiment of the present invention;

Fig. 8 is a schematic structural diagram of an aircraft provided by an embodiment of the present invention.

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

The terms "first", "second", "third", "fourth", etc. (if any) in the description and claims of the present invention and the above drawings are used to distinguish similar objects, and not necessarily Used to describe a specific sequence or sequence. It is to be understood that the data so used are interchangeable under appropriate circumstances such that the embodiments of the invention described herein, for example, can be practiced in sequences other than those illustrated or described herein. Furthermore, the terms "comprising" and "having", as well as any variations thereof, are intended to cover a non-exclusive inclusion, for example, a process, method, system, product or device comprising a sequence of steps or elements is not necessarily limited to the expressly listed instead, may include other steps or elements not explicitly listed or inherent to the process, method, product or apparatus.

It should be noted that the following specific embodiments may be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.

Fig. 1 is a schematic structural view of a high-performance deep-stall wing structure 10 provided by the embodiment of the present invention, please refer to Fig. 1. Of course, the embodiment of the present invention is only illustrated by taking Fig. 1 as an example, but it does not represent the present invention. The invention is limited only to this. The high performance deep stall airfoil structure 10 includes:

The wing body 101 and the plasma actuator 103 , the plasma actuator 103 is attached to the rear edge of the wing body 101 , and the shape of the front edge of the wing body 101 is a preset waveform 102 .

Among them, the large angle of attack usually refers to the angle of attack greater than or equal to 12 degrees, and the small and medium angle of attack refers to the angle of attack less than 12 degrees. Of course, it can be divided according to actual needs. The present invention only uses 12 degrees as an example for illustration , but it does not mean that the present invention is limited thereto.

For example, the shape of the leading edge of the wing body 101 is a preset waveform 102, the preset waveform 102 means that its shape has a wavelength and an amplitude, please refer to FIG. 2, which is a kind of The top view of the leading edge of the wing body 101 , of course, the embodiment of the present invention is only illustrated by taking FIG. 2 as an example, but it does not mean that the embodiment of the present invention is limited thereto.

In the embodiment of the present invention, by attaching the plasma actuator 103 at the trailing edge of the wing body 101, when the plasma actuator 103 is turned on, driven by a high-voltage high-frequency AC power supply, the surface of the plasma actuator 103 Periodically, wall jets from the exposed electrode 1033 to the covered electrode 1031, and from the covered electrode 1031 to the exposed electrode 1033, flush the reflow area downward, thereby generating a kind of downstream suction on the upper surface of the wing body 101 effect, this pumping effect further improves its ability to resist flow separation. More importantly, this suction effect increases the flow velocity of the airflow on the upper surface of the wing body 101 toward the downstream direction, thereby increasing the circulation of the wing body 101 , thereby increasing the lift force. Simultaneously, the speed of the free flow hitting the wall jet on the lower surface of the wing body 101 slows down. Therefore, a small low-speed and high-pressure recirculation zone is formed on the lower surface of the wing body 101, which increases the pressure on the lower surface and can also improve The lift of the wing body 101 improves the aerodynamic performance of the aircraft at medium and small angles of attack.

Further, in the embodiment of the present invention, by setting the shape of the leading edge of the wing body 101 into a preset waveform 102, when the airflow flows through the leading edge of the wing body 101, a vortex will be rolled up from the concave to the convex, the The vortex is elongated by the airflow in the flow direction and extends downstream. At the same time, the vortex rotates with the flow direction as the axis, and gradually forms a turbulent flow with a higher degree of flow disorder in the downstream development. The entrainment ability of the vortex and the mixing ability of the turbulence can involve the high-speed flow away from the surface of the wing body 101 into the low-speed flow close to the surface of the wing body 101, so that the kinetic energy of the airflow near the surface of the wing body 101 increases, thereby improving The ability of the boundary layer to resist flow separation is improved, thereby improving the aerodynamic performance of the aircraft at high angles of attack.

The high-performance deep-stall wing structure 10 provided by the embodiment of the present invention, the high-performance deep-stall wing structure 10 includes: a wing body 101 and a plasma actuator 103, and the plasma actuator 103 is attached to the trailing edge of the wing body 101 , the shape of the leading edge of the wing body 101 is a preset waveform 102 . It can be seen that, in the embodiment of the present invention, by attaching the plasma exciter 103 at the trailing edge of the wing body 101, under the drive of the high-voltage and high-frequency AC power, the surface of the plasma exciter 103 will periodically generate The direction from the exposed electrode 1033 to the covered electrode 1031, and the wall jet flow from the covered electrode 1031 to the exposed electrode 1033 direction scour the reflow area downward, which can enhance the lift of the wing body 101, thereby improving the aerodynamic performance of the aircraft at small and medium angles of attack. In addition, by changing the shape of the leading edge of the wing body 101 to the preset waveform 102, the kinetic energy of the airflow close to the surface of the wing body 101 can be increased, thereby improving the ability of the boundary layer to resist flow separation, thereby improving the aircraft's ability to withstand large attacks. The aerodynamic performance under the angle, that is, the high-performance deep-stall wing structure 10 provided by the embodiment of the present invention improves the aerodynamic performance of the aircraft in the range of the full angle of attack.

Based on the embodiment corresponding to Fig. 1, on the basis of the embodiment corresponding to Fig. 1, further, the embodiment of the present invention also provides another high-performance deep stall wing structure 10, please refer to Fig. 3, Fig. 3 A schematic structural diagram of another high-performance deep-stall wing structure 10 is provided for the embodiment of the present invention. Of course, the embodiment of the present invention is only illustrated by taking FIG. 2 as an example, but it does not mean that the present invention is limited thereto. The high performance deep stall airfoil structure 10 also includes:

Optionally, the plasma actuator 103 includes a covering electrode 1031 , an insulating medium 1032 and an exposed electrode 1033 .

For an example, please refer to FIG. 4, which is a schematic structural diagram of a plasma actuator 103 provided by an embodiment of the present invention. Of course, the present invention is only illustrated by using FIG. limited to this. The covered electrode 1031 and the exposed electrode 1033 are asymmetrically attached to both sides of the insulating medium 1032, the covered electrode 1031 is attached to the edge of the rear edge of the wing body 101, and the first end of the covered electrode 1031 is connected to the bottom of the rear edge of the wing body 101. The surface is flush, and the first end of the exposed electrode 1033 is flush with the upper surface at the rear edge of the wing body 101 .

Wherein, the insulating medium 1032 between the exposed electrode 1033 and the covered electrode 1031 of the plasma actuator 103 plays a role of blocking high voltage and high frequency discharge. The exposed electrode 1033 and the covered electrode 1031 are respectively connected to two output terminals of the high-voltage high-frequency power supply, and the covered electrode 1031 is used as a reference potential.

Optionally, the distance between the straight line where the second end of the covered electrode 1031 is located and the straight line where the second end of the exposed electrode 1033 is located is M millimeters, where M is greater than or equal to 0 and less than or equal to 1.5.

Wherein, the distance between the straight line where the second end of the covered electrode 1031 is located and the straight line where the second end of the exposed electrode 1033 is located refers to the vertical distance between the straight line where the second end of the covered electrode 1031 is located and the straight line where the second end of the exposed electrode 1033 is located. Preferably, in the embodiment of the present invention, the distance M between the straight line where the second end of the covered electrode 1031 is located and the straight line where the second end of the exposed electrode 1033 is located is 0, that is, one end of the covered electrode 1031 coincides with one end of the exposed electrode 1033, To improve the discharge performance of the plasma actuator 103 .

Further, for the plasma actuator 103, the length of the covered electrode 1031 is equal to the length of the exposed electrode 1033, and is less than or equal to the length of the wing body 101 in the span direction, and the length of the insulating medium 1032 is greater than the length of the covered electrode 1031 , so as to completely cover the covering electrode 1031; the width of the covering electrode 1031 and the exposed electrode 1033 is less than or equal to N microns, the width of the insulating medium 1032 is less than or equal to S microns, and the height of the covering electrode 1031 and the exposed electrode 1033 is the average aerodynamic force of the wing body 101 T times the chord length, the height of the insulating medium 1032 is greater than or equal to the sum of the height of the covered electrode 1031, the height of the exposed electrode 1033 and the distance between the second end of the covered electrode 1031 and the second end of the exposed electrode 1033; wherein, N is greater than or equal to 0 and less than or equal to 15, S is greater than or equal to 0 and less than or equal to 250, T is greater than or equal to 0.3% and less than or equal to 1%, and the height of the plane at the rear edge of the wing body 101 is greater than or equal to the height of the exposed electrode 1033, the covered electrode 1031 and the inter-electrode gap Sum.

As an example, in the embodiment of the present invention, in order to facilitate the installation and use of the plasma actuator 103 , it is usually necessary to cut the tip of the trailing edge of the wing body 101 . That is, the circular or sharp rear edge is corrected into a plane, and the height of the corrected plane is not less than the sum of the exposed electrode 1033, the covered electrode 1031 and the height of the inter-electrode gap of the plasma actuator 103, so that the plasma actuator 103 can Preferably attached to the trailing edge of the wing body 101 .

In addition, usually, the height of the insulating medium 1032 is greater than or equal to the sum of the height of the covered electrode 1031, the height of the exposed electrode 1033, and the distance between the second end of the covered electrode 1031 and the second end of the exposed electrode 1033, and the insulating medium 1032 is at least The outer end of the covering electrode 1031 is extended by 1 mm to 2 mm to avoid discharge between the exposed electrode 1033 and the covering electrode 1031 through the end surface of the insulating medium 1032 , thereby improving the high voltage resistance of the plasma actuator 103 .

Further, by setting the thickness of the exposed electrode 1033 and the covered electrode 1031 to no more than 15 microns, and the thickness of the insulating medium 1032 to no more than 250 microns, the plasma actuator 103 can be directly attached to the rear edge of the wing body 101 Since the thickness of the plasma actuator 103 is very small relative to the thickness of the local flow boundary layer, the disturbance from the incoming flow to the plasma actuator 103 can be neglected. In the embodiment of the present invention, by directly attaching the plasma to the trailing edge of the wing body 101 instead of being integrally processed and formed with the wing body 101 , the implementation method is simple and convenient, and has high feasibility. In addition, since the effect of the plasma actuator 103 can be achieved by adjusting the power signal, the pilot can adjust the control effect according to the actual flight requirements, so as to achieve the best flight state of the aircraft.

In the actual application process, the waveform of the high-voltage high-frequency voltage is a sinusoidal waveform signal as an example for illustration. For the power signal, the peak voltage is required to be 2kV-24kV, and the frequency is 1kHz-15kHz. Among them, the control effect of the plasma actuator 103 on the flow increases with the increase of voltage and frequency. At the same time, in order to consider the requirements of airborne equipment, the equipment should not work under excessive energy consumption, so the voltage and frequency of the power signal Can not be too high. For an example, please refer to FIG. 5 , which is a schematic diagram of electron flow in a negative half cycle of a high-voltage and high-frequency sinusoidal AC signal provided by an embodiment of the present invention. When the high-voltage and high-frequency sinusoidal AC signal is in the negative half cycle, that is, when the exposed electrode 1033 is at a low potential relative to the covered electrode 1031, the high-voltage and high-frequency action causes the air near the exposed electrode 1033 to ionize to form electrons, and under the action of the electric field force, the electrons Movement on the surface of the insulating medium 1032 forms an electron flow from the exposed electrode 1033 to the covered electrode 1031 , and the discharge direction points from the exposed electrode 1033 to the covered electrode 1031 . Due to the blocking effect of the insulating medium 1032, a small number of electrons can pass through the surface layer of the insulating medium 1032, but most of the electrons cannot pass through the insulating medium 1032 to reach the covering electrode 1031, so most of the electrons gather and stay in the insulating medium 1032 outside the covering electrode 1031 surface. The discharge process continues, and the electrons generated by the high-voltage and high-frequency discharge continuously move from the exposed electrode 1033 to the insulating medium 1032 covering the surface of the electrode 1031 until the potential of the exposed electrode 1033 is higher than that of the covered electrode 1031. At the same time as the electrons are moving, due to the effect of air viscosity, the surrounding air is driven to move together, thus generating a wall jet on the surface of the insulating medium 1032 from the exposed electrode 1033 to the covered electrode 1031 .

Similarly, please refer to FIG. 6 , which is a schematic diagram of electron flow in the positive half cycle of a high-voltage and high-frequency sinusoidal AC signal provided by an embodiment of the present invention. When the high-voltage high-frequency AC signal is in the positive half cycle and the covered electrode 1031 is at a lower potential than the exposed electrode 1033 , the high-voltage high-frequency action causes the air near the covered electrode 1031 to ionize to form electrons. Due to the blocking effect of the insulating medium 1032, the electrons generated by the covering electrode 1031 itself cannot pass through the insulating medium 1032 to reach the exposed electrode 1033, but the electrons gathered near the insulating medium 1032 outside the covering electrode 1031 can be driven by the electric field force Moving to the exposed electrode 1033, an electron flow from the covered electrode 1031 to the exposed electrode 1033 is formed, and the discharge direction is from the covered electrode 1031 to the exposed electrode 1033 direction. The discharge process continues, and the electrons accumulated on the surface of the covered electrode 1031 flow continuously from the direction of the covered electrode 1031 to the direction of the exposed electrode 1033 until the potential of the covered electrode 1031 is higher than that of the exposed electrode 1033 . While the electrons are moving, due to the effect of air viscosity, the surrounding air is driven to move together, thus generating a wall jet on the surface of the insulating medium 1032 from the covered electrode 1031 to the exposed electrode 1033 .

After the above-mentioned positive half cycle and negative half cycle form the wall jet, the high-speed wall jet scours the recirculation area downwards, so that the original low-velocity and high-pressure tail recirculation area becomes a high-speed and low-pressure area, thereby creating an airfoil on the upper surface of the wing body 101 An effect of downstream suction that further increases its resistance to flow separation. More importantly, this suction effect increases the flow velocity of the airflow on the upper surface of the wing body 101 toward the downstream direction, thereby increasing the circulation of the wing body 101 , thereby increasing the lift force. Simultaneously, the speed of the free flow hitting the wall jet on the lower surface of the wing body 101 slows down. Therefore, a small low-speed and high-pressure recirculation zone is formed on the lower surface of the wing body 101, which increases the pressure on the lower surface and can also improve The lift of the wing body 101 improves the aerodynamic performance of the aircraft at medium and small angles of attack.

Optionally, both the covering electrode 1031 and the exposed electrode 1033 are made of metal.

Exemplarily, in the embodiment of the present invention, both the exposed electrode 1033 and the covered electrode 1031 are made of conductive metal material, such as copper foil. In addition, the insulating medium 1032 is made of epoxy resin, quartz glass, ceramics, polyimide film, polyester film and other insulating materials with high impedance and good insulating properties. In particular, the insulating medium 1032 of the plasma actuator 103 can be made of a flexible polyester film to form a flexible plasma actuator 103, so that it can be attached to a curved surface.

Optionally, the shape of the pre-wave is a triangle waveform, a sine waveform or a cosine waveform. Further, the amplitude of the preset shape is P times the average aerodynamic chord length of the wing body 101, and the wavelength of the preset shape is Q times the average aerodynamic chord length of the wing body 101, wherein P is greater than or equal to 0.03 and less than or equal to 0.11, Q is greater than or equal to 0.11 and less than or equal to 0.43.

Here, the amplitude represents the distance between the peaks and the troughs of the sine wave defining the shape of the leading edge, and the wavelength represents the distance between the peaks and the peaks (or the distance between the troughs) of the sine wave defining the shape of the leading edge. If the wave amplitude is too large, it will lead to significant lift loss and drag increase; if the wave amplitude is too small, it will weaken the ability to weaken separation and eliminate stall at large angles of attack. If the wavelength is too large, it will compromise its ability to reduce separation and eliminate stall at high angles of attack.

In the embodiment of the present invention, the shape of the leading edge of the wing body 101 is set as a triangular waveform, a sine waveform or a cosine waveform. When the airflow passes through the leading edge of the wing body 101, a vortex will be rolled up from the concave to the convex, and the vortex is elongated by the airflow in the flow direction and extends downstream, while the vortex rotates with the flow direction as the axis, and As it develops downstream, turbulence with a higher degree of flow disorder gradually forms. The entrainment ability of the vortex and the mixing ability of the turbulence can involve the high-speed flow away from the surface of the wing body 101 into the low-speed flow close to the surface of the wing body 101, so that the kinetic energy of the airflow near the surface of the wing body 101 increases, thereby improving The ability of the boundary layer to resist flow separation is improved, thereby improving the aerodynamic performance of the aircraft at high angles of attack.

During application, the use of the plasma actuator 103 can increase the lift coefficient of the wing body 101 , thereby increasing the lift force of the wing body 101 . Please refer to FIG. 7 . FIG. 7 is a relationship diagram between an angle of attack and a lift coefficient provided by an embodiment of the present invention. Wherein, the abscissa represents the angle of attack α, and the ordinate represents the lift coefficient C _L . As an example, the frequency of the plasma actuator 103 is 3 kHz, and the peak-to-peak voltage is 4 kV. It can be seen from Fig. 7 that, compared with the case where the plasma actuator 103 is turned off (black solid line), after the plasma actuator 103 is turned on (white hollow line), at medium and low angles of attack, the lift coefficient curve shifts upwards, The overall lift of the wing body 101 has been improved. At high angles of attack, although the lift-increasing capability at medium and low angles of attack is significantly weakened, the plasma actuator 103 can further improve the lift-increasing capability at large angles of attack. Therefore, in the embodiment of the present invention, by making the shape of the leading edge of the wing body 101 into a preset waveform 102, and attaching the plasma actuator 103 at the trailing edge of the wing body 101, the overall performance of the wing body 101 can be improved. The lift coefficient in the range of the angle of attack improves the aerodynamic performance of the aircraft in the range of the full angle of attack.

Fig. 8 is a schematic structural diagram of an aircraft 80 provided by an embodiment of the present invention. As an example, the aircraft 80 may be an aircraft. Please refer to Fig. 8, the aircraft 80 may include:

Airframe 801 and the high-performance deep-stall wing structure 10 shown in any of the above-mentioned embodiments.

The aircraft 80 shown in the embodiment of the present invention can implement the technical solutions shown in any of the above-mentioned embodiments, and its implementation principles and beneficial effects are similar, and will not be repeated here.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than limiting them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: It is still possible to modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the technical solutions of the various embodiments of the present invention. scope.

Claims (4)

1. a high performance deep stall wing structure, comprising:

The plasma exciter is attached to the rear edge of the wing body, and the shape of the front edge of the wing body is a preset waveform;

The preset waveform is a triangular waveform, a sine waveform or a cosine waveform;

The plasma exciter comprises a covering electrode, an insulating medium and an exposed electrode;

the covered electrodes and the exposed electrodes are asymmetrically attached to two sides of the insulating medium, the covered electrodes are attached to the edge of the rear edge of the wing body, the first ends of the covered electrodes are flush with the lower surface of the rear edge of the wing body, and the first ends of the exposed electrodes are flush with the upper surface of the rear edge of the wing body; the distance between the straight line where the second end of the covered electrode is located and the straight line where the second end of the exposed electrode is located is M millimeters, and M is larger than 0 and smaller than or equal to 1.5;

The length of the covering electrode is equal to that of the exposed electrode and less than or equal to that of the wing body in the spanwise direction, and the length of the insulating medium is greater than that of the covering electrode; the width of each of the covering electrode and the exposed electrode is less than or equal to N micrometers, the width of the insulating medium is less than or equal to S micrometers, the height of each of the covering electrode and the exposed electrode is T times of the average aerodynamic chord length of the wing body, and the height of the insulating medium is greater than or equal to the sum of the height of the covering electrode, the height of the exposed electrode and the distance between the second end of the covering electrode and the second end of the exposed electrode; n is greater than 0 and less than or equal to 15, S is greater than 0 and less than or equal to 250, T is greater than or equal to 0.3% and less than or equal to 1%, and the height of the plane at the rear edge of the wing body is greater than or equal to the height of the insulating medium.

2. The structure of claim 1,

the wave amplitude of the preset waveform is P times of the average aerodynamic chord length of the wing body, the wavelength of the preset waveform is Q times of the average aerodynamic chord length of the wing body, wherein P is greater than or equal to 0.03 and less than or equal to 0.11, and Q is greater than or equal to 0.11 and less than or equal to 0.43.

3. The structure according to claim 1 or 2,

The covered electrode and the exposed electrode are both made of metal materials.

4. an aircraft, characterized in that it comprises:

an airframe and a high performance deep stall wing structure as claimed in any one of claims 1 to 3.