CN106564585B - High-performance deep stall wing structure and aircraft - Google Patents
High-performance deep stall wing structure and aircraft Download PDFInfo
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- CN106564585B CN106564585B CN201610968343.6A CN201610968343A CN106564585B CN 106564585 B CN106564585 B CN 106564585B CN 201610968343 A CN201610968343 A CN 201610968343A CN 106564585 B CN106564585 B CN 106564585B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/146—Aerofoil profile comprising leading edges of particular shape
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a high-performance deep stall wing structure and an aircraft, and belongs to the technical field of aviation equipment. This high performance deep stall wing structure includes: 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 a full attack angle range.
Description
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
In the field of aviation, the emphasis of people has been on improving the aerodynamic performance of aircrafts. Wherein separation and stalling of the wing body at high angles of attack can affect the aerodynamic performance of the aircraft, thereby compromising passenger safety.
In the prior art, in order to solve the problems of separation and stall of an airfoil body under a large attack angle, a conceptual design scheme is that a smooth front edge of an original airfoil body is modified into an uneven front edge, so that when airflow flows through the front edge of the airfoil body, a vortex is curled up from a concave part to a convex part, the vortex is elongated by the airflow in the flowing direction and extends downstream, and meanwhile, the vortex rotates by taking the flowing direction as an axis to gradually form turbulence with higher flowing mixing degree, so that high-speed flow far away from the surface of the airfoil body is involved into low-speed flow close to the surface of the airfoil body, the kinetic energy of the airflow close to the surface of the airfoil body is increased, the capability of a boundary layer for resisting flowing separation is improved, and the phenomena of separation and stall of the airfoil body.
However, in the prior art, although the phenomenon of separation and stall of the wing body at a large attack angle is eliminated through the uneven leading edge of the wing body, and the aerodynamic performance of the aircraft at the large attack angle is improved, the maximum lift force of the wing body is reduced in the middle and small attack angles by adopting the method, so that the aerodynamic performance of the aircraft at the middle and small attack angles is poor.
Disclosure of Invention
The invention provides a high-performance deep stall wing structure and an aircraft, and aims to improve the aerodynamic performance of the aircraft in a full attack angle range.
The embodiment of the invention provides a high-performance deep stall wing structure, which comprises:
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 invention, the pre-wave shape is a triangular waveform, a sine waveform or a cosine waveform.
In one embodiment of the present invention, the plasma exciter comprises a cover electrode, an insulating medium and a bare electrode.
In an embodiment of the present invention, the covered electrode and the exposed electrode are asymmetrically attached to two sides of the insulating medium, the covered electrode is attached to the trailing edge of the wing body, a first end of the covered electrode is flush with the lower surface of the trailing edge of the wing body, and a first end of the exposed electrode is flush with the upper surface of the trailing edge of the wing body.
In an embodiment of the invention, a distance between a straight line where the second end of the covered electrode is located and a straight line where the second end of the exposed electrode is located is M millimeters, and 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 airfoil body in the spanwise direction, and the length of the insulating medium is greater than the length of the covered 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 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 trailing edge of the wing body is greater than or equal to the height of the insulating medium.
in an embodiment of the invention, an amplitude of the preset shape is P times of an average aerodynamic chord length of the airfoil body, and a wavelength of the preset shape is Q times of the average aerodynamic chord length of the airfoil body, where 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 invention, the covered electrode and the exposed electrode are made of metal.
an embodiment of the present invention further provides an aircraft, including:
The airframe and the high performance deep stall wing structure of any one of the embodiments described above.
The embodiment of the invention provides a high-performance deep stall wing structure and an aircraft, wherein the high-performance deep stall wing structure comprises: 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. It can thus be seen that, in embodiments of the invention, by attaching a plasma exciter at the trailing edge of the airfoil body, so that the surface of the plasma exciter can periodically generate a direction from the exposed electrode to the covered electrode under the driving of a high-voltage high-frequency alternating current power supply, and the wall surface jet flow in the direction from the covered electrode to the exposed electrode washes the backflow area downwards, so that the lift force of the wing body can be improved, thereby improving the aerodynamic performance of the aircraft at medium and small attack angles, in addition, the kinetic energy of the airflow close to the surface of the wing body can be increased by setting the shape of the front edge of the wing body into a preset waveform, thereby improving the ability of the boundary layer to resist flow separation and further improving the aerodynamic performance of the aircraft under a large attack angle, namely, the high-performance deep stall wing structure provided by the embodiment of the invention improves the aerodynamic performance of an aircraft in a full attack angle range.
drawings
in order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a high performance deep stall wing structure according to an embodiment of the present invention;
FIG. 2 is a top view of a leading edge of a wing body provided in accordance with an embodiment of the present invention;
FIG. 3 is a schematic structural view of another high performance deep stall wing configuration provided by an embodiment of the present invention;
Fig. 4 is a schematic structural diagram of a plasma exciter according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of the electron flow direction of a high-voltage high-frequency sinusoidal AC signal in the negative half cycle according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of the electron flow direction of a high voltage high frequency sinusoidal AC signal during a positive half cycle according to an embodiment of the present invention;
FIG. 7 is a graph of angle of attack versus lift coefficient provided by an embodiment of the present invention;
fig. 8 is a schematic structural diagram of an aircraft according to an embodiment of the present invention.
Detailed Description
In order to make the objects, 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 with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
the terms "first," "second," "third," "fourth," and the like in the description and in the claims, as well as in the drawings, if any, are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are, for example, capable of operation in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, 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 described in detail in some embodiments.
Fig. 1 is a schematic structural diagram of a high-performance deep stall wing structure 10 according to an embodiment of the present invention, please refer to fig. 1, but the embodiment of the present invention is only illustrated in fig. 1, and the present invention is not limited thereto. The high performance deep stall wing structure 10 includes:
The plasma exciter 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.
The large attack angle generally refers to an attack angle with an angle greater than or equal to 12 degrees, the medium attack angle refers to an attack angle with an angle smaller than 12 degrees, and of course, the angles can be divided according to actual needs.
For example, the shape of the leading edge of the wing body 101 is a preset waveform 102, and the preset waveform 102 refers to the shape having a wavelength and an amplitude, please refer to fig. 2, and fig. 2 is a top view of the leading edge of the wing body 101 according to an embodiment of the present invention.
In the embodiment of the invention, by attaching the plasma exciter 103 at the rear edge of the wing body 101, when the plasma exciter 103 is turned on, the surface of the plasma exciter 103 periodically generates a direction from the exposed electrode 1033 to the covered electrode 1031 and a wall surface jet flow in a direction from the covered electrode 1031 to the exposed electrode 1033 to wash back flow regions downwards under the driving of a high-voltage high-frequency alternating current power supply, so that a downstream pumping effect is generated on the upper surface of the wing body 101, and the pumping effect further improves the capability of resisting flow separation. More importantly, the suction effect increases the flow speed of the airflow on the upper surface of the wing body 101 in the downstream direction, so that the circulation of the wing body 101 is increased, and the lift force is increased. Meanwhile, the speed of the free incoming flow impacting the wall jet flow on the lower surface of the wing body 101 is reduced, so that a small low-speed high-pressure backflow area is formed on the lower surface of the wing body 101, the pressure of the lower surface is increased, the lift force of the wing body 101 can be improved, and the aerodynamic performance of the aircraft at medium and small attack angles is improved.
further, in the embodiment of the present invention, by shaping the leading edge of the wing body 101 into the preset waveform 102, when the airflow flows through the leading edge of the wing body 101, a vortex is curled from the concave to the convex, the vortex is elongated by the airflow in the flow direction and extends downstream, and the vortex rotates around the flow direction as an axis and gradually forms turbulent flow with higher degree of flow disorder in the downstream development. The entrainment capacity of the vortex and the mixing capacity of the turbulent flow can roll the high-speed flow far 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 close to the surface of the wing body 101 is increased, the capacity of a boundary layer for resisting flow separation is improved, and the aerodynamic performance of the aircraft under a large attack angle is improved.
The embodiment of the present invention provides a high performance deep stall wing structure 10, where the high performance deep stall wing structure 10 includes: the plasma exciter 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. It can be seen that, in the present embodiment, by attaching the plasma exciter 103 at the trailing edge of the airfoil body 101, so that under the driving of the high-voltage high-frequency alternating current power supply, the surface of the plasma exciter 103 can periodically generate the direction from the bare electrode 1033 to the covering electrode 1031, and the wall surface jet flow in the direction from the covering electrode 1031 to the exposed electrode 1033 washes the backflow area downwards, so that the lifting force of the wing body 101 can be improved, thereby improving the aerodynamic performance of the aircraft at medium and small attack angles, in addition, the kinetic energy of the airflow close to the surface of the wing body 101 can be increased by setting the shape of the leading edge of the wing body 101 to be the preset waveform 102, thereby improving the ability of the boundary layer to resist flow separation and further improving the aerodynamic performance of the aircraft under a large attack angle, namely, the high-performance deep stall wing structure 10 provided by the embodiment of the invention improves the aerodynamic performance of the aircraft in the full attack angle range.
Based on the embodiment corresponding to fig. 1, on the basis of the embodiment corresponding to fig. 1, further, another high-performance deep stall wing structure 10 is provided in the embodiment of the present invention, please refer to fig. 3, where fig. 3 is a schematic structural diagram of another high-performance deep stall wing structure 10 provided in the embodiment of the present invention, of course, the embodiment of the present invention is only illustrated by fig. 2, but it does not mean that the present invention is limited thereto. The high performance deep stall wing structure 10 further comprises:
Optionally, the plasma actuator 103 includes a covered electrode 1031, an insulating medium 1032, and a bare electrode 1033.
For example, please refer to fig. 4, fig. 4 is a schematic structural diagram of a plasma exciter 103 according to an embodiment of the present invention, and it should be understood that the present invention is only illustrated in fig. 3, but the present invention is not limited thereto. The covered electrode 1031 and the exposed electrode 1033 are asymmetrically attached to two sides of the insulating medium 1032, the covered electrode 1031 is attached to the edge of the rear edge of the wing body 101, the first end of the covered electrode 1031 is flush with the lower surface of the rear edge of the wing body 101, and the first end of the exposed electrode 1033 is flush with the upper surface of the rear edge of the wing body 101.
among them, the insulating medium 1032 between the bare electrode 1033 and the covered electrode 1031 of the plasma actuator 103 plays a role of blocking high-voltage high-frequency discharge. The bare electrode 1033 and the covered electrode 1031 are respectively connected to two output terminals of a high-voltage high-frequency power supply, and the covered electrode 1031 serves as a reference potential.
Optionally, a distance between a straight line where the second end of the covered electrode 1031 is located and a straight line where the second end of the exposed electrode 1033 is located is M millimeters, and M is greater than or equal to 0 and less than or equal to 1.5.
The distance between the straight line of the second end of the covered electrode 1031 and the straight line of the second end of the exposed electrode 1033 is the vertical distance between the straight line of the second end of the covered electrode 1031 and the straight line of the second end of the exposed electrode 1033. Preferably, in the embodiment of the present invention, a distance value M between a straight line of the second end of the covered electrode 1031 and a straight line of the second end of the bare electrode 1033 is 0, that is, one end of the covered electrode 1031 coincides with one end of the bare electrode 1033, so as to improve the discharge performance of the plasma exciter 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 span-wise direction of the wing body 101, and the length of the insulating medium 1032 is greater than the length of the covered electrode 1031, so as to completely cover the covered electrode 1031; the widths of the covered electrode 1031 and the exposed electrode 1033 are less than or equal to N micrometers, the width of the insulating medium 1032 is less than or equal to S micrometers, the heights of the covered electrode 1031 and the exposed electrode 1033 are both T times of the average aerodynamic chord length of the wing body 101, and 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 trailing edge of the wing body 101 is greater than or equal to the sum of the bare electrode 1033, the covered electrode 1031, and the inter-electrode gap height.
For example, in the embodiment of the present invention, in order to facilitate the installation and use of the plasma exciter 103, it is generally required that the trailing edge of the wing body 101 should be sharpened. I.e. the rounded or pointed trailing edge is modified to a plane, and the height of the modified plane is not less than the sum of the bare electrode 1033, the covered electrode 1031 and the inter-electrode gap height of the plasma exciter 103, so that the plasma exciter 103 can be better attached to the trailing edge of the airfoil body 101.
In addition, in general, the height of the insulating medium 1032 is equal to or greater than 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 extends at least 1 mm to 2 mm at the outer end of the covered electrode 1031, so as to avoid end-face discharge between the exposed electrode 1033 and the covered electrode 1031 through the insulating medium 1032, thereby improving the high voltage resistance of the plasma exciter 103.
Further, by setting the thickness of the bare electrode 1033 and the covered electrode 1031 to be not more than 15 microns, and the thickness of the insulating medium 1032 to be not more than 250 microns, the plasma exciter 103 can be directly attached to the trailing edge of the wing body 101, and the disturbance of the plasma exciter 103 caused by the incoming flow can be ignored because the thickness of the plasma exciter 103 is small relative to the thickness of the local flow boundary layer. In the embodiment of the invention, the plasma is directly attached to the rear edge of the wing body 101 instead of being integrally processed and formed with the wing body 101, so that the realization mode is simple and convenient, and the feasibility is high. In addition, since the effect of the plasma exciter 103 can be realized by adjusting the power supply signal, the pilot can adjust the control effect according to the actual flight requirement, thereby realizing the optimal flight state of the aircraft.
In the practical application, the waveform of the high-voltage high-frequency voltage is taken as a sine waveform signal as an example for explanation. The voltage peak value of the power supply signal is required to be 2kV to 24kV, and the frequency is required to be 1kHz to 15 kHz. Wherein the control effect of the plasma actuator 103 on the flow increases with increasing voltage and frequency, and at the same time, to take into account the requirements of the on-board equipment, the equipment should not operate at too high a power consumption, and therefore the voltage and frequency of the power supply signal should not be too high. For example, please refer to fig. 5, fig. 5 is a schematic diagram of an electron flow direction of a high-voltage high-frequency sinusoidal ac signal in a negative half cycle according to an embodiment of the present invention. When the high-voltage high-frequency sinusoidal alternating-current signal is in a negative half cycle, that is, the bare electrode 1033 is at a low potential relative to the covered electrode 1031, the high-voltage high-frequency action ionizes air near the bare electrode 1033 to form electrons, and the electrons move on the surface of the insulating medium 1032 under the action of an electric field force to form an electron flow in a direction from the bare electrode 1033 to the covered electrode 1031, and a discharge direction is directed from the bare electrode 1033 to the covered electrode 1031. Due to the blocking effect of the insulating medium 1032, a small portion of electrons may pass through the surface layer of the insulating medium 1032, but a large portion of electrons cannot pass through the insulating medium 1032 to reach the covering electrode 1031, and therefore, a large portion of electrons are gathered and stayed on the surface of the insulating medium 1032 outside the covering electrode 1031. The discharge process continues, and electrons generated by the high-voltage high-frequency discharge continuously move from the bare electrode 1033 to the insulating medium 1032 covering the surface of the electrode 1031 until the potential of the bare electrode 1033 is higher than that of the covered electrode 1031. At the same time as the electrons move, the air viscosity effect drives the surrounding air to move together, so that a wall surface jet flow of the surface of the insulating medium 1032 is generated, wherein the wall surface jet flow is directed from the exposed electrode 1033 to the covering electrode 1031.
Similarly, referring to fig. 6, fig. 6 is a schematic diagram of an electron flow direction of a high-voltage high-frequency sinusoidal ac signal in a positive half cycle according to 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 low potential relative to the bare electrode 1033, the high voltage high frequency action causes air in the vicinity of the covered electrode 1031 to ionize to form electrons. Due to the blocking effect of the insulating medium 1032, electrons generated by the covered electrode 1031 cannot pass through the insulating medium 1032 to the exposed electrode 1033, but electrons collected near the insulating medium 1032 outside the covered electrode 1031 can move to the exposed electrode 1033 under the driving of the electric field force to form an electron flow in the direction from the covered electrode 1031 to the exposed electrode 1033, and the discharge direction is directed from the covered electrode 1031 to the exposed electrode 1033. The discharge process continues, and the electrons collected on the surface of the covered electrode 1031 continuously flow from the covered electrode 1031 direction to the exposed electrode 1033 direction until the potential of the covered electrode 1031 is higher than the potential of the exposed electrode 1033. At the same time as the electrons move, the air viscosity drives the surrounding air to move together, so that a wall surface jet flow of the surface of the insulating medium 1032 is generated, wherein the wall surface jet flow is directed from the covering electrode 1031 to the exposed electrode 1033.
After the wall jets are formed in the positive half cycle and the negative half cycle, the high-speed wall jets wash the recirculation zone downward, so that the tail end recirculation zone, which is originally low in speed and high in pressure, becomes a high-speed low-pressure zone, and a downstream pumping effect is generated on the upper surface of the wing body 101, and the pumping effect further improves the flow separation resistance of the wing body. More importantly, the suction effect increases the flow speed of the airflow on the upper surface of the wing body 101 in the downstream direction, so that the circulation of the wing body 101 is increased, and the lift force is increased. Meanwhile, the speed of the free incoming flow impacting the wall jet flow on the lower surface of the wing body 101 is reduced, so that a small low-speed high-pressure backflow area is formed on the lower surface of the wing body 101, the pressure of the lower surface is increased, the lift force of the wing body 101 can be improved, and the aerodynamic performance of the aircraft at medium and small attack angles is improved.
Optionally, the covered electrode 1031 and the exposed electrode 1033 are made of metal.
For example, in the embodiment of the present invention, the bare electrode 1033 and the covered electrode 1031 are both made of a metal material having a conductive property, such as a copper foil. In addition, the insulating medium 1032 is made of an insulating material having high impedance and good insulating properties, such as epoxy resin, quartz glass, ceramic, a polyimide film, or a polyester film. In particular, the insulating medium 1032 of the plasma actuator 103 may be made of flexible polyester film to form the flexible plasma actuator 103, so as to be attached to the curved surface.
Optionally, the pre-wave shape is a triangular waveform, a sine waveform or a cosine waveform. Furthermore, the amplitude of the preset shape is P times of the average aerodynamic chord length of the wing body 101, and the wavelength of the preset shape is Q times of 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, and Q is greater than or equal to 0.11 and less than or equal to 0.43.
where amplitude represents the distance between the peak and trough of the sine wave defining the leading edge shape and wavelength represents the distance between the peak and peak (or the distance between trough and trough) of the sine wave defining the leading edge shape. If the amplitude is too large, the lift loss and the resistance increase are relatively remarkable; if the amplitude is too small, the ability to attenuate separation and eliminate stall at high angles of attack is impaired. If the wavelength is too large, its ability to attenuate separation and eliminate stall at high angles of attack is compromised.
in the embodiment of the present invention, the shape of the leading edge of the wing body 101 is set to be a triangular waveform, a sine waveform or a cosine waveform. As the airflow passes over the leading edge of the wing body 101, a vortex is swirled from the valley to the peak, the vortex being elongated by the airflow in the direction of flow and extending downstream, the vortex rotating about the direction of flow and gradually creating turbulence that is more turbulent in the downstream direction. The entrainment capacity of the vortex and the mixing capacity of the turbulent flow can roll the high-speed flow far 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 close to the surface of the wing body 101 is increased, the capacity of a boundary layer for resisting flow separation is improved, and the aerodynamic performance of the aircraft under a large attack angle is improved.
In the application process, the lift coefficient of the wing body 101 can be increased by using the plasma exciter 103, so that the lift of the wing body 101 is improved, as shown in fig. 7, fig. 7 is a relationship graph of an attack angle and a lift coefficient, provided by the embodiment of the invention, wherein the abscissa represents the attack angle alpha, and the ordinate represents the lift coefficient C L, for example, the frequency of the plasma exciter 103 is 3kHz, the peak-to-peak voltage value is 4 kV., as can be seen from fig. 7, after the plasma exciter 103 is turned on (white hollow line), the lift coefficient curve is shifted upwards at a medium and low attack angle, so that the overall lift of the wing body 101 is improved, compared with the case that the plasma exciter 103 is turned off (black solid line), while the lift increasing capability at a low and low attack angle is obviously weakened, the plasma exciter 103 can further improve the lift increasing capability at a high attack angle.
Fig. 8 is a schematic structural diagram of an aircraft 80 according to an embodiment of the present invention, where the aircraft 80 may be an airplane, and please refer to fig. 8, the aircraft 80 may include:
The body 801 and the high performance deep stall wing structure 10 of any of the embodiments described above.
The aircraft 80 shown in the embodiment of the present invention may implement the technical solutions shown in any of the above embodiments, and the implementation principles and beneficial effects thereof are similar and will not be described herein again.
finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610968343.6A CN106564585B (en) | 2016-10-26 | 2016-10-26 | High-performance deep stall wing structure and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610968343.6A CN106564585B (en) | 2016-10-26 | 2016-10-26 | High-performance deep stall wing structure and aircraft |
Publications (2)
| Publication Number | Publication Date |
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| CN106564585A CN106564585A (en) | 2017-04-19 |
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| CN107037824B (en) * | 2017-06-09 | 2023-10-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Transverse control device and control method for flying wing model |
| CN107914865B (en) * | 2017-11-27 | 2020-09-25 | 西北工业大学 | Plasma virtual dynamic bionic device and method for wing leading edge |
| CN109050876B (en) * | 2018-07-13 | 2021-04-06 | 北京航空航天大学 | Use miniature unmanned aerial vehicle of bionical wing |
| CN109305326B (en) * | 2018-09-21 | 2020-08-11 | 北京航空航天大学 | Wing and aircraft |
| CN112373673B (en) * | 2020-09-25 | 2023-09-26 | 哈尔滨工业大学 | Flow control method of leading edge biconvex structure for improving performance of biconvex wing section |
| CN112298549A (en) * | 2020-10-30 | 2021-02-02 | 北京航空航天大学 | Tilt rotor with bionic wavy leading edge and tilt rotor aircraft |
| CN113460285B (en) * | 2021-09-03 | 2021-11-23 | 中国商用飞机有限责任公司 | High lift device for fixed wing aircraft and manufacturing method thereof |
| CN115716529B (en) * | 2023-01-10 | 2023-05-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing leading edge drooping dynamic stall control device and method |
| CN116873187B (en) * | 2023-09-07 | 2023-11-14 | 中国航空工业集团公司沈阳空气动力研究所 | Low-Reynolds-number low-noise bionic coupling wing based on owl wing characteristics |
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