CN214824062U - Grid fusion wing for improving low-speed large-attack-angle flow characteristics - Google Patents
Grid fusion wing for improving low-speed large-attack-angle flow characteristics Download PDFInfo
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- CN214824062U CN214824062U CN202023162520.2U CN202023162520U CN214824062U CN 214824062 U CN214824062 U CN 214824062U CN 202023162520 U CN202023162520 U CN 202023162520U CN 214824062 U CN214824062 U CN 214824062U
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Abstract
The utility model discloses a grid fusion wing for improving the flow characteristic of a low-speed large attack angle, which comprises a basic single wing, a grid framework, a hollow wing structure formed on the basic single wing, a transverse grid clapboard and a longitudinal grid clapboard which are evenly distributed in the grid framework, the transverse grid partition plates are arranged along the direction parallel to the upper plate surface and the lower plate surface of the grid framework, the longitudinal grid partition plates are arranged along the direction vertical to the upper plate surface and the lower plate surface of the grid framework and are intersected with the transverse grid partition plates to divide the grid framework into a plurality of hollowed-out grid holes, the grid air inlets are arranged in the front edge area of the lower surface of the basic single wing, the grid air outlet is arranged on the upper surface of the basic single wing, formed by a cavity formed between the lower end surface of the transverse grid spacer and the lower plate surface of the grid frame. The utility model discloses a grid fuses wing can effectively restrain the big angle of attack air flow separation of wing under the condition that does not additionally consume the energy, do not produce additional resistance, increases the stall angle of attack of wing, promotes the maximum lift coefficient of wing.
Description
Technical Field
The utility model relates to an aeronautical equipment technical field, concretely relates to grid fusion wing that is used for big angle of attack flow characteristic of low-speed to improve.
Background
When the aircraft wing attack angle reaches the critical stall attack angle, the lift force of the aircraft wing decreases along with the increase of the attack angle, and the aircraft can generate out-of-control nose-down pitching movement and non-commanded rotation in the stall state. The main reason for generating stall is that asymmetric airflow separation occurs in the wings under a large attack angle state, and many aviation accidents are caused by wing stall, so that the improvement of the stall attack angle of the wings of the aircraft has important significance on the safety and the maneuverability of the aircraft.
The main method for inhibiting the airflow separation of the wings and delaying the stall of the wings at the current stage is a flow control technology, and the flow control technology is divided into passive flow control and active flow control according to a control mode. The most typical engineering application of the passive flow control technology is a vortex generator, and the main control mechanism of the passive flow control technology is that the vortex generator generates vortex to transmit energy to a boundary layer with low energy so as to achieve the effects of overcoming a counter pressure gradient and delaying airflow separation, further increase the stall attack angle and the maximum lift coefficient of the wing, and generate the lift increasing effect at the cost of resistance increase and lift-drag ratio reduction. Except for the vortex generator, the slotting airfoil, the bionic node and the groove technology belong to the category of passive flow control. The control mode of active flow control is that a proper disturbance mode is directly applied in a flow field and the flow is internally coupled with the flow characteristic of the flow to realize the control of the flow, and the main ways of inhibiting the separation of the gas flow comprise jet flow, blowing and suction, plasma releasing and the like.
The main disadvantages of active flow control are that extra energy consumption is needed to control the wing bypass flow, and the addition of active flow control related equipment increases the weight of the aircraft to a certain extent, which affects the economy of the aircraft. The passive flow control modes such as the vortex generator and the like can increase the resistance of the aircraft to a certain extent while inhibiting the airflow separation of the wings, and because the control modes of the passive flow control are designed in advance, the passive flow control cannot achieve the expected control effect when the flow field situation deviates from the design state, and even has adverse effects on the flow bypassing of the wings.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a grid fuses wing that is used for big angle of attack flow characteristic of low-speed to improve aims at improving the anti separation of big angle of attack of aerospace vehicle low-speed and stall characteristic.
The utility model adopts the technical proposal that:
a grid fusion fin for low speed high angle of attack flow characteristic improvement, the grid fusion fin comprising
A basic single wing is arranged on the upper portion of the wing,
a grid framework arranged on the basic single wing to form a hollow wing structure,
the transverse grid partition plates and the longitudinal grid partition plates are uniformly distributed in the grid framework, the transverse grid partition plates are arranged along the direction parallel to the upper plate surface and the lower plate surface of the grid framework, the longitudinal grid partition plates are arranged along the direction vertical to the upper plate surface and the lower plate surface of the grid framework and are intersected with the transverse grid partition plates to divide the grid framework into a plurality of hollowed-out grid holes,
the grid air inlet is arranged in the front edge area of the lower surface of the basic single wing and is formed by a cavity formed between the upper end surface of the transverse grid partition plate and the upper plate surface of the grid frame,
and the grid air outlet is arranged on the upper surface of the basic single wing and is formed by a cavity formed between the lower end surface of the transverse grid partition plate and the lower plate surface of the grid framework.
Preferably, the diversion angle of the grid frame is-10 degrees to-20 degrees.
Preferably, the grid framework overall span is 10% of the length of the base monowing chord.
Preferably, the thickness of the transverse grid partitions and the longitudinal grid partitions is 1% -2% of the length of the basic single wing chord line.
Preferably, the lattice width chord ratio of the hollowed grid holes is 0.14.
Preferably, the number of the arrangement of the transverse grid partitions is 1, and the number of the arrangement of the longitudinal grid partitions is 2.
The utility model has the advantages that:
the utility model discloses a grid that improves big angle of attack flow characteristic of wing fuses wing is applicable to low-speed and the big angle of attack state of subsonic speed, comprises basic single wing, grid frame, grid baffle triplex, and the arrangement of grid is fretwork wing (wing trompil) form, and the grid air inlet arranges in the region of appearing under basic single wing leading edge, and the grid gas vent arranges in basic single wing upper surface. The utility model discloses a grid fuses wing can effectively restrain the big angle of attack air flow separation of wing under the condition that does not additionally consume the energy, do not produce additional resistance, increases the stall angle of attack of wing, promotes the maximum lift coefficient of wing.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only 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 global view of a grid fusion wing for low speed high angle of attack flow characteristic improvement of the present invention;
fig. 2 is a top surface view of a grid fusion wing of the present invention for low speed high angle of attack flow characteristic improvement;
fig. 3 is a lower surface view of a grid fusion wing for low speed high angle of attack flow characteristic improvement in accordance with the present invention;
FIG. 4 is a cross-sectional view of a grid fusion wing;
FIG. 5 is a grid blended wing angle of flow guidance;
FIG. 6 is a flow diagram of a single wing and grid blend wing flow field; (a) a single wing; (b) a grid fusion wing;
fig. 7 is a graph of variation of lift coefficient and drag coefficient with angle of attack of a single wing and grids fused with different diversion angles (Ma is 0.6); (a) the lift coefficient is along the change curve of the attack angle; (b) the coefficient of resistance varies with angle of attack.
Wherein, 1-a grid framework; 2-basic single wing; 3-transverse grid spacers; 4-longitudinal grid spacers; 5-grid exhaust port; 6-a grid air inlet; 7-diversion angle.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying 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.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
The utility model particularly provides a grid fuses wing that is used for big angle of attack flow characteristic of low-speed to improve, as shown in fig. 1-5, grid fuses wing includes
A basic single wing is arranged on the upper portion of the wing,
a grid framework arranged on the basic single wing to form a hollow wing structure,
the transverse grid partition plates and the longitudinal grid partition plates are uniformly distributed in the grid framework, the transverse grid partition plates are arranged along the direction parallel to the upper plate surface and the lower plate surface of the grid framework, the longitudinal grid partition plates are arranged along the direction vertical to the upper plate surface and the lower plate surface of the grid framework and are intersected with the transverse grid partition plates to divide the grid framework into a plurality of hollowed-out grid holes,
the grid air inlet is arranged in the front edge area of the lower surface of the basic single wing and is formed by a cavity formed between the upper end surface of the transverse grid partition plate and the upper plate surface of the grid frame,
and the grid air outlet is arranged on the upper surface of the basic single wing and is formed by a cavity formed between the lower end surface of the transverse grid partition plate and the lower plate surface of the grid framework.
The utility model discloses a grid fuses wing device geometric features and describes as follows:
1) the flow guide angle of the grid frame is-10 degrees to-20 degrees, the flow guide angle can be correspondingly adjusted according to actual needs, the flow guide angle is defined as the included angle between the chord direction of the grid and the chord line of the basic single wing, and the flow guide angle of the grid structure air inlet is a negative value when the grid structure air inlet is arranged on the lower surface of the basic single wing.
2) The basic single wing airfoil profile is an NACA2214 airfoil profile, and other airfoil profiles can be selected according to the actual needs of the aircraft.
3) The overall lattice width of the grid framework is about 10% of the length of the base monowing chord.
4) The thickness of the grid partition (including the transverse grid partition and the longitudinal grid partition) is 1% -2% of the length of the basic single wing chord.
5) The lattice width chord ratio of the hollowed-out lattice holes is about 0.14, and the change of the lattice number has influence on the dimensionless numerical value. The lattice width chord ratio refers to the ratio of the width (longitudinal length) of each hollowed-out grid hole to the chord length of the grid partition plate.
6) The arrangement number of the transverse grid partition plates is 1, the arrangement number of the longitudinal grid partition plates is 2, and the arrangement number of the grid partition plates can be adjusted according to the structural strength requirement.
The flow guide angles and the number of the transverse grid partition plates in the geometric parameters are obtained through comparison of numerical experiments, and table 1 and table 2 are the aerodynamic characteristic numerical experiment data of the grid fusion wing with different flow guide angles in the low-speed and subsonic states, so that the stall attack angles of the grid fusion wing are obviously larger than those of a conventional single wing when the flow guide angle is in the range of-10 degrees to-20 degrees in the low-speed (Ma is 0.3), the grid fusion wing has a relatively larger maximum lift coefficient when the flow guide angle is-10 degrees, and the grid fusion wing has a larger stall attack angle when the flow guide angle is-20 degrees. When the diversion angle is-20 ° under subsonic (Ma ═ 0.6) state, the grid fuses the wing and possesses bigger stall angle of attack and maximum lift coefficient simultaneously, so the utility model discloses a range is selected to the diversion angle of grid fuses the wing and is got for-10 to-20.
Table 1 influence of diversion angle on aerodynamic characteristics of large angle of attack of lattice fusion wing (Ma ═ 0.3)
Table 2 influence of diversion angle on aerodynamic characteristics of large angle of attack of grid fusion wing (Ma ═ 0.6)
Table 3 has demonstrated that the grid of horizontal grid baffle quantity difference fuses wing aerodynamic characteristic numerical experiment data under subsonic (Ma ═ 0.6) state, can find that the size of grid fuses wing stall angle of attack is irrelevant basically with horizontal grid baffle quantity, the grid that does not have under the horizontal grid baffle condition fuses the wing is fused to the grid that the maximum lift coefficient of grid fused the wing is less than having horizontal grid baffle relatively, horizontal grid baffle quantity is more than 1 back along with the change of the maximum lift coefficient of the increase of baffle quantity and is not obvious, adopt more horizontal grid baffle can lead to the increase of resistance, so the utility model discloses a grid fuses the horizontal grid baffle quantity of wing and gets to be 1.
The grid fuses the vertical grid baffle arrangement quantity of wing right the utility model relates to a grid fuses the aerodynamic characteristic of wing and influences lessly, arranges the leading cause of vertical grid baffle for the structural strength of reinforcing grid fusion wing, and it arranges that quantity is to select according to the experience of arranging of conventional grid wing baffle.
TABLE 3 influence of number of transverse grid spacers on aerodynamic performance of large angle of attack of grid-fused airfoil (Ma ═ 0.6)
The other geometric parameters mainly comprise the thickness of the longitudinal grid partition plate, the thickness of the transverse grid partition plate, the grid width of the grid assembly and the grid width-wing chord ratio, and most of the parameters are set according to engineering practice experience.
On the pneumatic level, the smaller the thickness of the grid longitudinal partition plate and the smaller the thickness of the grid transverse partition plate are, the better the pneumatic characteristics of the grid fusion wing are, but in order to ensure the structural strength of the longitudinal grid partition plate and the transverse grid partition plate and the reliability and the safety of the grid fusion wing, the thickness of the grid fusion wing is set to be 1% -2% of the wing chord length after the comprehensive consideration of the design data of the existing grid wing;
the whole lattice width of the grid framework is influenced by the maximum thickness of the wing and the diversion angle of the grid framework, and the width of the grid framework is about 10% of the length of the wing chord, so that a design space can be reserved for the grid fusion wing under the condition of other diversion angles on the basis of ensuring the large attack angle aerodynamic performance of the grid fusion wing;
the wide chord ratio of the check of single grid hole who is cut apart into with grid frame by vertical grid baffle and horizontal grid baffle is decided by the whole width of grid frame, water conservancy diversion angle, wing airfoil, and above-mentioned any parameter changes and all can lead to the fluctuation of the wide chord ratio of check, because the utility model discloses a grid fuses the whole width of grid frame, water conservancy diversion angle of wing, has been the result after preferred, and the wide chord ratio of check decided jointly by the three is great with conventional grid wing difference, nevertheless more is applicable to the grid fuses the wing the utility model discloses a grid.
The utility model discloses a grid fuses wing can effectively restrain the big angle of attack air flow separation of wing under the condition that does not additionally consume the energy, do not produce additional resistance, increases the stall angle of attack of wing, promotes the maximum lift coefficient of wing. The main mechanism of the grid fusion wing for inhibiting airflow separation and improving the lift performance of the large attack angle of the wing is that the grid structure guides high-energy airflow on the lower surface of the wing to a low-energy separation area on the upper surface of the wing to inhibit airflow separation on the upper surface of the wing. Meanwhile, as the rear stagnation point of the lifting surface moves backwards, the pressure of the lower surface of the grid fusion wing is higher than that of the basic single wing, so that the grid fusion wing has better aerodynamic characteristics with a large attack angle.
Simulation example
The numerical simulation method based on three-dimensional reynolds average Navier-Stokes equation has been used to this embodiment to carry out numerical simulation to the big angle of attack aerodynamic characteristic of grid fusion wing, has verified the utility model discloses a grid fusion wing restraines the air current separation under subsonic speed state, increases wing stall angle of attack and maximum lift coefficient's ability, has proven the utility model relates to a grid fusion wing is at the practicality of big angle of attack state.
The simulation object is a basic single wing and a grid fusion wing with grid diversion angles of-10 degrees and-20 degrees, the basic single wing airfoil is an NACA2214 airfoil, the integral grid width of a grid frame is 10% of the chord length of the basic single wing, the thicknesses of the transverse grid partition plates and the longitudinal grid partition plates are 1% of the chord length of the basic single wing, the grid width chord ratio of a single hollowed grid hole is 0.14, the arrangement number of the transverse grid partition plates is 1, and the arrangement number of the longitudinal grid partition plates is 2. The simulated incoming flow Mach number is 0.6, and the wing attack angle is 0-36 degrees.
Fig. 6 is a streamline graph of single wing (a) and grid fusion wing (b) under the condition that mach number is 0.6, and the angle of attack is 28 °, and it can be found that the utility model discloses a grid fusion wing can effectively restrain the air current separation of wing upper surface, and the stagnant water zone that flows of wing upper surface obviously reduces under the effect of grid exhaust air current, and this lift performance when having the stall angle of attack and the big angle of attack that promotes the wing has important meaning.
FIG. 7 is a graph of the variation of lift coefficient and drag coefficient with attack angle of a grid-fused wing with a single wing and different diversion angles, wherein the stall attack angle of the grid-fused wing with the diversion angle of-10 degrees is increased by about 8 degrees and the maximum lift coefficient is increased by about 10 percent compared with the single wing; the stall attack angle of the grid fusion wing with the diversion angle of-20 degrees is improved by about 16 degrees, and the maximum lift coefficient is improved by about 20 percent. The drag coefficient of the grid fusion wing with the diversion angle of-20 degrees under the condition of larger attack angle is closer to that of the single wing, and the drag coefficient of the grid fusion wing with the diversion angle of-10 degrees under the condition of larger attack angle is slightly smaller than that of the single wing.
The numerical simulation method verifies that the grid fusion wing device designed in the embodiment can effectively inhibit the airflow separation of the wing in a large attack angle state, improves the large attack angle flow characteristic of the wing under the conditions of no extra energy consumption and no additional resistance, and obviously improves the stall attack angle and the maximum lift coefficient of the wing.
The above description is only for the purpose of illustrating the technical solutions of the present invention and not for the purpose of limiting the same, and other modifications or equivalent replacements made by those of ordinary skill in the art to the technical solutions of the present invention should be covered within the scope of the claims of the present invention as long as they do not depart from the spirit and scope of the technical solutions of the present invention.
Claims (6)
1. A grid fusion fin for low-speed high-angle-of-attack flow improvement, characterized in that it comprises
A basic single wing is arranged on the upper portion of the wing,
a grid framework arranged on the basic single wing to form a hollow wing structure,
the transverse grid partition plates and the longitudinal grid partition plates are uniformly distributed in the grid framework, the transverse grid partition plates are arranged along the direction parallel to the upper plate surface and the lower plate surface of the grid framework, the longitudinal grid partition plates are arranged along the direction vertical to the upper plate surface and the lower plate surface of the grid framework and are intersected with the transverse grid partition plates to divide the grid framework into a plurality of hollowed-out grid holes,
the grid air inlet is arranged in the front edge area of the lower surface of the basic single wing and is formed by a cavity formed between the upper end surface of the transverse grid partition plate and the upper plate surface of the grid frame,
and the grid air outlet is arranged on the upper surface of the basic single wing and is formed by a cavity formed between the lower end surface of the transverse grid partition plate and the lower plate surface of the grid framework.
2. The grid fusion wing for low-speed high-angle-of-attack flow characteristic improvement according to claim 1, wherein a draft angle of the grid frame is-10 ° to-20 °.
3. A lattice-blending wing for low-speed high-angle-of-attack flow property improvement according to claim 1, characterized in that the lattice frame overall span is 10% of the length of the base mono-wing chord line.
4. The lattice fusion wing for low-velocity high-angle-of-attack flow characteristic improvement according to claim 1, wherein the thickness of the transverse lattice partitions and the longitudinal lattice partitions is 1% to 2% of the length of a base singlet chord line.
5. The lattice fusion wing for improved low velocity high angle of attack flow characteristics of claim 1, wherein the lattice width chord ratio of the pierced lattice holes is 0.14.
6. The cascade fusion vane for improvement in low-speed high-angle-of-attack flow characteristics of claim 1, wherein the number of transverse cascade arrangements is 1 and the number of longitudinal cascade arrangements is 2.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202023162520.2U CN214824062U (en) | 2020-12-24 | 2020-12-24 | Grid fusion wing for improving low-speed large-attack-angle flow characteristics |
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| CN202023162520.2U CN214824062U (en) | 2020-12-24 | 2020-12-24 | Grid fusion wing for improving low-speed large-attack-angle flow characteristics |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114879718A (en) * | 2022-07-12 | 2022-08-09 | 南京理工大学 | Method for controlling an aircraft with a grid rudder |
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2020
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114879718A (en) * | 2022-07-12 | 2022-08-09 | 南京理工大学 | Method for controlling an aircraft with a grid rudder |
| CN114879718B (en) * | 2022-07-12 | 2022-09-13 | 南京理工大学 | Method for controlling an aircraft with a grid rudder |
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