CN210416955U - Low-speed unmanned aerial vehicle wing section with high lift-drag ratio - Google Patents
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Abstract
The utility model discloses a high lift-drag ratio's low-speed unmanned aerial vehicle wing section, wing section are button head point tail shape, and the wing section has designed head leading edge radius, chord length, maximum relative thickness position, maximum relative camber and maximum relative camber position, makes the wing section have great thickness, less camber, possesses better pneumatic performance simultaneously, can satisfy low-speed long time unmanned aerial vehicle's operation requirement when navigating. The utility model discloses have potential market value.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle field, in particular to high lift-drag ratio's low-speed unmanned aerial vehicle wing section.
Background
The wings have the function of lifting weight in the appearance design of an aircraft, and the aerodynamic and mechanical properties of the wings are mainly influenced by the wing profiles. In order to improve the aerodynamic and mechanical properties of an aircraft, high performance airfoils need to be selected. At present, the high lift wing section that domestic low-speed unmanned aerial vehicle's wing was used generally divide into two kinds: the unmanned aerial vehicle has the advantages that the unmanned aerial vehicle has larger thickness, smaller camber and lower lift-drag ratio, is beneficial to the mechanical design of the wing structure, but is not beneficial to improving the pneumatic related performances of the unmanned aerial vehicle such as cruise, climbing and the like, such as CLARKY and NACA 4412; and secondly, the unmanned aerial vehicle has smaller thickness, larger camber and higher lift-drag ratio, is unfavorable for the mechanical design of the wing structure, but is beneficial to improving the aerodynamic related performances of the unmanned aerial vehicle such as cruise, climbing and the like, such as NACA 6409. At present, no wing section which has wing structural mechanical design and has better aerodynamic performance exists, and the use requirement of the unmanned aerial vehicle during low-speed long-endurance can be met.
Disclosure of Invention
In order to solve the technical problem, the utility model discloses a high lift-drag ratio's low-speed unmanned aerial vehicle wing section.
The technical scheme of the utility model is that: the high lift-drag ratio low speed unmanned aerial vehicle wing section uses the vertical line passing through the left end point of the wing section as Y axis, uses the horizontal line passing through the left end point of the wing section as X axis, and the expressions of the upper edge curve and the lower edge curve of the wing section are respectively
Wherein,
x is the abscissa, yUIs the ordinate of the upper arc, yLIs the ordinate of the lower arc; au coatingiFrom i to 0 to i to 5 are-0.22573, -0.27045, -0.30945, -0.28817, -0.33337 and-0.29560 in sequence, and AliFrom i-0 to i-5, in the order-0.13119, -0.01689, -0.03217, -0.04308, 0.00361, 0.10598, the trailing edge thickness Δ ξU＝ΔξL. Can be 0.00135, and can also be changed according to the actual thickness requirement.
The utility model discloses carried out redesign to low-speed unmanned aerial vehicle wing section, according to design condition and index requirement, on NACA 6409 high lift-drag ratio wing section basis, the new wing section of design out has great thickness, less camber, possesses better aerodynamic performance simultaneously, can satisfy low-speed long time unmanned aerial vehicle's operation requirement when navigating.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive labor.
FIG. 1 is a schematic view of the geometrical profile of the airfoil of the present invention;
FIG. 2 is a schematic diagram comparing the airfoil shape of the present invention with the airfoil shape of NACA 6409;
FIG. 3 is a comparison graph of lift drag coefficient of airfoil profile and NACA 6409 airfoil profile varying with angle of attack;
fig. 4 is a comparison graph of the lift-drag ratio and pitching moment of the airfoil profile of the present invention and NACA 6409 airfoil profile with the change of the attack angle.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
It should be noted that all the directional indicators (such as upper, lower, left, right, front and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the motion situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
In the description of the embodiments, the terms "disposed," "connected," and the like are to be construed broadly unless otherwise explicitly specified or limited. For example, the connection can be fixed, detachable or integrated; can be mechanically or electrically connected; either directly or through an intervening medium, or through internal communication between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the descriptions related to "first", "second", etc. in the present invention are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit ly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature.
The high lift-drag ratio low speed unmanned aerial vehicle wing section uses the vertical line passing through the left end point of the wing section as Y axis, uses the horizontal line passing through the left end point of the wing section as X axis, and the expressions of the upper edge curve and the lower edge curve of the wing section are respectively
Wherein,
x is the abscissa, yUIs the ordinate of the upper arc, yLIs the ordinate of the lower arc;
Auifrom i to 0 to i to 5 are-0.22573, -0.27045, -0.30945, -0.28817, -0.33337 and-0.29560 in sequence, and AliFrom i-0 to i-5, in the order-0.13119, -0.01689, -0.03217, -0.04308, 0.00361, 0.10598, the trailing edge thickness Δ ξU＝ΔξL. 0.00135 is taken.
According to the above formula, the airfoil upper edge curve coordinate points include:
the 1 st coordinate point, X is 0.00000 and Y is 0.00000; the 2 nd coordinate point, X ═ 0.00080, Y ═ 0.00796; the 3 rd coordinate point, X-0.00720, Y-0.01964; the 4 th coordinate point, X-0.01920, Y-0.03120; the 5 th coordinate point, X-0.03677, Y-0.04298; the 6 th coordinate point, X-0.05968, Y-0.05471; the 7 th coordinate point, X-0.08780, Y-0.06610; the 8 th coordinate point, X-0.12080, Y-0.07686; the 9 th coordinate point, X-0.15830, Y-0.08667; the 10 th coordinate point, X-0.19988, Y-0.09520; the 11 th coordinate point, X-0.24502, Y-0.10209; the 12 th coordinate point, X-0.29315, Y-0.10705; the 13 th coordinate point, X-0.34367, Y-0.10987; the 14 th coordinate point, X-0.39590, Y-0.11035; the 15 th coordinate point, X-0.44840, Y-0.10876; the 16 th coordinate point, X-0.50132, Y-0.10553; the 17 th coordinate point, X-0.55413, Y-0.10066; the 18 th coordinate point, X-0.60627, Y-0.09416; the 19 th coordinate point, X-0.65710, Y-0.08620; the 20 th coordinate point, X-0.70608, Y-0.07713; the 21 st coordinate point, X-0.75272, Y-0.06732; the 22 nd coordinate point, X-0.79647, Y-0.05723; the 23 rd coordinate point, X-0.83690, Y-0.04720; the 24 th coordinate point, X-0.87357, Y-0.03760; the 25 th coordinate point, X-0.90615, Y-0.02868; the 26 th coordinate point, X-0.93423, Y-0.02075; the 27 th coordinate point, X-0.95760, Y-0.01398; the 28 th coordinate point, X-0.97603, Y-0.00855; the 29 th coordinate point, X-0.98930, Y-0.00459; the 30 th coordinate point, X-0.99732, Y-0.00217; the 31 st coordinate point, X is 1.00000 and Y is 0.00135;
according to the formula, the curve coordinate points of the lower edge of the airfoil comprise:
the 1 st coordinate point, X is 0.00000 and Y is 0.00000; the 2 nd coordinate point, X ═ 0.00467, Y ═ 0.00916; the 3 rd coordinate point, X-0.01467, Y-0.01518; the 4 th coordinate point, X-0.02973, Y-0.01938; the 5 th coordinate point, X-0.04970, Y-0.02219; the 6 th coordinate point, X-0.07428, Y-0.02379; the 7 th coordinate point, X-0.10317, Y-0.02428; the 8 th coordinate point, X-0.13607, Y-0.02384; the 9 th coordinate point, X-0.17257, Y-0.02269; the 10 th coordinate point, X-0.21235, Y-0.02103; the 11 th coordinate point, X-0.25498, Y-0.01905; the 12 th coordinate point, X-0.30012, Y-0.01697; the 13 th coordinate point, X-0.34730, Y-0.01502; the 14 th coordinate point, X-0.39618, Y-0.01340; the 15 th coordinate point, X-0.44707, Y-0.01192; the 16 th coordinate point, X-0.49868, Y-0.01019; the 17 th coordinate point, X-0.55040, Y-0.00815; the 18 th coordinate point, X-0.60167, Y-0.00573; the 19 th coordinate point, X-0.65193, Y-0.00313; the 20 th coordinate point, X-0.70065, Y-0.00062; the 21 st coordinate point, X-0.74728, Y-0.00157; the 22 nd coordinate point, X-0.79130, Y-0.00327; the 23 rd coordinate point, X-0.83223, Y-0.00432; the 24 th coordinate point, X-0.86957, Y-0.00468; the 25 th coordinate point, X-0.90288, Y-0.00439; the 26 th coordinate point, X-0.93180, Y-0.00356; the 27 th coordinate point, X-0.95593, Y-0.00238; the 28 th coordinate point, X-0.97503, Y-0.00105; the 29 th coordinate point, X-0.98883, Y-0.00021; the 30 th coordinate point, X-0.99722, Y-0.00107; the 31 st coordinate point, X ═ 1.00000, and Y ═ 0.00135. The shape graph drawn according to the coordinate points is shown in fig. 1.
As shown in figure 1, the wing of the utility model is round-head tip-tail, the radius r of the front edge of the head is 0.01537m, and the chord length c is 1 m. The maximum relative thickness t/c of the airfoil is 12.45 percent of chord length, and the position x of the maximum relative thicknesstAt 34.73% chord length, the maximum relative curvature f/c is 4.82% chord length, and the maximum relative curvature position xfAt 39.62% chord length. As shown in fig. 2, the maximum relative thickness t/c is increased from 9% to 12.45% compared to the NACA 6409 airfoil, which is a 38.18% improvement; the maximum relative camber f/c is reduced to 4.82% from 6%, and the same ratio is reduced by 19.67%, so that the wing structure design is facilitated, and the unmanned aerial vehicle is suitable for being used by long-endurance unmanned aerial vehicles with large aspect ratios.
As shown in FIG. 3, in a state of a Reynolds number of 4e 5-9 e5 in a design state, by taking the Reynolds number of 9e5 as an example, compared with the international high lift-drag ratio airfoil NACA 6409, the maximum lift coefficient can reach 1.6, the attack angle of the maximum lift coefficient is increased from 11 degrees to 14 degrees, and the unmanned aerial vehicle is favorable for improving the take-off, landing and stall performances.
As shown in fig. 4, in a state of reynolds numbers 4e 5-9 e5 in a design state, taking reynolds numbers 9e5 as an example, compared with an international high lift-drag ratio airfoil NACA 6409, lift-drag ratios of the two airfoils are similar and are both at a higher level, and the lift-drag ratio within a small incidence angle range (-1-4 °) is slightly higher than that of NACA 6409, which is beneficial to improving the unmanned aerial vehicle during sailing; meanwhile, the zero-lift pitching moment coefficient is increased from-0.1511 to-0.1318, and the zero-lift pitching moment coefficient is increased by 12.77% on the same scale, so that the pitching balancing resistance is favorably reduced, and the sailing time is improved.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention. In addition, the technical solutions between the various embodiments can be combined with each other, but must be based on the realization of those skilled in the art; when the technical solutions are contradictory or cannot be combined, the combination of the technical solutions should be considered to be absent, and is not within the protection scope of the present invention.
Claims (2)
1. A high lift-drag ratio's low-speed unmanned aerial vehicle wing section which characterized in that: the vertical line passing through the left end point of the wing profile is taken as an Y axis, the horizontal line passing through the left end point of the wing profile is taken as an X axis, and expressions of an upper edge curve and a lower edge curve of the wing profile are respectively
Wherein,
x is the abscissa, yUIs the ordinate of the upper arc, yLIs the ordinate of the lower arc;
Aui＝[-0.22573,-0.27045,-0.30945,-0.28817,-0.33337,-0.29560]，
Ali＝[-0.13119,-0.01689,-0.03217,-0.04308,0.00361,0.10598]；
trailing edge thickness Δ ξU＝ΔξL。
2. A high lift to drag ratio low speed drone airfoil according to claim 1Characterized by a trailing edge thickness delta ξU＝ΔξL＝0.00135。
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115593612A (en) * | 2022-12-15 | 2023-01-13 | 中国空气动力研究与发展中心空天技术研究所（Cn） | Self-leveling anti-stall high-performance airfoil |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115593612A (en) * | 2022-12-15 | 2023-01-13 | 中国空气动力研究与发展中心空天技术研究所（Cn） | Self-leveling anti-stall high-performance airfoil |
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