CN107757871B - Airfoil profile for light and small fixed wing unmanned aerial vehicle - Google Patents
Airfoil profile for light and small fixed wing unmanned aerial vehicle Download PDFInfo
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Abstract
The invention relates to a wing profile for a light and small fixed wing unmanned aerial vehicle, wherein the relative thickness of the wing profile is 12%, the wing profile is positioned at the position of 28.8% of the chord length, the maximum camber is 3.5%, the wing profile is positioned at the position of 53.8% of the chord length, the thickness of the rear edge of the wing profile with 100mm is 0.4mm, and the radius of the front edge of the wing profile with 100mm is 1.21mm. The LRF1235 airfoil for the light and small fixed-wing unmanned aerial vehicle has the advantages that the airfoil not only has good lift-drag characteristic and stall characteristic, but also has larger relative thickness and trailing edge thickness, which shows that the airfoil has good aerodynamic characteristic and engineering property, and has the characteristics of meeting the application requirements of the light and small fixed-wing unmanned aerial vehicle on high lift force, high lift-drag ratio, high stall attack angle, maximum lift coefficient and large relative thickness.
Description
Technical Field
The invention relates to a wing profile for a light and small fixed wing unmanned aerial vehicle, which is a low-Reynolds number large-thickness wing profile (LRF 1235) with good middle-low aerodynamic performance, is used for replacing the traditional aviation wing profile used in the design of the light and small fixed wing unmanned aerial vehicle, can obviously improve the endurance and stall performance of the light and small fixed wing unmanned aerial vehicle, and belongs to the technical application field of unmanned aerial vehicle design.
Background
Compared with the conventional unmanned aerial vehicle and the medium-sized and large-sized unmanned aerial vehicle, the light and small-sized fixed wing unmanned aerial vehicle has specificity in pneumatic design and evaluation. The light and small fixed wing unmanned aerial vehicle has the characteristics of low flying height, low flying speed, low flying Reynolds number and the like. The cruising flight Reynolds number of the light and small fixed-wing unmanned aerial vehicle is 10-70 ten thousand, and low Reynolds number effects such as laminar flow separation and the like can occur, so that the light and small fixed-wing unmanned aerial vehicle has obvious differences from the conventional unmanned aerial vehicle and medium and large unmanned aerial vehicles. In addition, a stall recovery mode is adopted by a plurality of light unmanned aerial vehicles, the attack angle is large when the unmanned aerial vehicles are recovered, and the requirement on the stall characteristic of the large attack angle of the unmanned aerial vehicles is high.
The aerodynamic performance of a lightweight, small fixed wing drone depends on the wing design and the airfoil used in its profile. The design of the wings of the light and small fixed wing unmanned aerial vehicle mostly adopts traditional classical aviation wing types, and mainly comprises NACA wing types, clark-Y wing types, RAF wing types in the United kingdom, gottingen wing types in the Germany and the like. The wing profile is used under the condition of low Reynolds number, and the lift resistance characteristic and the high attack angle stall characteristic of the unmanned aerial vehicle under the condition of cruising and landing are not ideal, so that the performance of the unmanned aerial vehicle is not improved. For example, a typical NACA4412 airfoil has a maximum lift-drag ratio K of 60 at a Reynolds number of 65 ten thousand, a maximum lift-drag coefficient CL of 1.39, and a maximum lift-drag coefficient CL of 1.52 at a Reynolds number of 27 ten thousand of 51.8.
At present, most of light and small fixed wing unmanned aerial vehicles adopting traditional classical aviation wing shapes have the defects of smaller lift-drag ratio of an airplane, limited maximum available lift force, poor stall characteristic at a large attack angle, limited flight endurance, longer take-off and landing distance, incapability of effectively adopting stall recovery and the like.
Disclosure of Invention
The invention aims to provide a wing profile for a light and small fixed wing unmanned aerial vehicle, which is suitable for the wing profile with low speed, low Reynolds number and large thickness of the light and small fixed wing unmanned aerial vehicle, so that the unmanned aerial vehicle has good low Reynolds number pneumatic characteristics, cruises in a larger flying speed range and has good lift resistance characteristics and larger endurance, and meanwhile, the unmanned aerial vehicle has good stall characteristics in the process of taking off and landing, and the attack angle and the maximum lift coefficient which can be used are larger, thereby being convenient for the short-distance taking off and landing or stall recovery of the unmanned aerial vehicle.
The invention discloses a low-speed, low-Reynolds number and large-thickness airfoil designed for a light and small fixed-wing unmanned aerial vehicle, which is named as LRF1235. The invention has the innovation point that the flight characteristics of the light and small fixed wing unmanned aerial vehicle are fully considered, the specific low-Reynolds number characteristic design is carried out, and the laminar flow separation of the wing profile is effectively controlled.
The invention relates to a wing profile for a light and small fixed wing unmanned aerial vehicle, wherein the relative thickness of the wing profile is 12%, the wing profile is positioned at the position of 28.8% of the chord length, the maximum camber is 3.5%, the wing profile is positioned at the position of 53.8% of the chord length, the thickness of the rear edge of the wing profile with 100mm is 0.4mm, and the radius of the front edge of the wing profile with 100mm is 1.21mm.
Wherein, the airfoil profile parameters are as follows: two sets of x, y values, i.e. x 1 、y 1 X is a group 2 、y 2 Respectively representing the coordinate values of discrete points on the upper surface and the lower surface of the lower airfoil of the two-dimensional coordinate system;
the values of the upper surfaces x1 and y1 of the wing profile are as follows: (1.00000,0.00200), (0.99042,0.00449), (0.96898,0.00974), (0.93378,0.01751), (0.91482,0.02134), (0.89529,0.02511), (0.87554,0.02882), (0.85563,0.03249), (0.83559,0.03613), (0.81545,0.03975), (0.79542,0.04330), (0.77537,0.04680), (0.75527,0.05026), (0.73531,0.05364), (0.71535,0.05695), (0.69547,0.06017), (0.67566,0.06328), (0.65593,0.06626), (0.63623,0.06911), (0.61660,0.07181), (0.59702,0.07435), (0.57749,0.07672), (0.55793,0.07893), (0.53842,0.08096), (0.51904,0.08279), (0.49950,0.08445), (0.48011,0.08590), (0.46075,0.08715), (0.44138,0.08820), (0.42170,0.08905), (0.40243,0.08967), (0.38340,0.09007), (0.36200,0.09025), (0.34540,0.09019), (0.32570,0.08989), (0.30631,0.08932), (0.28780,0.08850), (0.26880,0.08737), (0.25013,0.08597), (0.23131,0.08425), (0.21298,0.08225), (0.19465,0.07990), (0.17660,0.07722), (0.15874,0.07418), (0.14120,0.07078), (0.12406,0.06702), (0.10743,0.06290), (0.09154,0.05845), 0.03944 (0.03270,0.03504), (0.02588,0.03095), (0.02035,0.02716), (0.01582,0.02362), (0.01212,0.02034), (0.00908,0.01727), (0.00659,0.01441), (0.00454,0.01172), (0.00288,0.00917), (0.00158,0.00671), (0.00069,0.00440), (0.00015,0.00207);
the values of the lower surfaces x2 and y2 of the wing profile are as follows: (0.00000), (0.00025, -0.00234), (0.00095, -0.00454), (0.00204, -0.00657), (0.00371, -0.00872), (0.00575, -0.01067), (0.00827, -0.01257), (0.01126, -0.01439), (0.01479, -0.01615), (0.01897, -0.01787), (0.02401, -0.01955), (0.03005, -0.02119), (0.03752, -0.02285), (0.02285), -0.02285), (0.02285, -0.02285), (0.02285, -0.01862), (0.02285, -0.01667), (0.02285, -0.02285), a metal oxide film, (0.55872-0.00857), (0.57904-0.00653), (0.59950-0.00449), (0.61967-0.00251), (0.63976-0.00058), (0.65990,0.00128), (0.67967,0.00301), (0.69961,0.00464), (0.71930,0.00612), (0.73896,0.00744), (0.75850,0.00857), (0.77785,0.00950), (0.79730,0.01023), (0.81643,0.01072), (0.83510,0.01096), (0.85457,0.01095), (0.87322,0.01067), (0.89202,0.01010), (0.91015,0.00921), (0.92813,0.00793), (0.94574,0.00625), (0.96200,0.00428), (0.97698,0.00208), (0.99040-0.00020), (1.00000-0.00200).
The wing type Reynolds number RE is 27 ten thousand, the maximum lift coefficient CL is greater than 1.65, the maximum lift-drag ratio K is greater than 60, and the wing type Reynolds number RE has the lift-drag ratio not lower than 50 in the range of 8-degree attack angle variation.
The aerodynamic performance curves of the wing type LRF1235 for the light and small fixed wing unmanned aerial vehicle are shown in fig. 2 and 3. As can be seen from the graph, compared with the traditional aviation wing section, the light and small fixed wing unmanned aerial vehicle adopting the invention has the maximum lift-drag ratio of 5-6 degrees in the range of 10-70 thousands of flying Reynolds numbers, and has larger lift-drag ratio in the larger attack angle variation range (8 degrees). The maximum lift-drag ratio K increases by about 16%, the maximum lift coefficient CL increases by about 11%, and the stall angle of attack increases by about 1 degree. The unmanned aerial vehicle using the wing profile has better aerodynamic characteristics, is suitable for a larger flying speed range and a larger flying height change, and has longer endurance, shorter take-off and landing distance and safer recovery mode.
The LRF1235 airfoil for the light and small fixed-wing unmanned aerial vehicle has the advantages that the airfoil not only has good lift-drag characteristic and stall characteristic, but also has larger relative thickness and trailing edge thickness, which shows that the airfoil has good aerodynamic characteristic and engineering property, and has the characteristics of meeting the application requirements of the light and small fixed-wing unmanned aerial vehicle on high lift force, high lift-drag ratio, high stall attack angle, maximum lift coefficient and large relative thickness.
Drawings
Fig. 1 is a light and small-sized wing shape LRF1235 for a fixed wing unmanned aerial vehicle according to the present invention.
FIG. 2 is a graph comparing lift coefficient as a function of angle of attack for an airfoil of the invention LRF1235 with a classical conventional airfoil.
Fig. 3 is a graph comparing lift-drag ratio of the airfoil LRF1235 of the present invention to a classical conventional airfoil as a function of lift coefficient.
Fig. 4a and b show a 4kg hand-thrown light and small fixed wing aerodynamics unmanned aerial vehicle platform with the wing type LRF1235 of the present invention.
The symbols in FIG. 4 are as follows
1 propeller, 2 fuselage, 3 wings, 4 tail wing, A-A section is LRF1235 airfoil
Detailed Description
The technical scheme of the invention is further described below with reference to the accompanying drawings and examples.
The wing profile is used in the optimal design of a certain 4kg hand-thrown light small fixed wing unmanned aerial vehicle shown in fig. 4, and the endurance is improved by about 10%. Referring to fig. 4, the invention is a low reynolds number airfoil for a lightweight small fixed wing unmanned aerial vehicle platform wing design. The unmanned aerial vehicle platform at least comprises a propeller 1, a fuselage 2, wings 3 and a tail wing 4; the wing profile LRF1235 shown in the figure 1 is used in different section positions of the unmanned aerial vehicle platform wing 3 along the spanwise direction, each section wing profile uses a corresponding local installation angle and torsion angle according to the aerodynamic design requirement of the wing, and each section is stretched along the spanwise direction to generate the wing, so that a main bearing component of the unmanned aerial vehicle is formed, and the main component is a main component affecting the lifting resistance characteristic and the stall characteristic of the unmanned aerial vehicle.
The unmanned aerial vehicle platform has a length of 1.28m, a wingspan of 2.4m, a maximum take-off weight of 4kg, a maximum mission load of 1kg, a cruising flying speed of 15m/s, a flying height of 500m, a cruising flying Reynolds number of about 20 ten thousand, a duration of 90min and a power of an electric engine.
The airfoil LRF1235 has a relative thickness of 12%, a maximum camber of 3.5% at 28.8% chord length, a trailing edge thickness of 0.4mm at 100mm and a leading edge radius of 1.21mm at 53.8% chord length. The airfoil profile is shown in fig. 1. The airfoil profile parameters are shown in table 1 below. Two groups of x, y in the table are x 1 、y 1 X is a group 2 、y 2 The values represent discrete point coordinate values of the upper surface and the lower surface of the airfoil under the two-dimensional coordinate system respectively.
TABLE 1
The airfoil LRF1235 is specially designed for the light and small fixed-wing unmanned aerial vehicle, effectively improves the characteristics of low-Reynolds-number laminar flow separation of the airfoil, improves the lift-drag ratio and the maximum lift coefficient, improves the stall characteristic of the unmanned aerial vehicle, and solves the defects that the light and small fixed-wing unmanned aerial vehicle adopting the traditional typical aviation airfoil mostly has smaller lift-drag ratio of an airplane, limited maximum available lift, poor stall characteristic at a large attack angle, limited flight endurance and longer take-off and landing distance and cannot effectively adopt stall recovery.
Claims (1)
1. The utility model provides a light small-size fixed wing airfoil for unmanned aerial vehicle which characterized in that: the airfoil has a relative thickness of 12%, a maximum camber of 3.5% at 28.8% chord length, a trailing edge thickness of 0.4mm at 53.8% chord length, and a leading edge radius of 1.21mm at 100 mm;
the airfoil profile parameters are as follows: two sets of x, y values, i.e. x 1 、y 1 X is a group 2 、y 2 Respectively representing the coordinate values of discrete points on the upper surface and the lower surface of the lower airfoil of the two-dimensional coordinate system;
the values of the upper surfaces x1 and y1 of the wing profile are as follows: (1.00000,0.00200), (0.99042,0.00449), (0.96898,0.00974), (0.93378,0.01751), (0.91482,0.02134), (0.89529,0.02511),
（0.87554，0.02882）、（0.85563，0.03249）、（0.83559，0.03613）、（0.81545，0.03975）、
（0.79542，0.04330）、（0.77537，0.04680）、（0.75527，0.05026）、（0.73531，0.05364）、
（0.71535，0.05695）、（0.69547，0.06017）、（0.67566，0.06328）、（0.65593，0.06626）、
（0.63623，0.06911）、（0.61660，0.07181）、（0.59702，0.07435）、（0.57749，0.07672）、
（0.55793，0.07893）、（0.53842，0.08096）、（0.51904，0.08279）、（0.49950，0.08445）、
（0.48011，0.08590）、（0.46075，0.08715）、（0.44138，0.08820）、（0.42170，0.08905）、
（0.40243，0.08967）、（0.38340，0.09007）、（0.36200，0.09025）、（0.34540，0.09019）、
（0.32570，0.08989）、（0.30631，0.08932）、（0.28780，0.08850）、（0.26880，0.08737）、
（0.25013，0.08597）、（0.23131，0.08425）、（0.21298，0.08225）、（0.19465，0.07990）、
（0.17660，0.07722）、（0.15874，0.07418）、（0.14120，0.07078）、（0.12406，0.06702）、
（0.10743，0.06290）、（0.09154，0.05845）、（0.07661，0.05373）、（0.06303，0.04888）、
（0.05113，0.04407）、（0.04107，0.03944）、（0.03270，0.03504）、（0.02588，0.03095）、
（0.02035，0.02716）、（0.01582，0.02362）、（0.01212，0.02034）、（0.00908，0.01727）、
（0.00659，0.01441）、（0.00454，0.01172）、（0.00288，0.00917）、（0.00158，0.00671）、
（0.00069，0.00440）、（0.00015，0.00207）；
The values of the lower surfaces x2 and y2 of the wing profile are as follows: (0.00000), (0.00025, -0.00234),
（0.00095，-0.00454）、（0.00204，-0.00657）、（0.00371，-0.00872）、（0.00575，-0.01067）、
（0.00827，-0.01257）、（0.01126，-0.01439）、（0.01479，-0.01615）、（0.01897，-0.01787）、
（0.02401，-0.01955）、（0.03005，-0.02119）、（0.03752，-0.02285）、（0.04679，-0.02451）、
（0.05827，-0.02616）、（0.07221，-0.02779）、（0.08819，-0.02931）、（0.10566，-0.03063）、
（0.12401，-0.03171）、（0.14275，-0.03254）、（0.16187，-0.03313）、（0.18060，-0.03347）、
（0.20030，-0.03359）、（0.21940，-0.03349）、（0.23900，-0.03317）、（0.25840，-0.03265）、
（0.27786，-0.03193）、（0.29753，-0.03101）、（0.31697，-0.02993）、（0.33680，-0.02867）、
（0.35649，-0.02728）、（0.37651、-0.02574）、（0.39647，-0.02410）、（0.41651，-0.02236）、
（0.43663，-0.02053）、（0.45693，-0.01862）、（0.47721，-0.01667）、（0.49750，-0.01469）、
（0.51781，-0.01268）、（0.53826，-0.01063）、（0.55872，-0.00857）、（0.57904，-0.00653）、
（0.59950，-0.00449）、（0.61967，-0.00251）、（0.63976，-0.00058）、（0.65990，0.00128）、
（0.67967，0.00301）、（0.69961，0.00464）、（0.71930，0.00612）、（0.73896，0.00744）、
（0.75850，0.00857）、（0.77785，0.00950）、（0.79730，0.01023）、（0.81643，0.01072）、
（0.83510，0.01096）、（0.85457，0.01095）、（0.87322，0.01067）、（0.89202，0.01010）、
（0.91015，0.00921）、（0.92813，0.00793）、（0.94574，0.00625）、（0.96200，0.00428）、
（0.97698，0.00208）、（0.99040，-0.00020）、（1.00000，-0.00200）；
The wing type Reynolds number RE is 27 ten thousand, the maximum lift coefficient CL is greater than 1.65, the maximum lift-drag ratio K is greater than 60, and the wing type Reynolds number RE has the lift-drag ratio not lower than 50 in the range of 8-degree attack angle variation.
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| CN110498037B (en) * | 2019-08-22 | 2020-09-08 | 西安探索鹰航空科技有限公司 | High lift-drag ratio laminar flow wing section suitable for low-altitude low-speed unmanned aerial vehicle |
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| CN111498084A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | Low-resistance laminar flow airfoil applied to high-altitude high-speed long-endurance unmanned aerial vehicle |
| CN115593612B (en) * | 2022-12-15 | 2023-04-25 | 中国空气动力研究与发展中心空天技术研究所 | Self-balancing stall-resistant high-performance airfoil |
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