CN107757871A - A kind of small-sized fixed-wing unmanned plane aerofoil profile - Google Patents
A kind of small-sized fixed-wing unmanned plane aerofoil profile Download PDFInfo
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- CN107757871A CN107757871A CN201710852194.1A CN201710852194A CN107757871A CN 107757871 A CN107757871 A CN 107757871A CN 201710852194 A CN201710852194 A CN 201710852194A CN 107757871 A CN107757871 A CN 107757871A
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- B—PERFORMING OPERATIONS; TRANSPORTING
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Abstract
The present invention relates to a kind of small-sized fixed-wing unmanned plane aerofoil profile, relative thickness of airfoil 12%, positioned at the position of chord length 28.8%, maximum camber is 3.5%, positioned at the position of chord length 53.8%, 100mm airfoil trailing edges thickness is 0.4mm, and 100mm leading-edge radius of airfoil is 1.21mm.A kind of small-sized fixed-wing unmanned plane aerofoil profile of the present invention, its advantage is that the LRF1235 aerofoil profiles not only have good lifting resistance characteristic and stalling characteristics, and aerofoil profile has larger relative thickness and rear edge thickness, show that the present invention has good aerodynamic characteristic and engineering, have and meet application demand feature of the small-sized fixed-wing unmanned plane to high-lift, high lift-drag ratio, high stall angle and maximum lift coefficient, big relative thickness.
Description
Technical field
It is a kind of there is good low-to-medium altitude aeroperformance the present invention relates to a kind of small-sized fixed-wing unmanned plane aerofoil profile
The big thickness aerofoil profile (LRF1235) of low reynolds number, for substituting the traditional aviation wing used in small-sized fixed-wing unmanned aerial vehicle design
Type, the endurance and stall performance of small-sized fixed-wing unmanned plane can be significantly improved, belongs to unmanned aerial vehicle design technical applications.
Background technology
Compared with routinely having man-machine and medium-and-large-sized unmanned plane, small-sized fixed-wing unmanned plane is in terms of pneumatic design and assessment
With particularity.Small-sized fixed-wing unmanned plane has the characteristics that flying height is low, flying speed is slow, flight Reynolds number is low.Gently
The cruising flight Reynolds number of small-sized fixed-wing unmanned plane is 100,000-70 ten thousand, it may appear that the low reynolds number effect such as laminar flow separation, it is and normal
Rule have man-machine and medium-and-large-sized unmanned plane to have significant difference.In addition many small-sized unmanned planes are by the way of stall recovery, nothing
The angle of attack is larger during man-machine recovery, requires higher to the big angle of attack stalling characteristics of unmanned plane.
The aeroperformance of small-sized fixed-wing unmanned plane depends on the aerofoil profile that wing design and its section use.It is small-sized solid
The wing design for determining wing unmanned plane selects traditional classical aviation aerofoil profile mostly, the main NACA aerofoil profiles including the U.S., Clark-Y
Gottinggen aerofoil profiles of aerofoil profile, the RAF aerofoil profiles of Britain and Germany etc..Above-mentioned aerofoil profile uses under the conditions of low reynolds number, nobody
Big angle of attack stalling characteristics when lifting resistance characteristic of the machine under Cruise Conditions and landing are all less desirable, are unfavorable for improving unmanned plane
Performance.Such as typical NACA4412 aerofoil profiles maximum lift-drag ratio K when Reynolds number is 650,000 is 60, maximum lift coefficient CL is
1.39, lift-drag ratio K is 51.8 when Reynolds number is 270,000, and maximum lift coefficient CL is 1.52.
It is smaller to there is aircraft lift-drag ratio mostly using the small-sized fixed-wing unmanned plane of traditional classical aviation aerofoil profile at present,
Maximum available lift is limited, and big angle of attack stalling characteristics are poor, flight endurance is limited, landing distance is longer and can not be effectively using mistake
The shortcomings of speed recovery.
The content of the invention
It is an object of the invention to provide a kind of small-sized fixed-wing unmanned plane aerofoil profile, with suitable for small-sized fixed-wing without
Man-machine low speed, low reynolds number, big thickness aerofoil profile so that unmanned plane has good low reynolds number aerodynamic characteristic, larger
Being cruised in the range of flying speed all has good lifting resistance characteristic and larger endurance, while unmanned plane has very well in landing
Stalling characteristics, the angle of attack that can be used, maximum lift coefficient are all larger, be easy to unmanned plane STOL or stall recovery.
A kind of low speed of small-sized fixed-wing unmanned plane Airfoil Design of the present invention, low reynolds number, big thickness aerofoil profile title
For LRF1235.The innovative point of the present invention is the flight characteristic for having taken into full account small-sized fixed-wing unmanned plane, is directed to
Property the design of low reynolds number characteristic, effective control has been carried out to the laminar flow separation of aerofoil profile.
A kind of small-sized fixed-wing unmanned plane aerofoil profile of the present invention, relative thickness of airfoil 12%, positioned at chord length 28.8%
Position, maximum camber 3.5%, positioned at the position of chord length 53.8%, 100mm airfoil trailing edges thickness is 0.4mm, before 100mm aerofoil profiles
Edge radius is 1.21mm.
Wherein, described aerofoil profile parameter is as follows：Two groups of x, y values are x1、y1And x2、y2Two-dimensional coordinate system is represented respectively
Airfoil upper and lower surface discrete point coordinate value；
Wherein, aerofoil profile upper surface x1, y1 value 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)；
Wherein, aerofoil profile lower surface x2, y2 value are as follows：(0.00000,0.00000), (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).
Wherein, described aerofoil profile Reynolds number RE is 270,000, and maximum lift coefficient CL is more than 1.65, and maximum lift-drag ratio K is more than
60, there is the lift-drag ratio not less than 50 in 8 degree of conversion range of angle of attack.
A kind of small-sized fixed-wing unmanned plane aerofoil profile LRF1235 aeroperformance curve such as Fig. 2 and Fig. 3 institutes of the present invention
Show.It can be seen that compared with traditional aviation aerofoil profile, using the small-sized fixed-wing unmanned plane of the present invention 100,000-70
In the range of ten thousand flight Reynolds numbers, the maximum lift-drag ratio of aerofoil profile is that (8 °) all have in large angles of attack excursion near 5 °~6 °
There is larger lift-drag ratio.Maximum lift-drag ratio K improves about 16%, and maximum lift coefficient CL improves about 11%, and stall angle improves about 1
Degree.There is more preferable aerodynamic characteristic using the unmanned plane of aerofoil profile of the present invention, adapt to larger flying speed scope and larger flight
Height change, there is longer endurance and shorter landing distance, safer way of recycling.
A kind of small-sized fixed-wing unmanned plane aerofoil profile of the present invention, its advantage are that the LRF1235 aerofoil profiles not only have well
Lifting resistance characteristic and stalling characteristics, and aerofoil profile has larger relative thickness and rear edge thickness, and it is good to show that the present invention has
Aerodynamic characteristic and engineering, have and meet small-sized fixed-wing unmanned plane to high-lift, high lift-drag ratio, high stall angle and most
Rise higher the application demand feature of force coefficient, big relative thickness.
Brief description of the drawings
Fig. 1 is a kind of small-sized fixed-wing unmanned plane aerofoil profile LRF1235 of the present invention.
Fig. 2 is the aerofoil profile LRF1235 of the present invention and the lift coefficient of classical traditional airfoil with angle of attack variation contrast curve.
Fig. 3 is that the aerofoil profile LRF1235 of the present invention changes contrast curve with the lift-drag ratio of classical traditional airfoil with lift coefficient.
Fig. 4 a, b are the aerofoil profile LRF1235 of the application present invention small-sized fixed-wing aerial survey unmanned aerial vehicle platform of 4kg hand throwing types.
Symbol description is as follows in Fig. 4
1 propeller, 2 fuselages, 3 wings, 4 empennages, A-A sections are LRF1235 aerofoil profiles
Embodiment
With reference to the accompanying drawings and examples, technical scheme is described further.
The aerofoil profile is had been used in the optimization design of certain small-sized fixed-wing unmanned plane of 4kg hand throwing types shown in Fig. 4 at present, boat
Shi Tigao about 10%.See Fig. 4, the present invention is a kind of low reynolds number wing for the design of small-sized fixed-wing unmanned aerial vehicle platform wing
Type.The unmanned aerial vehicle platform comprises at least propeller 1, fuselage 2, wing 3 and empennage 4；Wherein unmanned aerial vehicle platform wing 3 is extended to not
Aerofoil profile LRF1235 shown in Fig. 1 of the present invention is used with profile position, each section aerofoil profile uses phase according to wing aerodynamic design requirement
The local established angle and torsion angle answered, then each section is extended to stretching and generates wing, form the main load portion of unmanned plane
Part, and be to influence unmanned plane lifting resistance characteristic and the critical piece of stalling characteristics.
The unmanned aerial vehicle platform captain 1.28m, span 2.4m, maximum take-off weight 4kg, maximum mission payload 1kg, cruise
Flying speed 15m/s, flying height 500m, cruising flight Reynolds number about 200,000, cruising time 90min, power is genemotor.
Aerofoil profile LRF1235, relative thickness 12%, positioned at the position of chord length 28.8%, maximum camber 3.5%, it is located at
The position of chord length 53.8%, 100mm airfoil trailing edges thickness are 0.4mm, and 100mm leading-edge radius of airfoil is 1.21mm.The aerofoil profiles
As shown in Figure 1.Aerofoil profile parameter is as shown in table 1 below.Two groups of x, y are x in table1、y1And x2、y2Value represents two-dimensional coordinate respectively
It is Airfoil upper and lower surface discrete point coordinate value.
Table 1
Aerofoil profile LRF1235 is a kind of aerofoil profile exclusively for small-sized fixed-wing unmanned aerial vehicle design, effectively improves aerofoil profile
The characteristics of low reynolds number laminar flow separation, lift-drag ratio and maximum lift coefficient are improved, improve the stalling characteristics of unmanned plane, solved
Smaller, the maximum available lift that aircraft lift-drag ratio mostly be present using the small-sized fixed-wing unmanned plane of traditional typical airline aerofoil profile
Limited, big angle of attack stalling characteristics are poor, flight endurance is limited, landing distance is longer, it is impossible to the shortcomings that effectively being reclaimed using stall.
Claims (3)
- A kind of 1. small-sized fixed-wing unmanned plane aerofoil profile, it is characterised in that：The relative thickness of airfoil is 12%, positioned at chord length 28.8% position, maximum camber 3.5%, positioned at the position of chord length 53.8%, 100mm airfoil trailing edges thickness is 0.4mm, 100mm Leading-edge radius of airfoil is 1.21mm.
- A kind of 2. small-sized fixed-wing unmanned plane aerofoil profile according to claim 1, it is characterised in that：Described aerofoil profile is cutd open Face parameter is as follows：Two groups of x, y values are x1、y1And x2、y2Two-dimensional coordinate system Airfoil upper and lower surface discrete point is represented respectively Coordinate value；Wherein, aerofoil profile upper surface x1, y1 value 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)；Wherein, aerofoil profile lower surface x2, y2 value are as follows：(0.00000,0.00000), (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).
- A kind of 3. small-sized fixed-wing unmanned plane aerofoil profile according to claim 1 or 2, it is characterised in that：The described wing Type Reynolds number RE is 270,000, and maximum lift coefficient CL is more than 1.65, and maximum lift-drag ratio K is more than 60, in 8 degree of conversion range of angle of attack With the lift-drag ratio not less than 50.
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| CN110498037A (en) * | 2019-08-22 | 2019-11-26 | 西安探索鹰航空科技有限公司 | A kind of high lift-drag ratio laminar flow airfoil suitable for low-altitude low-speed unmanned plane |
| CN111348175A (en) * | 2020-01-13 | 2020-06-30 | 北京航空航天大学 | Special airfoil profile matched with high-universality large-loading small-sized unmanned aerial vehicle |
| 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 |
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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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| CN111348175A (en) * | 2020-01-13 | 2020-06-30 | 北京航空航天大学 | Special airfoil profile matched with high-universality large-loading small-sized unmanned aerial vehicle |
| 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 |
| 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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