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
- Publication number
- 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
- Authority
- CN
- China
- Prior art keywords
- aerofoil profile
- unmanned plane
- small
- wing unmanned
- sized fixed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000006243 chemical reaction Methods 0.000 claims description 2
- 238000011084 recovery Methods 0.000 description 4
- 238000000926 separation method Methods 0.000 description 3
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical compound CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 description 1
- 241000985905 Candidatus Phytoplasma solani Species 0.000 description 1
- 241001669680 Dormitator maculatus Species 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Wind Motors (AREA)
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710852194.1A CN107757871B (en) | 2017-09-20 | 2017-09-20 | Airfoil profile for light and small fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710852194.1A CN107757871B (en) | 2017-09-20 | 2017-09-20 | Airfoil profile for light and small fixed wing unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107757871A true CN107757871A (en) | 2018-03-06 |
| CN107757871B CN107757871B (en) | 2023-11-28 |
Family
ID=61266147
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710852194.1A Active CN107757871B (en) | 2017-09-20 | 2017-09-20 | Airfoil profile for light and small fixed wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107757871B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110386243A (en) * | 2019-07-22 | 2019-10-29 | 北京耐威科技股份有限公司 | A kind of low-speed unmanned aerial vehicle aerofoil profile of high lift-drag ratio |
| 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 |
| WO2021109441A1 (en) * | 2019-12-06 | 2021-06-10 | 北京二郎神科技有限公司 | Rotor wing of rotorcraft and rotorcraft |
| 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 |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB605765A (en) * | 1946-01-04 | 1948-07-29 | Norman Kenneth Walker | Improvements in or relating to aerofoil sections for low reynolds numbers |
| US20080283674A1 (en) * | 2007-01-08 | 2008-11-20 | Israel Aerospace Industries Ltd. | Low-drag swept wings |
| US20110262281A1 (en) * | 2008-10-23 | 2011-10-27 | Repower Systems Ag | Profile of a rotor blade and rotor blade of a wind power plant |
| CN103482054A (en) * | 2013-08-14 | 2014-01-01 | 西北工业大学 | Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle |
| CN104118556A (en) * | 2014-08-07 | 2014-10-29 | 西北工业大学 | Special spoon-shaped wing section with ultra-low Reynolds number, high lift-drag ratio and low speed |
| CN104354850A (en) * | 2014-10-30 | 2015-02-18 | 中国人民解放军空军航空大学 | Airfoil profile of airfoil of high-altitude long-endurance fixed-wing aircraft |
| CN104691739A (en) * | 2015-03-11 | 2015-06-10 | 西北工业大学 | High-lift-force laminar flow aerofoil profile with low-resistance and high-drag-divergence Mach number |
| CN105351248A (en) * | 2015-12-17 | 2016-02-24 | 新昌县三新空调风机有限公司 | High-performance airfoil for fan |
| US20160137288A1 (en) * | 2013-06-10 | 2016-05-19 | Israel Aerospace Industries Ltd. | Aerofoil and wings for air vehicles |
| CN105691596A (en) * | 2016-03-10 | 2016-06-22 | 中国航天空气动力技术研究院 | High-altitude propeller with like-triangular layout |
| CN105752314A (en) * | 2016-03-22 | 2016-07-13 | 西北工业大学 | High-altitude, low-speed and high-lift natural laminar flow airfoil |
| CN105781904A (en) * | 2016-03-22 | 2016-07-20 | 西北工业大学 | 30% thickness aerofoil suitable for megawatt-grade wind turbine blade |
| CN106089569A (en) * | 2016-07-20 | 2016-11-09 | 湘潭大学 | A kind of Miniature Wind Turbine Blades aerofoil profile being applicable to low reynolds number flow |
| CN207482179U (en) * | 2017-09-20 | 2018-06-12 | 中国水利水电科学研究院 | A kind of small-sized fixed-wing unmanned plane aerofoil profile |
-
2017
- 2017-09-20 CN CN201710852194.1A patent/CN107757871B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB605765A (en) * | 1946-01-04 | 1948-07-29 | Norman Kenneth Walker | Improvements in or relating to aerofoil sections for low reynolds numbers |
| US20080283674A1 (en) * | 2007-01-08 | 2008-11-20 | Israel Aerospace Industries Ltd. | Low-drag swept wings |
| US20110262281A1 (en) * | 2008-10-23 | 2011-10-27 | Repower Systems Ag | Profile of a rotor blade and rotor blade of a wind power plant |
| US20160137288A1 (en) * | 2013-06-10 | 2016-05-19 | Israel Aerospace Industries Ltd. | Aerofoil and wings for air vehicles |
| CN103482054A (en) * | 2013-08-14 | 2014-01-01 | 西北工业大学 | Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle |
| CN104118556A (en) * | 2014-08-07 | 2014-10-29 | 西北工业大学 | Special spoon-shaped wing section with ultra-low Reynolds number, high lift-drag ratio and low speed |
| CN104354850A (en) * | 2014-10-30 | 2015-02-18 | 中国人民解放军空军航空大学 | Airfoil profile of airfoil of high-altitude long-endurance fixed-wing aircraft |
| CN104691739A (en) * | 2015-03-11 | 2015-06-10 | 西北工业大学 | High-lift-force laminar flow aerofoil profile with low-resistance and high-drag-divergence Mach number |
| CN105351248A (en) * | 2015-12-17 | 2016-02-24 | 新昌县三新空调风机有限公司 | High-performance airfoil for fan |
| CN105691596A (en) * | 2016-03-10 | 2016-06-22 | 中国航天空气动力技术研究院 | High-altitude propeller with like-triangular layout |
| CN105752314A (en) * | 2016-03-22 | 2016-07-13 | 西北工业大学 | High-altitude, low-speed and high-lift natural laminar flow airfoil |
| CN105781904A (en) * | 2016-03-22 | 2016-07-20 | 西北工业大学 | 30% thickness aerofoil suitable for megawatt-grade wind turbine blade |
| CN106089569A (en) * | 2016-07-20 | 2016-11-09 | 湘潭大学 | A kind of Miniature Wind Turbine Blades aerofoil profile being applicable to low reynolds number flow |
| CN207482179U (en) * | 2017-09-20 | 2018-06-12 | 中国水利水电科学研究院 | A kind of small-sized fixed-wing unmanned plane aerofoil profile |
Non-Patent Citations (2)
| Title |
|---|
| 程春晓;李道春;向锦武;石庆华;: "柔性后缘可变形机翼气动特性分析", 北京航空航天大学学报, no. 02, pages 360 - 366 * |
| 邓阳平;高正红;詹浩;: "两种椭圆翼型高速气动特性实验研究", 实验力学, vol. 1, no. 02, pages 103 - 107 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110386243A (en) * | 2019-07-22 | 2019-10-29 | 北京耐威科技股份有限公司 | A kind of low-speed unmanned aerial vehicle aerofoil profile of high lift-drag ratio |
| CN110386243B (en) * | 2019-07-22 | 2024-04-16 | 北京耐威科技股份有限公司 | High lift-drag ratio low-speed unmanned wing type |
| 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 |
| WO2021109441A1 (en) * | 2019-12-06 | 2021-06-10 | 北京二郎神科技有限公司 | Rotor wing of rotorcraft and rotorcraft |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107757871B (en) | 2023-11-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107757871A (en) | A kind of small-sized fixed-wing unmanned plane aerofoil profile | |
| US9637226B2 (en) | Split winglet system | |
| CN105752314B (en) | A kind of high-altitude low speed Natural Laminar Flow high-lift airfoil | |
| CN110498037B (en) | High lift-drag ratio laminar flow wing section suitable for low-altitude low-speed unmanned aerial vehicle | |
| CN109808913B (en) | Design method of unmanned aerial vehicle with deflectable wingtip winglet | |
| CN103482054B (en) | Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle | |
| CN107140179B (en) | A kind of tailstock formula tandem chord endurance aerodynamic configuration of aircraft | |
| US8109473B2 (en) | Slotted high lift aerofoils | |
| CN202320772U (en) | High lift device of double-aisle large-type passenger plane | |
| CN106043688A (en) | Helicopter rotor airfoil | |
| CN102826216A (en) | Aerodynamic configuration of aircraft | |
| CN108423157B (en) | Two-blade propeller suitable for tilting rotor aircraft | |
| CN111674546B (en) | Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft | |
| CN110435873A (en) | A kind of half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race cruised from trim | |
| CN115571323A (en) | Flat fusion body overall arrangement aircraft of subsonic speed | |
| CN205819561U (en) | A kind of lifting airscrew aerofoil profile | |
| CN112660381A (en) | Laminar flow control technology-based wing body fusion layout passenger plane layout method | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN207482179U (en) | A kind of small-sized fixed-wing unmanned plane aerofoil profile | |
| CN102167152B (en) | Airplane wingtip device with aligned front edge | |
| CN104192294A (en) | A wing structure and an airplane | |
| CN207902734U (en) | A kind of unmanned plane of aerodynamic arrangement | |
| CN202541831U (en) | Small wing of airplane | |
| CN202783771U (en) | Aircraft aerodynamic configuration | |
| CN102167153B (en) | Airplane wingtip device with aligned back edges |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |