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
- Publication number
- CN107757871B CN107757871B CN201710852194.1A CN201710852194A CN107757871B CN 107757871 B CN107757871 B CN 107757871B CN 201710852194 A CN201710852194 A CN 201710852194A CN 107757871 B CN107757871 B CN 107757871B
- Authority
- CN
- China
- Prior art keywords
- airfoil
- wing
- light
- small fixed
- lift
- 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.)
- Active
Links
- 238000011084 recovery Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 3
- 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
- 241001669680 Dormitator maculatus Species 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000009434 installation Methods 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
Description
技术领域Technical field
本发明涉及一种轻小型固定翼无人机用翼型，是一种具有良好中低空气动性能的低雷诺数大厚度翼型(LRF1235)，用于替代轻小型固定翼无人机设计中使用的传统航空翼型，可以显著提高轻小型固定翼无人机的航时和失速性能，属于无人机设计技术应用领域。The invention relates to an airfoil for light and small fixed-wing UAVs. It is a low Reynolds number and large thickness airfoil (LRF1235) with good medium and low aerodynamic performance. It is used to replace the airfoil used in the design of light and small fixed-wing UAVs. The traditional aviation airfoil can significantly improve the flight time and stall performance of light and small fixed-wing UAVs, which belongs to the application field of UAV design technology.
背景技术Background technique
与常规有人机及中大型无人机相比，轻小型固定翼无人机在气动设计与评估方面具有特殊性。轻小型固定翼无人机具有飞行高度低、飞行速度慢、飞行雷诺数低等特点。轻小型固定翼无人机的巡航飞行雷诺数在10万-70万，会出现层流分离等低雷诺数效应，与常规有人机和中大型无人机具有明显区别。加之很多轻小型无人机采用失速回收的方式，无人机回收时攻角较大，对无人机的大攻角失速特性要求较高。Compared with conventional manned aircraft and medium and large unmanned aerial vehicles, light and small fixed-wing unmanned aerial vehicles have special features in aerodynamic design and evaluation. Light and small fixed-wing UAVs have the characteristics of low flight altitude, slow flight speed, and low flight Reynolds number. The cruising flight Reynolds number of light and small fixed-wing UAVs is between 100,000 and 700,000, and low Reynolds number effects such as laminar separation will occur, which is significantly different from conventional manned aircraft and medium and large UAVs. In addition, many light and small UAVs adopt the stall recovery method. The angle of attack of the UAV is relatively large during recovery, and the requirements for the stall characteristics of the UAV at large angles of attack are relatively high.
轻小型固定翼无人机的气动性能取决于机翼设计及其剖面使用的翼型。轻小型固定翼无人机的机翼设计大多选用传统的经典航空翼型，主要包括美国的NACA翼型、Clark-Y翼型、英国的RAF翼型和德国的Gottinggen翼型等。上述翼型在低雷诺数条件下使用，无人机在巡航条件下的升阻特性和起降时的大攻角失速特性都不是很理想，不利于提高无人机性能。例如典型的NACA4412翼型在雷诺数为65万时最大升阻比K为60，最大升力系数CL为1.39，雷诺数为27万时升阻比K为51.8，最大升力系数CL为1.52。The aerodynamic performance of small, lightweight fixed-wing UAVs depends on the wing design and the airfoil used in its profile. The wing designs of light and small fixed-wing UAVs mostly use traditional classic aviation airfoils, including the American NACA airfoil, Clark-Y airfoil, British RAF airfoil, and German Gottinggen airfoil. The above-mentioned airfoil is used under low Reynolds number conditions. The lift-drag characteristics of the UAV under cruising conditions and the stall characteristics at large angles of attack during takeoff and landing are not very ideal, which is not conducive to improving the performance of the UAV. For example, a typical NACA4412 airfoil has a maximum lift-drag ratio K of 60 and a maximum lift coefficient CL of 1.39 when the Reynolds number is 650,000. When the Reynolds number is 270,000, the lift-drag ratio K is 51.8 and the maximum lift coefficient CL is 1.52.
目前采用传统的经典航空翼型的轻小型固定翼无人机大多存在飞机升阻比较小，最大可用升力有限，大攻角失速特性较差、飞行航时有限、起降距离较长和不能有效采用失速回收等缺点。At present, most of the light and small fixed-wing UAVs using traditional classic aviation airfoils have small lift-to-drag ratios, limited maximum available lift, poor stall characteristics at high angles of attack, limited flight duration, long take-off and landing distances, and inefficiency. Disadvantages such as stall recovery are used.
发明内容Contents of the invention
本发明的目的是提供一种轻小型固定翼无人机用翼型，以适用于轻小型固定翼无人机的低速、低雷诺数、大厚度翼型，使得无人机具有很好的低雷诺数气动特性，在较大的飞行速度范围内巡航都具有良好的升阻特性和较大的航时，同时无人机在起降时具有很好的失速特性，可以使用的攻角、最大升力系数都较大，便于无人机的短距起降或失速回收。The purpose of the present invention is to provide an airfoil for a light and small fixed-wing UAV, which is suitable for the low-speed, low Reynolds number and large-thickness airfoil of a light and small fixed-wing UAV, so that the UAV has good low-speed Reynolds number aerodynamic characteristics, it has good lift-drag characteristics and large flight time when cruising in a large flight speed range. At the same time, the UAV has good stall characteristics when taking off and landing, and the usable angle of attack, maximum The lift coefficients are all large, which facilitates short take-off and landing or stall recovery of the UAV.
本发明一种轻小型固定翼无人机用翼型设计的低速、低雷诺数、大厚度翼型名称为LRF1235。本发明的创新点在于充分考虑了轻小型固定翼无人机的飞行特点，进行了针对性低雷诺数特性设计，对翼型的层流分离进行了有效控制。The low-speed, low-Reynolds-number, and large-thickness airfoil designed for a light and small fixed-wing unmanned aerial vehicle of the present invention is named LRF1235. The innovation of this invention is that it fully considers the flight characteristics of light and small fixed-wing UAVs, carries out targeted low Reynolds number characteristic design, and effectively controls the laminar flow separation of the airfoil.
本发明一种轻小型固定翼无人机用翼型，翼型相对厚度为12％，位于弦长28.8％位置，最大弯度为3.5％，位于弦长53.8％位置，100mm翼型后缘厚度为0.4mm，100mm翼型前缘半径为1.21mm。The present invention is an airfoil for light and small fixed-wing UAVs. The relative thickness of the airfoil is 12%, located at 28.8% of the chord length. The maximum curvature is 3.5%, located at 53.8% of the chord length. The thickness of the trailing edge of the 100mm airfoil is 0.4mm, 100mm airfoil leading edge radius is 1.21mm.
其中，所述的翼型剖面参数如下：两组x、y值即x1、y1及x2、y2分别代表二维坐标系下翼型上表面和下表面离散点坐标值；Among them, the airfoil profile parameters are as follows: two sets of x and y values, namely x 1 , y 1 and x 2 , y 2 respectively represent the coordinate values of discrete points on the upper surface and lower surface of the airfoil in a two-dimensional coordinate system;
其中，翼型上表面x1、y1的取值如下：(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)；Among them, the values of x1 and y1 on the upper surface of the airfoil 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, 0.050 26), (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, 0.0 8905), (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, 0.087 37), (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, 0.0 2716), (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, 0.004 40), (0.00015, 0.00207);
其中，翼型下表面x2、y2的取值如下：(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)。Among them, the values of x2 and y2 on the lower surface of the airfoil 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, -0.021 19), (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), (0.416 51,-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), (0.558 72,-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, 0.0 1095), (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, -0.00 020), (1.00000, -0.00200).
其中，所述的翼型雷诺数RE为27万，最大升力系数CL大于1.65，最大升阻比K大于60，在8度攻角变化范围内具有不低于50的升阻比。Among them, the Reynolds number RE of the airfoil is 270,000, the maximum lift coefficient CL is greater than 1.65, the maximum lift-to-drag ratio K is greater than 60, and it has a lift-to-drag ratio of no less than 50 within an 8-degree angle of attack range.
本发明一种轻小型固定翼无人机用翼型LRF1235的气动性能曲线如图2和图3所示。从图中可以看出，与传统航空翼型相比，采用本发明的轻小型固定翼无人机在10万-70万飞行雷诺数范围内，翼型的最大升阻比为5°～6°附近，在较大攻角变化范围内(8°)都具有较大的升阻比。最大升阻比K提高约16％，最大升力系数CL提高约11％，失速攻角提高约1度。使用本发明翼型的无人机具有更好的气动特性，适应较大飞行速度范围及较大的飞行高度变化，具有更长的航时和更短起降距离，更安全的回收方式。The aerodynamic performance curves of LRF1235, a light and small fixed-wing UAV airfoil of the present invention, are shown in Figures 2 and 3. It can be seen from the figure that compared with traditional aviation airfoils, the light and small fixed-wing UAV using the present invention has a maximum lift-drag ratio of 5° to 6 in the flight Reynolds number range of 100,000-700,000. ° near, it has a large lift-to-drag ratio within a large range of angle of attack (8°). The maximum lift-to-drag ratio K is increased by about 16%, the maximum lift coefficient CL is increased by about 11%, and the stall angle of attack is increased by about 1 degree. The UAV using the airfoil of the present invention has better aerodynamic characteristics, can adapt to a larger flight speed range and larger flight altitude changes, has longer flight time, shorter take-off and landing distance, and a safer recovery method.
本发明一种轻小型固定翼无人机用翼型，其优点是该LRF1235翼型不仅具有良好的升阻特性和失速特性，而且翼型具有较大的相对厚度和后缘厚度，表明本发明具有良好的气动特性和工程性，具有满足轻小型固定翼无人机对高升力、高升阻比、高失速攻角和最大升力系数、大相对厚度的应用需求特点。The advantage of the present invention is that the LRF1235 airfoil not only has good lift-drag characteristics and stall characteristics, but also has large relative thickness and trailing edge thickness. It has good aerodynamic characteristics and engineering properties, and has the characteristics to meet the application requirements of light and small fixed-wing UAVs for high lift, high lift-to-drag ratio, high stall angle of attack, maximum lift coefficient, and large relative thickness.
附图说明Description of the drawings
图1为本发明的一种一种轻小型固定翼无人机用翼型LRF1235。Figure 1 shows a light and small fixed-wing UAV airfoil LRF1235 according to the present invention.
图2为本发明的翼型LRF1235与经典传统翼型的升力系数随攻角变化对比曲线图。Figure 2 is a comparative graph of the lift coefficient changing with the angle of attack between the airfoil LRF1235 of the present invention and the classic traditional airfoil.
图3为本发明的翼型LRF1235与经典传统翼型的升阻比随升力系数变化对比曲线图。Figure 3 is a comparison graph of the lift-to-drag ratio as the lift coefficient changes between the airfoil LRF1235 of the present invention and the classic traditional airfoil.
图4a、b为应用本发明的翼型LRF1235的4kg手抛型轻小型固定翼航测无人机平台。Figures 4a and b show a 4kg hand-thrown light and small fixed-wing aerial survey drone platform using the airfoil LRF1235 of the present invention.
图4中符号说明如下The symbols in Figure 4 are explained as follows
1螺旋桨，2机身，3机翼，4尾翼，A-A剖面为LRF1235翼型1 propeller, 2 fuselage, 3 wings, 4 tails, A-A section is LRF1235 airfoil
具体实施方式Detailed ways
下面结合附图和实施例，对本发明的技术方案做进一步的说明。The technical solution of the present invention will be further described below with reference to the accompanying drawings and examples.
目前该翼型已经用于图4所示某4kg手抛型轻小型固定翼无人机的优化设计中，航时提高约10％。见图4，本发明是一种用于轻小型固定翼无人机平台机翼设计的低雷诺数翼型。该无人机平台至少包括螺旋桨1、机身2、机翼3及尾翼4；其中无人机平台机翼3沿展向不同剖面位置使用本发明图1所示翼型LRF1235，各个剖面翼型根据机翼气动设计要求使用相应的当地安装角和扭转角，再将各个剖面沿展向拉伸生成机翼，形成无人机的主要承力部件，并且是影响无人机升阻特性和失速特性的主要部件。At present, this airfoil has been used in the optimized design of a 4kg hand-thrown light and small fixed-wing UAV shown in Figure 4, and the flight time has been increased by about 10%. See Figure 4. The present invention is a low Reynolds number airfoil used in the wing design of light and small fixed-wing UAV platforms. The unmanned aerial vehicle platform at least includes a propeller 1, a fuselage 2, a wing 3 and a tail 4; the wing 3 of the unmanned aerial vehicle platform uses the airfoil LRF1235 shown in Figure 1 of the present invention at different cross-sectional positions along the span. Each cross-sectional airfoil According to the aerodynamic design requirements of the wing, the corresponding local installation angle and twist angle are used, and then each section is stretched along the span to generate the wing, which forms the main load-bearing component of the UAV and affects the lift-drag characteristics and stall of the UAV. Features of the main components.
所述无人机平台机长1.28m，翼展2.4m，最大起飞重量4kg,最大任务载荷1kg，巡航飞行速度15m/s，飞行高度500m，巡航飞行雷诺数约20万，续航时间90min，动力为电动发动机。The UAV 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 flight speed of 15m/s, a flight altitude of 500m, a cruising flight Reynolds number of about 200,000, a endurance of 90min, and a power For electric engines.
该翼型LRF1235，相对厚度为12％，位于弦长28.8％位置，最大弯度为3.5％，位于弦长53.8％位置，100mm翼型后缘厚度为0.4mm，100mm翼型前缘半径为1.21mm。该翼型外形如图1所示。翼型剖面参数如下表1所示。表中两组x、y即x1、y1及x2、y2值分别代表二维坐标系下翼型上表面和下表面离散点坐标值。The airfoil LRF1235 has a relative thickness of 12% and is located at 28.8% of the chord length. The maximum camber is 3.5% and is located at 53.8% of the chord length. The 100mm airfoil trailing edge thickness is 0.4mm and the 100mm airfoil leading edge radius is 1.21mm. . The airfoil shape is shown in Figure 1. The airfoil profile parameters are shown in Table 1 below. The two sets of x and y values in the table, namely x 1 , y 1 and x 2 , y 2 values respectively represent the coordinate values of discrete points on the upper and lower surfaces of the airfoil in the two-dimensional coordinate system.
表1Table 1
翼型LRF1235是一种专门为轻小型固定翼无人机设计的翼型，有效的改善了翼型低雷诺数层流分离的特点，提升了升阻比和最大升力系数，改善了无人机的失速特性，解决了采用传统典型航空翼型的轻小型固定翼无人机大多存在飞机升阻比较小，最大可用升力有限，大攻角失速特性较差、飞行航时有限、起降距离较长，不能有效采用失速回收的缺点。The airfoil LRF1235 is an airfoil specially designed for light and small fixed-wing UAVs. It effectively improves the low Reynolds number laminar flow separation characteristics of the airfoil, increases the lift-drag ratio and maximum lift coefficient, and improves the performance of the UAV. The stall characteristics of the aircraft solve the problem that most light and small fixed-wing UAVs using traditional typical aviation airfoils have small lift-to-drag ratios, limited maximum available lift, poor stall characteristics at high angles of attack, limited flight hours, and long take-off and landing distances. It is long and cannot effectively use stall recovery.
Claims (1)
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 CN107757871A (en) | 2018-03-06 |
| CN107757871B true 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) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN112918668B (en) * | 2019-12-06 | 2022-12-20 | 北京二郎神科技有限公司 | Rotor of rotor craft and rotor craft |
| 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 |
| 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 |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (4)
| 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 |
| US8113462B2 (en) * | 2007-01-08 | 2012-02-14 | Israel Aerospace Industries, Ltd. | Low-drag swept wings |
| DE102008052858B9 (en) * | 2008-10-23 | 2014-06-12 | Senvion Se | Profile of a rotor blade and rotor blade of a wind turbine |
| IL226859A (en) * | 2013-06-10 | 2017-09-28 | Abramov Danny | Slotted airfoil and wings for air vehicles |
-
2017
- 2017-09-20 CN CN201710852194.1A patent/CN107757871B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 (3)
| Title |
|---|
| 两种椭圆翼型高速气动特性实验研究;邓阳平;高正红;詹浩;;实验力学(第02期);第103-107页 * |
| 刘天宝，程兆雪.流体力学与叶栅理论.机械工业出版社,1990,(第1版),第292-297页. * |
| 柔性后缘可变形机翼气动特性分析;程春晓;李道春;向锦武;石庆华;;北京航空航天大学学报(第02期);第360-366页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107757871A (en) | 2018-03-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107757871B (en) | Airfoil profile for light and small fixed wing unmanned aerial vehicle | |
| CN103693187B (en) | A kind of wing structure | |
| CN108995803B (en) | Foldable wave rider pneumatic layout structure and method of supersonic passenger plane | |
| CN103482054B (en) | Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle | |
| CN109808913B (en) | A UAV design method with deflectable winglets | |
| CN110498037B (en) | High lift-drag ratio laminar flow wing section suitable for low-altitude low-speed unmanned aerial vehicle | |
| CN201023653Y (en) | Aerodynamic layout of large aspect ratio forward-swept wing aircraft | |
| CN203681864U (en) | Airfoil with high lift force and high lift-drag ratio | |
| CN106005366A (en) | Pneumatic layout of dual flying wings of UAV (Unmanned Aerial Vehicle) | |
| CN104691739A (en) | High-lift-force laminar flow aerofoil profile with low-resistance and high-drag-divergence Mach number | |
| CN203593160U (en) | Wing structure | |
| CN105366049A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN103171766A (en) | Short distance rising and landing unmanned all-wing aircraft | |
| CN107792359A (en) | A kind of empty dual-purpose unmanned plane of water | |
| CN110254720A (en) | A flying wing layout solar unmanned aerial vehicle | |
| CN103158856A (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN102826216A (en) | Aerodynamic configuration of aircraft | |
| CN110539880A (en) | High-overload symmetric maneuvering control method for multi-control-surface flying-wing unmanned aerial vehicle | |
| CN115571323A (en) | Flat fusion body overall arrangement aircraft of subsonic speed | |
| CN108423157B (en) | Two-blade propeller suitable for tilting rotor aircraft | |
| CN106828933A (en) | A kind of HAE tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference | |
| CN110104160A (en) | Double-vane aircraft is folded away from coupling in one kind | |
| CN116812144A (en) | Body structure and its drone | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN104192294B (en) | wing structure and aircraft |
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 |