CN109969381A - A kind of low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber - Google Patents
A kind of low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber Download PDFInfo
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Abstract
The invention discloses a kind of low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber, are related to a kind of low Reynolds number airfoil, and the aerofoil profile maximum gauge is d/c=0.09, and maximum gauge position is xd/ c=0.274；The aerofoil profile maximum camber is f/c=0.0595, and maximum camber position is xf/ c=0.527；Wherein c is aerofoil profile chord length, and d is aerofoil profile maximum gauge, and f is aerofoil profile maximum camber；The aerofoil profile upper and lower surface is coordinate origin in up-front tie point, and axis where aerofoil profile chord length is x-axis, xdFor the abscissa of maximum gauge position, xfFor the abscissa of maximum camber position.The present invention abandons the blunt configuration of conventional aerofoil profile, and using sharp leading edge, reduction soaks area, greatly reduces resistance, and make aerofoil profile lift coefficient linear change before stall；Meanwhile aerofoil profile provided by the invention has the characteristics that heavy camber, generates the negative pressuren zone of aerofoil profile upper surface by heavy camber, thus the characteristics of realizing high-lift.
Description
Technical field
The present invention relates to a kind of low Reynolds number airfoils, in particular to a kind of low Reynolds with sharp leading edge heavy camber
Number airfoil with high ratio of lift over drag.
Background technique
Reynolds number is the ratio for being used to characterize air inertia force and viscous force in aerodynamics, airliner, transporter
Etc. cruising conditions Reynolds number in ten million magnitude.Low reynolds number flow (Reynolds number is below 500,000) is also widely present, such as Miniature wind
Machine, minute vehicle, small drone, near space vehicle etc..However, the aeroperformance of aerofoil profile is influenced sternly by low reynolds number
Weight, aerofoil profile of good performance is often performed poor under low reynolds number under high reynolds number.Under low reynolds number flow, air is by inverse pressure
The influence of gradient is easy to appear separation, again phenomenon, is formed so-called " separate bubble ".Separate bubble seriously affects the lift resistance of aerofoil profile
Force characteristic, and then influence aerodynamic characteristic, the efficiency of aircraft.
About the existing many researchs of low Reynolds number airfoil, experiment plate of the discovery with camber has preferably than conventional aerofoil profile
Aeroperformance.Some airfoil geometry features for seriously affecting high reynolds number aerofoil profile, such as blunt leading edge shape, to low Reynolds number airfoil
Performance influence it is unobvious.The small plate of thickness have in air it is lesser soak area, so as to resistance reduction, therefore have
There is preferable drag characteristic.However in actual engineer application, the small plate of thickness may face the situation of intensity deficiency, hold
Easy buckling deformation at work destroys.
To sum up, a kind of typical low reynolds number flow feature of adaptation is designed, while adapting to the promotion of Practical Project demand again
Resistance is very necessary for improving the aircraft efficiency under low reynolds number flow than aerofoil profile.
Summary of the invention
It is an object of the invention to provide a kind of tool aiming at the problem that conventional aerofoil profile is performed poor under low reynolds number environment
There is the low reynolds number airfoil with high ratio of lift over drag of sharp leading edge heavy camber, not only conform with low reynolds number flow feature, and there is high-lift, low
Drag characteristic improves the efficiency of low reynolds number aircraft.
Purpose to realize the present invention, the technical solution of use are as follows: a kind of low reynolds number promotion with sharp leading edge heavy camber
Than aerofoil profile, the aerofoil profile maximum gauge is d/c=0.09 for resistance, and maximum gauge position is xd/ c=0.274；The aerofoil profile maximum is curved
Degree is f/c=0.0595, and maximum camber position is xf/c=0.527；Wherein c is aerofoil profile chord length, and d is aerofoil profile maximum gauge, and f is
Aerofoil profile maximum camber；The aerofoil profile upper and lower surface is coordinate origin in up-front tie point, and axis where aerofoil profile chord length is x-axis,
xdFor the abscissa of maximum gauge position, xfFor the abscissa of maximum camber position.
Further, when the aerofoil profile chord length is 1, then coordinate corresponding to aerofoil profile upper surface is as follows: x1, y1 are respectively represented
Two-dimensional coordinate system Airfoil upper surface discrete point coordinate value, wherein the value of aerofoil profile upper surface x1, y1 are as follows: (0.00000,
0.00000), (0.00029,0.00096), (0.00075,0.00196), (0.00134,0.00302), (0.00205,
0.00416), (0.00288,0.00538), (0.00383,0.00670), (0.00494,0.00811), (0.00620,
0.00962), (0.00765,0.01124), (0.00928,0.01298), (0.01113,0.01484), (0.01322,
0.01684), (0.01557,0.01897), (0.01821,0.02123), (0.02117,0.02364), (0.02449,
0.02620), (0.02820,0.02890), (0.03234,0.03175), (0.03694,0.03474), (0.04206,
0.03786), (0.04775,0.04112), (0.05404,0.04448), (0.06099,0.04795), (0.06865,
0.05150), (0.07707,0.05511), (0.08631,0.05875), (0.09641,0.06239), (0.10742,
0.06600), (0.11939,0.06956), (0.13235,0.07301), (0.14634,0.07634), (0.16138,
0.07949), (0.17749,0.08245), (0.19469,0.08517), (0.21298,0.08762), (0.23233,
0.08977), (0.25274,0.09160), (0.27417,0.09307), (0.29656,0.09417), (0.31985,
0.09487), (0.34397,0.09515), (0.36883,0.09501), (0.39433,0.09443), (0.42035,
0.09342), (0.44677,0.09198), (0.47346,0.09013), (0.50029,0.08790), (0.52712,
0.08532), (0.55382,0.08244), (0.58026,0.07930), (0.60631,0.07595), (0.63186,
0.07245), (0.65680,0.06885), (0.68103,0.06520), (0.70447,0.06153), (0.72705,
0.05788), (0.74870,0.05428), (0.76939,0.05076), (0.78908,0.04732), (0.80775,
0.04399), (0.04399,0.04076), (0.84200,0.03765), (0.85759,0.03464), (0.87218,
0.03176), (0.88579,0.02899), (0.89846,0.02633), (0.91022,0.02380), (0.92111,
0.02137), (0.93118,0.01907), (0.94047,0.01687), (0.94902,0.01480), (0.95688,
0.01283), (0.96409,0.01098), (0.97070,0.00924), (0.97676,0.00761), (0.98229,
0.00608), (0.98735,0.00465), (0.99196,0.00332), (0.99617,0.00209), (1.00000,
0.00094)。
Further, when the aerofoil profile chord length is 1, then coordinate corresponding to aerofoil profile lower surface is as follows: x2, y2 are respectively represented
Two-dimensional coordinate system Airfoil lower surface discrete point coordinate value, wherein the value of aerofoil profile lower surface x2, y2 are as follows: (0.00000,
0.00000), (0.00090,0.00043), (0.00195,0.00077), (0.00312,0.00106), (0.00443,
0.00135), (0.00587,0.00166), (0.00746,0.00196), (0.00922,0.00225), (0.01116,
0.00252), (0.01330,0.00282), (0.01565,0.00311), (0.01824,0.00333), (0.02109,
0.00359), (0.02421,0.00385), (0.02765,0.00405), (0.03141,0.00421), (0.03554,
0.00437), (0.04006,0.00448), (0.04501,0.00453), (0.05041,0.00454), (0.05631,
0.00449), (0.06273,0.00438), (0.06973,0.00420), (0.07734,0.00396), (0.08561,
0.00365), (0.09457,0.00329), (0.10426,0.00287), (0.11474,0.00242), (0.12604,
0.00196), (0.13821,0.00151), (0.15127,0.00111), (0.16526,0.00079), (0.18021,
0.00060), (0.19614,0.00058), (0.21306,0.00080), (0.23096,0.00129), (0.24985,
0.00209), (0.26968,0.00325), (0.29045,0.00478), (0.31209,0.00669), (0.33455,
0.00898), (0.35776,0.01160), (0.38166,0.01451), (0.40616,0.01764), (0.43116,
0.02092), (0.45656,0.02425), (0.48226,0.02754), (0.50815,0.03070), (0.53411,
0.03363), (0.56001,0.03626), (0.58574,0.03853), (0.61116,0.04039), (0.63616,
0.04180), (0.66063,0.04276), (0.68445,0.04327), (0.70755,0.04335), (0.72982,
0.04303), (0.75122,0.04233), (0.77168,0.04129), (0.79116,0.03994), (0.80963,
0.03815), (0.82705,0.03602), (0.84345,0.03366), (0.85883,0.03118), (0.87322,
0.02864), (0.88665,0.02609), (0.89914,0.02357), (0.91075,0.02112), (0.92150,
0.01875), (0.93145,0.01648), (0.94064,0.01432), (0.94911,0.01227), (0.95691,
0.01035), (0.96408,0.00855), (0.97066,0.00687), (0.97670,0.00530), (0.98223,
0.00385), (0.98729,0.00250), (0.99192,0.00126), (0.99614,0.00011), (1.00000 ,-
0.00094)。
Further, when the Reynolds number of the aerofoil profile is 100,000, it is maximum lift coefficient that the angle of attack, which is at 10 °, and the angle of attack is small
When 10 °, lift coefficient is changed linearly.
Further, when the Reynolds number of the aerofoil profile is 100,000, for the angle of attack at 3 °~4 °, the lift resistance ratio of aerofoil profile is maximum.
The beneficial effects of the invention are as follows,
The present invention abandons the blunt configuration of conventional aerofoil profile, using sharp leading edge, not only reduces and soaks area, and make resistance significantly
Reduce；Meanwhile aerofoil profile provided by the invention has the characteristics that heavy camber, produces the negative pressuren zone of aerofoil profile upper surface by heavy camber
It is raw, thus the characteristics of realizing high-lift.
The present invention makes airfoil trailing edge portion retracts, is conducive to reduce and soaks area, achievees the purpose that reduce resistance；Meanwhile
Aerofoil profile makes aerofoil profile edge that segregation phenomenon not occur using sharp leading edge, and flowing keeps good attachment；Meanwhile with the aerofoil profile
The angle of attack increases, and lift keeps linear change before stall, and resistance variation slowly, has aerofoil profile under wide in range operating condition good
Aerodynamic characteristic.
Detailed description of the invention
Fig. 1 is the High-Lift Airfoil at Low Reynold Numbers schematic shapes with sharp leading edge heavy camber feature provided by the invention；
Fig. 2 is the High-Lift Airfoil at Low Reynold Numbers with sharp leading edge heavy camber feature provided by the invention and conventional aerofoil profile stream
The comparison diagram of line；
It in Reynolds number is 10 that Fig. 3, which is the High-Lift Airfoil at Low Reynold Numbers with sharp leading edge heavy camber feature provided by the invention,
Lift curve when ten thousand；
It in Reynolds number is 10 that Fig. 4, which is the High-Lift Airfoil at Low Reynold Numbers with sharp leading edge heavy camber feature provided by the invention,
Lift resistance ratio curve when ten thousand.
Label and corresponding parts title in attached drawing:
Specific embodiment
The present invention is described in further detail below through specific implementation examples and in conjunction with the accompanying drawings.
A kind of shown low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber provided by the invention of Fig. 1, the wing
Type maximum gauge is d/c=0.09, and maximum gauge position is xd/ c=0.274；The aerofoil profile maximum camber is f/c=
0.0595, maximum camber position is xf/c=0.527；Wherein c is aerofoil profile chord length, and d is aerofoil profile maximum gauge, and f is that aerofoil profile is maximum
Camber；The aerofoil profile upper and lower surface is coordinate origin in up-front tie point, and axis where aerofoil profile chord length is x-axis, xdFor maximum
The abscissa of thickness position, xfFor the abscissa of maximum camber position.
The upper and lower surfaces of aerofoil profile proposed by the present invention are not geometry continuums in edge；And conventional aerofoil profile leading edge
It is continuous blunt configuration, keeps aerofoil profile big by the maximum curvature at the blunt nosed place of leading edge, so that air accelerates in leading edge, in the wing
Type upper surface forms negative pressuren zone, so that aerofoil profile following table surface pressure is become larger, thus generates lift.
The present invention is hindered using low reynolds number than aerofoil profile, in low reynolds number flow, the shadow of the air-flow of acceleration in adverse pressure gradient
It is separated quickly under sound, makes leading edge accelerate brought underbalance effect not significant, and as Reynolds number is smaller, the viscosity effect of gas
Should be more significant, Blunt leading edge soaks that area is larger, and bring drag effect is more obvious.
Currently, conventional aerofoil profile is easy to produce flow separation and steeps under low reynolds number and lesser flying angle, and with
The angle of attack increases, and separate bubble range expands and gradually to Blunt leading edge movement, and developing to a certain range can rupture suddenly；And conventional
At least there are two the adverse effects of aspect for low Reynolds number airfoil: 1) stalling angle of aerofoil profile is obviously reduced, thus maximum lift system
Number also declines therewith；2) lift is caused with angle of attack linear change, not may cause aircraft unstability and even destroy.Therefore the present invention
The blunt configuration for abandoning conventional aerofoil profile is soaked area to reduce, is not only made the negative pressure of aerofoil profile upper surface by relying on using sharp leading edge
The heavy camber of aerofoil profile is realized, and shrinks aerofoil profile close to rear edge part, and area is soaked in reduction.
When the aerofoil profile chord length is 1, then coordinate corresponding to aerofoil profile upper surface is as follows: x1, y1 respectively represent two-dimensional coordinate
It is Airfoil upper surface discrete point coordinate value, wherein the value of aerofoil profile upper surface x1, y1 are as follows: (0.00000,0.00000),
(0.00029,0.00096), (0.00075,0.00196), (0.00134,0.00302), (0.00205,0.00416),
(0.00288,0.00538), (0.00383,0.00670), (0.00494,0.00811), (0.00620,0.00962),
(0.00765,0.01124), (0.00928,0.01298), (0.01113,0.01484), (0.01322,0.01684),
(0.01557,0.01897), (0.01821,0.02123), (0.02117,0.02364), (0.02449,0.02620),
(0.02820,0.02890), (0.03234,0.03175), (0.03694,0.03474), (0.04206,0.03786),
(0.04775,0.04112), (0.05404,0.04448), (0.06099,0.04795), (0.06865,0.05150),
(0.07707,0.05511), (0.08631,0.05875), (0.09641,0.06239), (0.10742,0.06600),
(0.11939,0.06956), (0.13235,0.07301), (0.14634,0.07634), (0.16138,0.07949),
(0.17749,0.08245), (0.19469,0.08517), (0.21298,0.08762), (0.23233,0.08977),
(0.25274,0.09160), (0.27417,0.09307), (0.29656,0.09417), (0.31985,0.09487),
(0.34397,0.09515), (0.36883,0.09501), (0.39433,0.09443), (0.42035,0.09342),
(0.44677,0.09198), (0.47346,0.09013), (0.50029,0.08790), (0.52712,0.08532),
(0.55382,0.08244), (0.58026,0.07930), (0.60631,0.07595), (0.63186,0.07245),
(0.65680,0.06885), (0.68103,0.06520), (0.70447,0.06153), (0.72705,0.05788),
(0.74870,0.05428), (0.76939,0.05076), (0.78908,0.04732), (0.80775,0.04399),
(0.04399,0.04076), (0.84200,0.03765), (0.85759,0.03464), (0.87218,0.03176),
(0.88579,0.02899), (0.89846,0.02633), (0.91022,0.02380), (0.92111,0.02137),
(0.93118,0.01907), (0.94047,0.01687), (0.94902,0.01480), (0.95688,0.01283),
(0.96409,0.01098), (0.97070,0.00924), (0.97676,0.00761), (0.98229,0.00608),
(0.98735,0.00465), (0.99196,0.00332), (0.99617,0.00209), (1.00000,0.00094).
When the aerofoil profile chord length is 1, then coordinate corresponding to aerofoil profile lower surface is as follows: x2, y2 respectively represent two-dimensional coordinate
It is Airfoil lower surface discrete point coordinate value, wherein the value of aerofoil profile lower surface x2, y2 are as follows: (0.00000,0.00000),
(0.00090,0.00043), (0.00195,0.00077), (0.00312,0.00106), (0.00443,0.00135),
(0.00587,0.00166), (0.00746,0.00196), (0.00922,0.00225), (0.01116,0.00252),
(0.01330,0.00282), (0.01565,0.00311), (0.01824,0.00333), (0.02109,0.00359),
(0.02421,0.00385), (0.02765,0.00405), (0.03141,0.00421), (0.03554,0.00437),
(0.04006,0.00448), (0.04501,0.00453), (0.05041,0.00454), (0.05631,0.00449),
(0.06273,0.00438), (0.06973,0.00420), (0.07734,0.00396), (0.08561,0.00365),
(0.09457,0.00329), (0.10426,0.00287), (0.11474,0.00242), (0.12604,0.00196),
(0.13821,0.00151), (0.15127,0.00111), (0.16526,0.00079), (0.18021,0.00060),
(0.19614,0.00058), (0.21306,0.00080), (0.23096,0.00129), (0.24985,0.00209),
(0.26968,0.00325), (0.29045,0.00478), (0.31209,0.00669), (0.33455,0.00898),
(0.35776,0.01160), (0.38166,0.01451), (0.40616,0.01764), (0.43116,0.02092),
(0.45656,0.02425), (0.48226,0.02754), (0.50815,0.03070), (0.53411,0.03363),
(0.56001,0.03626), (0.58574,0.03853), (0.61116,0.04039), (0.63616,0.04180),
(0.66063,0.04276), (0.68445,0.04327), (0.70755,0.04335), (0.72982,0.04303),
(0.75122,0.04233), (0.77168,0.04129), (0.79116,0.03994), (0.80963,0.03815),
(0.82705,0.03602), (0.84345,0.03366), (0.85883,0.03118), (0.87322,0.02864),
(0.88665,0.02609), (0.89914,0.02357), (0.91075,0.02112), (0.92150,0.01875),
(0.93145,0.01648), (0.94064,0.01432), (0.94911,0.01227), (0.95691,0.01035),
(0.96408,0.00855), (0.97066,0.00687), (0.97670,0.00530), (0.98223,0.00385),
(0.98729,0.00250), (0.99192,0.00126), (0.99614,0.00011), (1.00000, -0.00094).
As shown in Fig. 2, the low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber provided by the invention, flows in the wing
Type upper surface and lower surface keep good attachment, do not there is flow separation generation, thus guarantee wing section lift coefficient stall it
Frontal variation keeps resistance variation gentle；In contrast, conventional aerofoil profile generates flow separation at Blunt leading edge, by serious shadow
Ring lift linear characteristic, maximum lift coefficient, resistance coefficient etc..
As shown in figure 3, the lift of the low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber provided by the invention is bent
Line chart, wherein abscissa is the angle of attack of aerofoil profile, and ordinate is the lift coefficient of aerofoil profile；When Reynolds number is 100,000, and the angle of attack is 0
At~8 °, propradation is kept with wing section lift coefficient, when the angle of attack is 10 °, the lift coefficient of aerofoil profile is maximum.
As shown in figure 4, curve is compared in the low reynolds number airfoil with high ratio of lift over drag resistance with sharp leading edge heavy camber provided by the invention
Figure, wherein abscissa is airfoil angle-of-attack, and ordinate is the lift resistance ratio of aerofoil profile, and when Reynolds number is 100,000, and the angle of attack is at 0 °~4 °
When, the lift resistance ratio of aerofoil profile is in upward status；When the angle of attack is 3 °~4 °, the lift resistance ratio of aerofoil profile is maximum；And the angle of attack is at 0~8 °,
Lift resistance ratio variation is gentle, is maintained at higher level, illustrates that the aerofoil profile has good lifting resistance characteristic.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (5)
1. a kind of low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber, which is characterized in that the aerofoil profile maximum gauge
For d/c=0.09, maximum gauge position is xd/ c=0.274；The aerofoil profile maximum camber is f/c=0.0595, maximum camber
Position is xf/ c=0.527；Wherein c is aerofoil profile chord length, and d is aerofoil profile maximum gauge, and f is aerofoil profile maximum camber；In the aerofoil profile
Lower surface is coordinate origin in up-front tie point, and axis where aerofoil profile chord length is x-axis, xdFor the horizontal seat of maximum gauge position
Mark, xfFor the abscissa of maximum camber position.
2. the low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber according to claim 1, which is characterized in that institute
State aerofoil profile chord length be 1 when, then coordinate corresponding to aerofoil profile upper surface is as follows: x1, y1 are respectively represented on two-dimensional coordinate system Airfoil
Discretization of half-space surface point coordinate value, wherein the value of aerofoil profile upper surface x1, y1 are as follows: (0.00000,0.00000), (0.00029,
0.00096), (0.00075,0.00196), (0.00134,0.00302), (0.00205,0.00416), (0.00288,
0.00538), (0.00383,0.00670), (0.00494,0.00811), (0.00620,0.00962), (0.00765,
0.01124), (0.00928,0.01298), (0.01113,0.01484), (0.01322,0.01684), (0.01557,
0.01897), (0.01821,0.02123), (0.02117,0.02364), (0.02449,0.02620), (0.02820,
0.02890), (0.03234,0.03175), (0.03694,0.03474), (0.04206,0.03786), (0.04775,
0.04112), (0.05404,0.04448), (0.06099,0.04795), (0.06865,0.05150), (0.07707,
0.05511), (0.08631,0.05875), (0.09641,0.06239), (0.10742,0.06600), (0.11939,
0.06956), (0.13235,0.07301), (0.14634,0.07634), (0.16138,0.07949), (0.17749,
0.08245), (0.19469,0.08517), (0.21298,0.08762), (0.23233,0.08977), (0.25274,
0.09160), (0.27417,0.09307), (0.29656,0.09417), (0.31985,0.09487), (0.34397,
0.09515), (0.36883,0.09501), (0.39433,0.09443), (0.42035,0.09342), (0.44677,
0.09198), (0.47346,0.09013), (0.50029,0.08790), (0.52712,0.08532), (0.55382,
0.08244), (0.58026,0.07930), (0.60631,0.07595), (0.63186,0.07245), (0.65680,
0.06885), (0.68103,0.06520), (0.70447,0.06153), (0.72705,0.05788), (0.74870,
0.05428), (0.76939,0.05076), (0.78908,0.04732), (0.80775,0.04399), (0.04399,
0.04076), (0.84200,0.03765), (0.85759,0.03464), (0.87218,0.03176), (0.88579,
0.02899), (0.89846,0.02633), (0.91022,0.02380), (0.92111,0.02137), (0.93118,
0.01907), (0.94047,0.01687), (0.94902,0.01480), (0.95688,0.01283), (0.96409,
0.01098), (0.97070,0.00924), (0.97676,0.00761), (0.98229,0.00608), (0.98735,
0.00465), (0.99196,0.00332), (0.99617,0.00209), (1.00000,0.00094).
3. the low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber according to claim 1 or 2, feature exist
In when the aerofoil profile chord length is 1, then coordinate corresponding to aerofoil profile lower surface is as follows: x2, y2 respectively represent two-dimensional coordinate system bottom wing
Type lower surface discrete point coordinate value, wherein the value of aerofoil profile lower surface x2, y2 are as follows: (0.00000,0.00000),
(0.00090,0.00043), (0.00195,0.00077), (0.00312,0.00106), (0.00443,0.00135),
(0.00587,0.00166), (0.00746,0.00196), (0.00922,0.00225), (0.01116,0.00252),
(0.01330,0.00282), (0.01565,0.00311), (0.01824,0.00333), (0.02109,0.00359),
(0.02421,0.00385), (0.02765,0.00405), (0.03141,0.00421), (0.03554,0.00437),
(0.04006,0.00448), (0.04501,0.00453), (0.05041,0.00454), (0.05631,0.00449),
(0.06273,0.00438), (0.06973,0.00420), (0.07734,0.00396), (0.08561,0.00365),
(0.09457,0.00329), (0.10426,0.00287), (0.11474,0.00242), (0.12604,0.00196),
(0.13821,0.00151), (0.15127,0.00111), (0.16526,0.00079), (0.18021,0.00060),
(0.19614,0.00058), (0.21306,0.00080), (0.23096,0.00129), (0.24985,0.00209),
(0.26968,0.00325), (0.29045,0.00478), (0.31209,0.00669), (0.33455,0.00898),
(0.35776,0.01160), (0.38166,0.01451), (0.40616,0.01764), (0.43116,0.02092),
(0.45656,0.02425), (0.48226,0.02754), (0.50815,0.03070), (0.53411,0.03363),
(0.56001,0.03626), (0.58574,0.03853), (0.61116,0.04039), (0.63616,0.04180),
(0.66063,0.04276), (0.68445,0.04327), (0.70755,0.04335), (0.72982,0.04303),
(0.75122,0.04233), (0.77168,0.04129), (0.79116,0.03994), (0.80963,0.03815),
(0.82705,0.03602), (0.84345,0.03366), (0.85883,0.03118), (0.87322,0.02864),
(0.88665,0.02609), (0.89914,0.02357), (0.91075,0.02112), (0.92150,0.01875),
(0.93145,0.01648), (0.94064,0.01432), (0.94911,0.01227), (0.95691,0.01035),
(0.96408,0.00855), (0.97066,0.00687), (0.97670,0.00530), (0.98223,0.00385),
(0.98729,0.00250), (0.99192,0.00126), (0.99614,0.00011), (1.00000, -0.00094).
4. the low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber according to claim 1, which is characterized in that institute
When the Reynolds number for stating aerofoil profile is 100,000, the angle of attack be maximum lift coefficient at 10 °, and when the angle of attack is less than 10 °, lift coefficient is in line
Property variation.
5. the low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber according to claim 1 or 4, feature exist
In when the Reynolds number of the aerofoil profile is 100,000, for the angle of attack at 3 °~4 °, the lift resistance ratio of aerofoil profile is maximum.
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Cited By (3)
| 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 |
| CN115320827A (en) * | 2022-10-14 | 2022-11-11 | 中国航空工业集团公司沈阳空气动力研究所 | High-lift-drag-ratio airfoil profile with high subsonic speed and low Reynolds number flow |
| CN115649417A (en) * | 2022-12-14 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | High subsonic speed self-balancing high stealth airfoil profile |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080283674A1 (en) * | 2007-01-08 | 2008-11-20 | Israel Aerospace Industries Ltd. | Low-drag swept wings |
| CN101813070A (en) * | 2010-04-13 | 2010-08-25 | 南京航空航天大学 | Vane airfoil profile of low power wind driven generator |
| CN102400847A (en) * | 2011-11-29 | 2012-04-04 | 吉林大学 | Wind-driven generator blade wing section |
| CN203770019U (en) * | 2014-04-17 | 2014-08-13 | 吉林大学 | 100-W wind turbine blade |
| 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 |
| CN108583847A (en) * | 2018-04-26 | 2018-09-28 | 陈俊胤 | A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft |
-
2019
- 2019-04-12 CN CN201910294428.4A patent/CN109969381A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080283674A1 (en) * | 2007-01-08 | 2008-11-20 | Israel Aerospace Industries Ltd. | Low-drag swept wings |
| CN101813070A (en) * | 2010-04-13 | 2010-08-25 | 南京航空航天大学 | Vane airfoil profile of low power wind driven generator |
| CN102400847A (en) * | 2011-11-29 | 2012-04-04 | 吉林大学 | Wind-driven generator blade wing section |
| CN203770019U (en) * | 2014-04-17 | 2014-08-13 | 吉林大学 | 100-W wind turbine blade |
| 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 |
| CN108583847A (en) * | 2018-04-26 | 2018-09-28 | 陈俊胤 | A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft |
Cited By (5)
| 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 |
| CN115320827A (en) * | 2022-10-14 | 2022-11-11 | 中国航空工业集团公司沈阳空气动力研究所 | High-lift-drag-ratio airfoil profile with high subsonic speed and low Reynolds number flow |
| CN115320827B (en) * | 2022-10-14 | 2023-01-31 | 中国航空工业集团公司沈阳空气动力研究所 | High-lift-drag-ratio airfoil profile with high subsonic speed and low Reynolds number flow |
| CN115649417A (en) * | 2022-12-14 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | High subsonic speed self-balancing high stealth airfoil profile |
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