CN201943900U - Wind-power machine vane-aerofoil family - Google Patents

Wind-power machine vane-aerofoil family Download PDF

Info

Publication number
CN201943900U
CN201943900U CN2010206771537U CN201020677153U CN201943900U CN 201943900 U CN201943900 U CN 201943900U CN 2010206771537 U CN2010206771537 U CN 2010206771537U CN 201020677153 U CN201020677153 U CN 201020677153U CN 201943900 U CN201943900 U CN 201943900U
Authority
CN
China
Prior art keywords
aerofoil profile
aerofoil
pressure side
string
chord length
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.)
Expired - Lifetime
Application number
CN2010206771537U
Other languages
Chinese (zh)
Inventor
白井艳
杨科
徐建中
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Institute of Engineering Thermophysics of CAS
Original Assignee
Institute of Engineering Thermophysics of CAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Institute of Engineering Thermophysics of CAS filed Critical Institute of Engineering Thermophysics of CAS
Priority to CN2010206771537U priority Critical patent/CN201943900U/en
Application granted granted Critical
Publication of CN201943900U publication Critical patent/CN201943900U/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • Y02E10/722—

Landscapes

  • Materials For Photolithography (AREA)

Abstract

The utility model relates to a wind-power machine vane-aerofoil family, which comprises a first aerofoil to a fourth aerofoil with different relative thicknesses, wherein the relative thickness is the specific value of the maximum distance and the chord length between an upper surface and a lower surface of each aerofoil, and the chord length is the length of a chord line from the front edge to the tail edge of each aerofoil; and each aerofoil comprises the front edge, the tail edge, a suction surface and a pressure surface. The front-edge radius of the wind-power machine vane-aerofoil family is 10.203-15.345 percent of the chord line, the thickness of the tail edge is 5-11 percent of the chord line, the relative thickness is 45-60 percent, the position of the maximum relative thickness is 32.1-33.2 percent of the chord line away from the front edge, and the pressure surfaces are four different S-shaped after-loaded pressure surfaces. The geometric shape of each aerofoil of the wind-power machine vane-aerofoil family is formed by smoothly connecting the dimensionless two-dimensional coordinates of all points on the pressure surface and the suction surface of each aerofoil, and the dimensionless two-dimensional coordinate is the specific value of the horizontal coordinate and the longitudinal coordinate of each point and the chord line.

Description

A kind of wind turbine blade airfoil family
Technical field
The utility model relates to a kind of wind turbine blade airfoil family, particularly a kind of thick family of aerofoil sections of blunt trailing edge of pneumatic equipment blades made.
Background technique
Along with energy issue of world becomes increasingly conspicuous, wind energy is developed rapidly as eco-friendly renewable energy sources.Pneumatic equipment blades made is the core component of wind-powered electricity generation unit, and blade be by aerofoil profile along its exhibition to being formed by stacking, so the quality of airfoil performance has directly determined the quality of wind-powered electricity generation unit performance.Therefore along with the continuous large scale development of wind-powered electricity generation unit, blade is more and more longer, and particularly root of blade all has higher requirement to the structure and the aerodynamic characteristic of aerofoil profile, designs and develops the thick wing type, aerofoil with blunt tail edge becomes inevitable demand.
Increase the structural characteristics that profile thickness can improve aerofoil profile, but along with the increase of profile thickness, the aerofoil profile aeroperformance can reduce, can reduce such as the maximum lift coefficient and the maximum lift-drag ratio of aerofoil profile, the coarse receptance of the leading edge of aerofoil profile can increase etc.And adopt blunt trailing edge can when satisfying the airfoil structure characteristic, improve the aerodynamic characteristic of thick wing type, increase the suction gradient that aerofoil profile trailing edge thickness can reduce the aerofoil profile suction surface, postpone the aerofoil profile turbulent separation, thereby improve wing section lift coefficient, the coarse receptance of reduction aerofoil profile leading edge.
The model utility content
The purpose of this utility model is to provide a kind of thick family of aerofoil sections of blunt trailing edge of pneumatic equipment blades made special use, adapting to the wind energy conversion system large scale development, the thick wing type is used for root of blade replacing traditional cylindrical structure, thereby improves Blade Properties.
For realizing above-mentioned target, the wind turbine blade airfoil family that the utility model provides comprises the aerofoil profile of first to fourth different relative thicknesses, and described relative thickness is the ratio of the length of the maximum ga(u)ge between each aerofoil profile upper and lower surfaces and the string of a musical instrument;
Each aerofoil profile is formed by leading edge, trailing edge, suction surface, pressure side;
Trailing edge has the thickness of chord length 5% ~ 11% from the leading edge to trailing edge, and pressure side is to load after four S shapes in various degree;
The relative thickness of this family of aerofoil sections is 45%-60%;
The position of the maximum relative thickness of this family of aerofoil sections is at distance leading edge point 32.1% ~ 33.2% chord length place;
Wherein, the geometric shape of first to fourth aerofoil profile is that the dimensionless two-dimensional coordinate smooth connection by each point on pressure side and the suction surface forms the abscissa that described dimensionless two-dimensional coordinate is an each point and the ratio of y coordinate and chord length.
Having the following advantages of wind turbine blade airfoil family of the present utility model:
1, wind turbine blade airfoil family of the present utility model has satisfied the structural requirement of large scale wind power machine blade sheet root aerofoil profile on geometrical construction;
2, wind turbine blade airfoil family of the present utility model has good aerodynamic characteristic, has effectively improved Blade Properties, can improve lift coefficient, the ratio of lift coefficient to drag coefficient of root of blade, reduces the coarse receptance of root of blade;
3, wind turbine blade airfoil family of the present utility model can reduce the weight of blade, reduces the blade cost.
Description of drawings
Fig. 1 is the perspective view of a pneumatic equipment blades made of application the utility model family of aerofoil sections structure.
Fig. 2 is the composite diagram of wind turbine blade airfoil family of the present utility model.
Fig. 3 is the profile diagram of first aerofoil profile of wind turbine blade airfoil family of the present utility model.
Fig. 4 is the profile diagram of second aerofoil profile of wind turbine blade airfoil family of the present utility model.
Fig. 5 is the profile diagram of the 3rd aerofoil profile of wind turbine blade airfoil family of the present utility model.
Fig. 6 is the profile diagram of the 4th aerofoil profile of wind turbine blade airfoil family of the present utility model.
Embodiment
Below in conjunction with accompanying drawing the utility model is described in detail, be to be noted that described specific embodiment only is intended to be convenient to understanding of the present utility model, and it is not played any qualification effect.
Referring now to Fig. 1, Fig. 1 has shown the pneumatic equipment blades made B that uses wind turbine blade airfoil family A of the present utility model.Wind turbine blade airfoil family of the present utility model preferably can be used for the horizontal-shaft wind turbine blade.Blade B comprises medial area 110, LHA 120 and the blade tip district 130 of next-door neighbour's wheel hub (not shown).Usually, medial area 110 accounts for blade 100 and opens up 50% of length, and LHA accounts for 30% of blade 100 exhibition length, and blade tip district 130 accounts for 20% of blade 100 exhibition length.
Fig. 2 has shown the utility model wind mill airfoil A of family.Family of aerofoil sections A includes leading edge A00, suction surface A20, trailing edge A10, pressure side A30.String of a musical instrument A40 extends to trailing edge A10 from each leading edge A00 of family of aerofoil sections A.The leading edge angle of first aerofoil profile 150, second aerofoil profile 160, the 3rd aerofoil profile 170, the 4th aerofoil profile 180, suction surface thickness, trailing edge thickness, pressure side radian, profile thickness etc. are all inequality shown in Fig. 2, are fit to use the medial area 110 at blade B shown in Figure 1.
All have how much good compatibility between each aerofoil profile, each aerofoil profile section is according to method as known in the art in blade, connect by the transitional surface that connects the appropriate section between any two adjacent air foil shapes, the aerofoil profile transverse section can translation-angle according to known method, so that blade is imported effective resistance, thereby form the blade incidence that requires determined variation by aerodynamic quality.
Profile thickness is meant the distance between the aerofoil profile upper and lower surface, and the ratio of maximum ga(u)ge and chord length is called the relative thickness of aerofoil profile.The scope of the relative thickness of family of aerofoil sections A is 45%-60% in the utility model, and the position of maximum ga(u)ge is at distance leading edge point 32.1% ~ 33.2%% chord length place.Be applicable to length of blade more than 20 meters, power MW above, Stall Type or become the wind energy conversion system of oar type.Family of aerofoil sections of the present utility model is in Re=3 * 10 6Operating mode under, have high lift coefficient, stalling range is less during Low Angle Of Attack.As can be seen, in the utility model, preferred, the trailing edge A10 of family of aerofoil sections A has certain thickness from the outside geometric properties of family of aerofoil sections A, and thickness range is 5% ~ 11% chord length, loads behind the S type in various degree that pressure side has.Along with the increase of profile thickness, the form that aerofoil profile is separated stall forwards the pressure side separation to from the trailing edge separation, and the relative thickness of this family of aerofoil sections is greater than 45%, and aerofoil profile can be pressure side just to occur to separate at Low Angle Of Attack, increases aerofoil profile trailing edge thickness and can effectively improve this situation.Aerofoil profile be if loading can make aerofoil profile occur separating at Low Angle Of Attack downforce face on a large scale after adopting bigger S type, though and load behind the too little S type that pressure side separates in the time of can suppressing Low Angle Of Attack, can make wing section lift coefficient lower.This family of aerofoil sections is taken all factors into consideration from two aspects, loads shape after making aerofoil profile have suitable S type.
Fig. 3-Fig. 6 has shown the embodiment of four aerofoil profiles that the utility model family of aerofoil sections A is comprised, the appearance profile of aerofoil profile among each embodiment.
The dimensionless two-dimensional coordinate data point of first aerofoil profile 150, second aerofoil profile 160, the 3rd aerofoil profile 170 and the 4th aerofoil profile 180 suction surfaces of the utility model family of aerofoil sections A is listed on the suction surface hurdle respectively among the table 1-8.The string of a musical instrument of each aerofoil profile extends to trailing edge from leading edge, and the length of the string of a musical instrument is chord length c, obtains the dimensionless geometric coordinate of this aerofoil profile suction surface after the abscissa of the each point on each aerofoil profile suction surface and the chord length of y coordinate divided by this aerofoil profile.The dimensionless two-dimensional coordinate data point of above-mentioned aerofoil profile pressure side is listed on the pressure side hurdle respectively among the table 1-8.Obtain the dimensionless geometric coordinate of this aerofoil profile pressure side after the abscissa of the each point on each aerofoil profile pressure side and the chord length of y coordinate divided by this aerofoil profile.Can form the suction surface and the pressure side profile of above-mentioned aerofoil profile respectively by the smooth connection of spline curve according to listed data point in the table.First, second, third aerofoil profile, the 4th aerofoil profile can be used as pneumatic equipment blades made medial area aerofoil profile.
Certain point in the table on x/c value representation suction surface or the pressure side on string of a musical instrument direction with respect to the position of leading edge, be on suction surface or the pressure side certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of y/c value representation certain point from the string of a musical instrument to the suction surface or on the pressure side and the ratio of chord length c.The dimensionless two-dimensional coordinate data of describing aerofoil profile in the table can be amplified and dwindle and be kept the shape invariance of aerofoil profile, the scalable scheme of coordinate multiply by for x, y coordinate figure among the table 1-8 or divided by non-vanishing constant, is met the aerofoil profile of the different chord lengths size of designing requirement then.
Specify each aerofoil profile below:
Fig. 3 has shown first aerofoil profile 150 of the utility model family of aerofoil sections A, and preferred, the relative thickness of this aerofoil profile is 45%, is used for the medial area 110 of blade B.Aerofoil profile at reynolds' number 3 * 10 6Operating mode under carry out work, and with other aerofoil profiles among the wind energy conversion system special airfoil A of family have good how much compatible.
First aerofoil profile 150 has the first aerofoil profile leading edge, 151, the first aerofoil profile strings of a musical instrument, 152, the first aerofoil profile suction surfaces, 153, the first aerofoil profile trailing edges, 154, the first aerofoil profile pressure sides 155.The first aerofoil profile string of a musical instrument 152 extends to the first aerofoil profile trailing edge 154 from the first aerofoil profile leading edge 151.The first aerofoil profile suction surface 153 of first aerofoil profile 150 is preferred, according to pressing the smooth connection of listing in the hurdle, the inside of dimensionless two-dimensional coordinate data point to form in the table 1.
Concrete shape provides with the dimensionless coordinate form in table 1,2.On x/c value representation suction surface 153 or the pressure side 155 certain point on the string of a musical instrument 152 directions with respect to the position of leading edge 151, be certain point on suction surface 153 or the pressure side 155 on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the y/c value then represent from the string of a musical instrument 152 to suction surface 153 or pressure side 155 on the height y of certain point and the ratio of chord length c.These values are scalable as the function of identical constant or quantity, amplify or dwindle and aerofoil profile that shape remains unchanged so that ratio to be provided.
The table 1 first aerofoil profile suction surface
x/c y/c x/c y/c x/c y/c
1.00000 0.02500 0.67180 0.15305 0.22271 0.20538
0.99376 0.02753 0.65814 0.15764 0.21309 0.20269
0.98753 0.03005 0.64416 0.16217 0.20344 0.19975
0.98129 0.03257 0.62988 0.16662 0.19379 0.19656
0.97505 0.03510 0.61535 0.17096 0.18418 0.19314
0.96882 0.03761 0.60059 0.17517 0.17463 0.18948
0.96196 0.04038 0.58566 0.17923 0.16520 0.18561
0.95499 0.04318 0.57062 0.18312 0.15593 0.18156
0.94791 0.04602 0.55551 0.18681 0.14687 0.17733
0.94072 0.04890 0.54039 0.19031 0.13807 0.17297
0.93344 0.05182 0.52534 0.19360 0.12956 0.16852
0.92605 0.05478 0.51041 0.19667 0.12141 0.16400
0.91856 0.05778 0.49565 0.19953 0.11365 0.15946
0.91096 0.06082 0.48114 0.20218 0.10631 0.15494
0.90326 0.06390 0.46691 0.20462 0.09943 0.15048
0.89545 0.06703 0.45302 0.20686 0.09301 0.14612
0.88751 0.07020 0.43949 0.20890 0.08708 0.14189
0.87946 0.07341 0.42637 0.21075 0.08161 0.13782
0.87127 0.07668 0.41366 0.21241 0.07662 0.13390
0.86293 0.07999 0.40138 0.21389 0.07205 0.13013
0.85444 0.08337 0.38953 0.21518 0.06786 0.12650
0.84578 0.08680 0.37809 0.21628 0.06400 0.12296
0.83693 0.09031 0.36705 0.21720 0.06038 0.11946
0.82789 0.09389 0.35638 0.21793 0.05689 0.11589
0.81863 0.09754 0.34604 0.21847 0.05343 0.11217
0.80914 0.10129 0.33599 0.21880 0.04984 0.10815
0.79940 0.10513 0.32618 0.21893 0.04600 0.10367
0.78940 0.10907 0.31658 0.21885 0.04177 0.09855
0.77912 0.11310 0.30712 0.21855 0.03702 0.09257
0.76854 0.11723 0.29777 0.21803 0.03168 0.08548
0.75765 0.12147 0.28847 0.21728 0.02577 0.07702
0.74643 0.12579 0.27920 0.21630 0.01939 0.06686
0.73488 0.13021 0.26992 0.21509 0.01286 0.05461
0.72298 0.13469 0.26060 0.21364 0.00672 0.03983
0.71072 0.13924 0.25122 0.21195 0.00190 0.02189
0.69810 0.14383 0.24178 0.21001 0.00000 0.00000
0.68513 0.14844 0.23228 0.20782 ? ?
Wherein, on the suction surface of x/c value representation first aerofoil profile 150 certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of certain point and the ratio of chord length c on the y/c value is then represented from the string of a musical instrument to first aerofoil profile, 150 suction surfaces;
The table 2 first aerofoil profile pressure side
x/c y/c x/c y/c x/c y/c
0.00000 0.00000 0.21360 -0.21144 0.69181 -0.10808
0.00221 -0.01909 0.22507 -0.21526 0.70316 -0.10306
0.00704 -0.03485 0.23705 -0.21876 0.71447 -0.09813
0.01306 -0.04805 0.24951 -0.22189 0.72574 -0.09330
0.01935 -0.05916 0.26243 -0.22463 0.73694 -0.08857
0.02536 -0.06853 0.27578 -0.22692 0.74805 -0.08394
0.03083 -0.07643 0.28952 -0.22873 0.75906 -0.07942
0.03568 -0.08308 0.30360 -0.23004 0.76996 -0.07501
0.03997 -0.08869 0.31797 -0.23081 0.78071 -0.07070
0.04378 -0.09348 0.33257 -0.23104 0.79131 -0.06652
0.04724 -0.09763 0.34732 -0.23071 0.80175 -0.06246
0.05049 -0.10131 0.36217 -0.22982 0.81200 -0.05853
0.05363 -0.10469 0.37704 -0.22838 0.82205 -0.05475
0.05677 -0.10789 0.39187 -0.22641 0.83191 -0.05112
0.06000 -0.11103 0.40661 -0.22394 0.84156 -0.04766
0.06339 -0.11420 0.42119 -0.22098 0.85100 -0.04437
0.06697 -0.11747 0.43559 -0.21759 0.86022 -0.04126
0.07080 -0.12088 0.44975 -0.21378 0.86922 -0.03836
0.07489 -0.12446 0.46365 -0.20962 0.87802 -0.03566
0.07926 -0.12823 0.47729 -0.20514 0.88660 -0.03319
0.08391 -0.13218 0.49065 -0.20038 0.89498 -0.03094
0.08884 -0.13633 0.50372 -0.19538 0.90316 -0.02893
0.09406 -0.14065 0.51653 -0.19020 0.91115 -0.02716
0.09957 -0.14512 0.52909 -0.18485 0.91894 -0.02564
0.10537 -0.14974 0.54141 -0.17939 0.92655 -0.02436
0.11147 -0.15448 0.55353 -0.17383 0.93398 -0.02334
0.11787 -0.15931 0.56547 -0.16821 0.94124 -0.02256
0.12460 -0.16421 0.57725 -0.16257 0.94832 -0.02202
0.13165 -0.16917 0.58892 -0.15691 0.95523 -0.02171
0.13906 -0.17415 0.60049 -0.15126 0.96197 -0.02163
0.14685 -0.17913 0.61199 -0.14564 0.96854 -0.02176
0.15503 -0.18409 0.62344 -0.14006 0.97484 -0.02207
0.16363 -0.18898 0.63486 -0.13454 0.98113 -0.02257
0.17267 -0.19379 0.64627 -0.12908 0.98742 -0.02325
0.18217 -0.19848 0.65766 -0.12370 0.99371 -0.02407
0.19215 -0.20301 0.66905 -0.11840 1.00000 -0.02500
0.20262 -0.20734 0.68044 -0.11320 ? ?
Wherein, on the pressure side of x/c value representation first aerofoil profile 150 certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of certain point and the ratio of chord length c on the y/c value is then represented from the string of a musical instrument to first aerofoil profile, 150 pressure sides.
Fig. 4 has shown second aerofoil profile 160 of the wind energy conversion system special airfoil A of family, and its leading edge is 161, and the string of a musical instrument is 162, and suction surface is 163, and trailing edge is 164, and pressure side is 165.The thickness of this aerofoil profile is 50%, is applicable to the medial area 110 of blade B.This aerofoil profile at reynolds' number 3 * 10 6Operating mode design, with other aerofoil profiles among the wind energy conversion system special airfoil A of family have good how much compatible.The concrete shape of second aerofoil profile 160 provides with the dimensionless coordinate form in table 3,4.
The table 3 second aerofoil profile suction surface
x/c y/c x/c y/c x/c y/c
1.00000 0.03500 0.70467 0.15528 0.22093 0.23331
0.99518 0.03681 0.69209 0.16022 0.21234 0.23060
0.99036 0.03876 0.67927 0.16522 0.20391 0.22771
0.98553 0.04073 0.66622 0.17027 0.19563 0.22463
0.98071 0.04270 0.65295 0.17535 0.18751 0.22138
0.97589 0.04466 0.63943 0.18045 0.17956 0.21797
0.97091 0.04669 0.62567 0.18556 0.17178 0.21441
0.96576 0.04877 0.61168 0.19064 0.16421 0.21071
0.96045 0.05093 0.59744 0.19568 0.15686 0.20691
0.95496 0.05315 0.58296 0.20064 0.14976 0.20302
0.94929 0.05545 0.56826 0.20551 0.14295 0.19907
0.94342 0.05784 0.55334 0.21023 0.13645 0.19509
0.93736 0.06031 0.53823 0.21479 0.13029 0.19113
0.93108 0.06288 0.52296 0.21914 0.12448 0.18722
0.92459 0.06555 0.50756 0.22327 0.11905 0.18341
0.91787 0.06833 0.49208 0.22713 0.11400 0.17972
0.91092 0.07121 0.47658 0.23070 0.10933 0.17620
0.90373 0.07420 0.46111 0.23397 0.10503 0.17287
0.89629 0.07730 0.44574 0.23691 0.10107 0.16972
0.88860 0.08052 0.43053 0.23950 0.09739 0.16674
0.88065 0.08385 0.41554 0.24176 0.09394 0.16389
0.87244 0.08729 0.40083 0.24366 0.09063 0.16108
0.86396 0.09084 0.38647 0.24522 0.08733 0.15819
0.85520 0.09449 0.37250 0.24644 0.08391 0.15508
0.84617 0.09825 0.35895 0.24732 0.08020 0.15155
0.83687 0.10211 0.34585 0.24789 0.07603 0.14735
0.82728 0.10607 0.33323 0.24814 0.07120 0.14221
0.81742 0.11012 0.32108 0.24809 0.06552 0.13584
0.80729 0.11426 0.30941 0.24774 0.05882 0.12793
0.79690 0.11848 0.29818 0.24712 0.05098 0.11817
0.78623 0.12280 0.28739 0.24624 0.04199 0.10624
0.77531 0.12720 0.27699 0.24509 0.03201 0.09182
0.76414 0.13168 0.26696 0.24370 0.02155 0.07453
0.75272 0.13624 0.25725 0.24206 0.01160 0.05393
0.74106 0.14089 0.24782 0.24020 0.00376 0.02939
0.72916 0.14561 0.23865 0.23811 0.00000 0.00000
0.71703 0.15041 0.22970 0.23581
Wherein, on the suction surface of x/c value representation second aerofoil profile 160 certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of certain point and the ratio of chord length c on the y/c value is then represented from the string of a musical instrument to second aerofoil profile, 160 suction surfaces;
The table 4 second aerofoil profile pressure side
x/c y/c x/c y/c x/c y/c
0.00000 0.00000 0.25119 -0.24188 0.72650 -0.10020
0.00098 -0.01534 0.26444 -0.24519 0.73798 -0.09527
0.00392 -0.02842 0.27790 -0.24788 0.74922 -0.09051
0.00787 -0.03981 0.29152 -0.24993 0.76021 -0.08592
0.01224 -0.04985 0.30524 -0.25132 0.77095 -0.08152
0.01674 -0.05877 0.31900 -0.25203 0.78144 -0.07730
0.02119 -0.06673 0.33275 -0.25209 0.79169 -0.07328
0.02550 -0.07386 0.34644 -0.25149 0.80169 -0.06946
0.02966 -0.08029 0.36002 -0.25026 0.81145 -0.06583
0.03369 -0.08614 0.37346 -0.24842 0.82098 -0.06240
0.03763 -0.09152 0.38674 -0.24601 0.83028 -0.05918
0.04154 -0.09656 0.39984 -0.24307 0.83936 -0.05615
0.04550 -0.10137 0.41277 -0.23963 0.84822 -0.05332
0.04956 -0.10604 0.42554 -0.23574 0.85686 -0.05069
0.05378 -0.11068 0.43816 -0.23143 0.86529 -0.04825
0.05822 -0.11536 0.45067 -0.22677 0.87352 -0.04599
0.06292 -0.12013 0.46309 -0.22178 0.88154 -0.04392
0.06793 -0.12507 0.47546 -0.21651 0.88937 -0.04202
0.07327 -0.13019 0.48781 -0.21101 0.89700 -0.04029
0.07896 -0.13553 0.50018 -0.20531 0.90445 -0.03873
0.08502 -0.14110 0.51260 -0.19945 0.91170 -0.03732
0.09147 -0.14689 0.52509 -0.19346 0.91877 -0.03607
0.09831 -0.15291 0.53766 -0.18739 0.92567 -0.03497
0.10555 -0.15912 0.55031 -0.18126 0.93239 -0.03401
0.11320 -0.16552 0.56306 -0.17510 0.93894 -0.03320
0.12127 -0.17205 0.57589 -0.16893 0.94532 -0.03253
0.12976 -0.17867 0.58877 -0.16277 0.95154 -0.03202
0.13867 -0.18535 0.60169 -0.15665 0.95760 -0.03165
0.14802 -0.19203 0.61463 -0.15058 0.96352 -0.03145
0.15780 -0.19864 0.62754 -0.14457 0.96929 -0.03142
0.16802 -0.20513 0.64040 -0.13863 0.97493 -0.03157
0.17868 -0.21144 0.65317 -0.13279 0.97994 -0.03188
0.18978 -0.21750 0.66583 -0.12705 0.98496 -0.03237
0.20130 -0.22324 0.67834 -0.12141 0.98997 -0.03304
0.21323 -0.22861 0.69069 -0.11590 0.99499 -0.03391
0.22554 -0.23354 0.70284 -0.11052 1.00000 -0.03500
0.23821 -0.23798 0.71478 -0.10529
Wherein, on the pressure side of x/c value representation second aerofoil profile 160 certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of certain point and the ratio of chord length c on the y/c value is then represented from the string of a musical instrument to second aerofoil profile, 160 pressure sides.
Fig. 5 has shown the 3rd aerofoil profile 170 of the wind energy conversion system special airfoil A of family, and its leading edge is 171, and the string of a musical instrument is 172, and suction surface is 173, and trailing edge is 174, and pressure side is 175.The thickness of this aerofoil profile is 55%, is applicable to the medial area 110 of blade B.This aerofoil profile at reynolds' number 3 * 10 6Operating mode design, with other aerofoil profiles among the wind energy conversion system special airfoil A of family have good how much compatible.The concrete shape of the 3rd aerofoil profile 170 provides with the dimensionless coordinate form in table 5,6.
Table 5 the 3rd aerofoil profile suction surface
x/c y/c x/c y/c x/c y/c
1.00000 0.04500 0.67907 0.19104 0.23077 0.25606
0.99411 0.04743 0.66581 0.19610 0.22202 0.25319
0.98899 0.04984 0.65237 0.20112 0.21329 0.25007
0.98389 0.05226 0.63875 0.20607 0.20462 0.24670
0.97877 0.05466 0.62499 0.21093 0.19600 0.24310
0.97366 0.05708 0.61108 0.21569 0.18745 0.23927
0.96790 0.05983 0.59706 0.22033 0.17900 0.23525
0.96199 0.06266 0.58294 0.22483 0.17066 0.23106
0.95592 0.06560 0.56876 0.22918 0.16250 0.22669
0.94968 0.06864 0.55454 0.23335 0.15453 0.22220
0.94327 0.07180 0.54030 0.23733 0.14679 0.21761
0.93665 0.07505 0.52608 0.24112 0.13931 0.21292
0.92985 0.07843 0.51191 0.24470 0.13213 0.20819
0.92283 0.08190 0.49782 0.24806 0.12526 0.20342
0.91559 0.08549 0.48385 0.25119 0.11873 0.19863
0.90814 0.08917 0.47002 0.25409 0.11252 0.19384
0.90045 0.09297 0.45637 0.25675 0.10663 0.18904
0.89253 0.09685 0.44292 0.25917 0.10104 0.18424
0.88436 0.10084 0.42971 0.26136 0.09568 0.17940
0.87594 0.10492 0.41676 0.26329 0.09053 0.17448
0.86726 0.10909 0.40410 0.26499 0.08551 0.16944
0.85832 0.11336 0.39173 0.26646 0.08054 0.16421
0.84912 0.11772 0.37967 0.26768 0.07553 0.15869
0.83964 0.12216 0.36794 0.26866 0.07040 0.15280
0.82990 0.12668 0.35653 0.26940 0.06504 0.14641
0.81988 0.13129 0.34543 0.26990 0.05937 0.13940
0.80958 0.13598 0.33466 0.27016 0.05334 0.13162
0.79901 0.14074 0.32418 0.27017 0.04689 0.12296
0.78817 0.14558 0.31400 0.26993 0.04005 0.11323
0.77706 0.15047 0.30406 0.26944 0.03287 0.10232
0.76567 0.15543 0.29437 0.26871 0.02549 0.09005
0.75404 0.16045 0.28488 0.26769 0.01815 0.07625
0.74213 0.16550 0.27557 0.26642 0.01124 0.06071
0.72999 0.17059 0.26642 0.26489 0.00530 0.04313
0.71759 0.17569 0.25738 0.26309 0.00117 0.02310
0.70497 0.18082 0.24845 0.26102 0.00000 0.00000
0.69212 0.18593 0.23958 0.25867
Wherein, on the suction surface of x/c value representation the 3rd aerofoil profile 170 certain point with respect to the length x of leading edge and the ratio of chord length c, the y/c value is then represented the height y of certain point from the string of a musical instrument to the three aerofoil profiles 170 suction surfaces and the ratio of chord length c on string of a musical instrument direction;
Table 6 the 3rd aerofoil profile pressure side
x/c y/c x/c y/c x/c y/c
0.00000 0.00000 0.23785 -0.26460 0.71665 -0.11547
0.00234 -0.02054 0.25061 -0.26894 0.72744 -0.11042
0.00703 -0.03803 0.26375 -0.27264 0.73808 -0.10551
0.01307 -0.05310 0.27724 -0.27563 0.74854 -0.10075
0.01970 -0.06618 0.29102 -0.27789 0.75882 -0.09614
0.02645 -0.07765 0.30502 -0.27936 0.76892 -0.09168
0.03299 -0.08776 0.31918 -0.28003 0.77885 -0.08737
0.03915 -0.09672 0.33347 -0.27993 0.78862 -0.08322
0.04484 -0.10471 0.34782 -0.27902 0.79820 -0.07923
0.05006 -0.11184 0.36216 -0.27737 0.80762 -0.07542
0.05487 -0.11825 0.37648 -0.27497 0.81685 -0.07178
0.05932 -0.12404 0.39072 -0.27188 0.82593 -0.06833
0.06350 -0.12932 0.40488 -0.26816 0.83484 -0.06506
0.06749 -0.13419 0.41889 -0.26384 0.84358 -0.06199
0.07136 -0.13873 0.43278 -0.25898 0.85216 -0.05913
0.07522 -0.14304 0.44650 -0.25366 0.86058 -0.05648
0.07910 -0.14722 0.46009 -0.24794 0.86884 -0.05403
0.08309 -0.15134 0.47350 -0.24186 0.87694 -0.05181
0.08724 -0.15550 0.48678 -0.23551 0.88488 -0.04980
0.09159 -0.15975 0.49992 -0.22895 0.89266 -0.04800
0.09618 -0.16418 0.51292 -0.22221 0.90029 -0.04643
0.10106 -0.16881 0.52578 -0.21537 0.90776 -0.04506
0.10625 -0.17372 0.53854 -0.20846 0.91510 -0.04389
0.11179 -0.17889 0.55117 -0.20153 0.92228 -0.04291
0.11769 -0.18438 0.56371 -0.19463 0.92933 -0.04212
0.12400 -0.19014 0.57614 -0.18778 0.93623 -0.04152
0.13072 -0.19619 0.58848 -0.18100 0.94299 -0.04108
0.13790 -0.20247 0.60072 -0.17433 0.94963 -0.04080
0.14555 -0.20897 0.61286 -0.16777 0.95612 -0.04068
0.15369 -0.21561 0.62489 -0.16136 0.96249 -0.04071
0.16235 -0.22232 0.63681 -0.15508 0.96873 -0.04087
0.17154 -0.22903 0.64863 -0.14897 0.97509 -0.04121
0.18126 -0.23568 0.66031 -0.14300 0.98146 -0.04173
0.19154 -0.24214 0.67187 -0.13719 0.98782 -0.04249
0.20235 -0.24836 0.68330 -0.13153 0.99419 -0.04356
0.21369 -0.25423 0.69456 -0.12602 1.00000 -0.04500
0.22553 -0.25967 0.70569 -0.12068
Wherein, on the pressure side of x/c value representation the 3rd aerofoil profile 170 certain point with respect to the length x of leading edge and the ratio of chord length c, the y/c value is then represented the height y of certain point from the string of a musical instrument to the three aerofoil profiles 170 pressure sides and the ratio of chord length c on string of a musical instrument direction.
Fig. 6 has shown the 4th aerofoil profile 180 of the wind energy conversion system special airfoil A of family, and its leading edge is 181, and the string of a musical instrument is 182, and suction surface is 183, and trailing edge is 184, and pressure side is 185.The thickness of this aerofoil profile is 60%, is applicable to the medial area 110 of blade B.This aerofoil profile at reynolds' number 3 * 10 6Operating mode design, with other aerofoil profiles among the wind energy conversion system special airfoil A of family have good how much compatible.The concrete shape of the 4th aerofoil profile 180 provides with the dimensionless coordinate form in table 7,8.
Table 7 the 4th aerofoil profile suction surface
x/c y/c x/c y/c x/c y/c
1.00000 0.05500 0.63406 0.22843 0.22839 0.27607
0.99276 0.05870 0.62145 0.23310 0.22028 0.27285
0.98552 0.06236 0.60886 0.23765 0.21227 0.26940
0.97827 0.06598 0.59632 0.24208 0.20438 0.26576
0.97103 0.06955 0.58384 0.24639 0.19661 0.26195
0.96379 0.07309 0.57143 0.25057 0.18897 0.25797
0.95655 0.07661 0.55911 0.25461 0.18148 0.25387
0.94724 0.08109 0.54687 0.25851 0.17417 0.24968
0.93798 0.08554 0.53471 0.26226 0.16707 0.24543
0.92876 0.08996 0.52263 0.26586 0.16021 0.24116
0.91958 0.09437 0.51063 0.26929 0.15363 0.23690
0.91044 0.09879 0.49869 0.27255 0.14735 0.23271
0.90133 0.10323 0.48680 0.27563 0.14142 0.22860
0.89224 0.10769 0.47497 0.27851 0.13584 0.22463
0.88315 0.11221 0.46319 0.28120 0.13063 0.22081
0.87403 0.11677 0.45144 0.28367 0.12579 0.21716
0.86488 0.12140 0.43975 0.28593 0.12131 0.21368
0.85567 0.12611 0.42810 0.28796 0.11716 0.21037
0.84636 0.13089 0.41652 0.28976 0.11329 0.20718
0.83695 0.13575 0.40502 0.29131 0.10964 0.20406
0.82739 0.14069 0.39362 0.29263 0.10610 0.20092
0.81768 0.14571 0.38234 0.29369 0.10256 0.19765
0.80778 0.15080 0.37119 0.29450 0.09889 0.19410
0.79769 0.15597 0.36021 0.29506 0.09492 0.19010
0.78737 0.16119 0.34940 0.29537 0.09047 0.18544
0.77682 0.16647 0.33880 0.29542 0.08535 0.17987
0.76603 0.17178 0.32842 0.29522 0.07937 0.17313
0.75499 0.17711 0.31826 0.29475 0.07237 0.16493
0.74372 0.18245 0.30834 0.29404 0.06421 0.15494
0.73220 0.18778 0.29865 0.29306 0.05486 0.14283
0.72047 0.19309 0.28920 0.29183 0.04440 0.12821
0.70853 0.19836 0.27996 0.29034 0.03314 0.11069
0.69641 0.20358 0.27094 0.28860 0.02169 0.08977
0.68413 0.20872 0.26211 0.28659 0.01113 0.06488
0.67172 0.21379 0.25346 0.28434 0.00037 0.01707
0.65922 0.21877 0.24497 0.28183 0.00006 0.00947
0.64666 0.22366 0.23661 0.27907 0.00000 0.00000
Wherein, on the suction surface of x/c value representation the 4th aerofoil profile 180 certain point with respect to the length x of leading edge and the ratio of chord length c, the y/c value is then represented the height y of certain point from the string of a musical instrument to the four aerofoil profiles 180 suction surfaces and the ratio of chord length c on string of a musical instrument direction;
Table 8 the 4th aerofoil profile pressure side
x/c y/c x/c y/c x/c y/c
0.00000 0.00000 0.24121 -0.28922 0.66910 -0.16108
0.00029 -0.00580 0.25278 -0.29329 0.67886 -0.15540
0.00092 -0.01344 0.26452 -0.29677 0.68858 -0.14982
0.00186 -0.02108 0.27639 -0.29964 0.69827 -0.14432
0.00647 -0.03926 0.28834 -0.30189 0.70796 -0.13893
0.01233 -0.05497 0.30034 -0.30351 0.71766 -0.13364
0.01875 -0.06882 0.31235 -0.30450 0.72739 -0.12846
0.02527 -0.08116 0.32434 -0.30489 0.73716 -0.12338
0.03159 -0.09220 0.33628 -0.30468 0.74697 -0.11842
0.03757 -0.10210 0.34815 -0.30390 0.75683 -0.11357
0.04316 -0.11102 0.35995 -0.30257 0.76674 -0.10883
0.04837 -0.11907 0.37168 -0.30073 0.77669 -0.10421
0.05325 -0.12639 0.38332 -0.29841 0.78668 -0.09971
0.05787 -0.13310 0.39490 -0.29563 0.79668 -0.09532
0.06233 -0.13933 0.40641 -0.29244 0.80669 -0.09106
0.06670 -0.14520 0.41788 -0.28887 0.81668 -0.08692
0.07109 -0.15083 0.42931 -0.28494 0.82664 -0.08291
0.07555 -0.15634 0.44072 -0.28069 0.83655 -0.07903
0.08016 -0.16183 0.45213 -0.27616 0.84639 -0.07530
0.08497 -0.16738 0.46353 -0.27137 0.85613 -0.07172
0.09003 -0.17305 0.47493 -0.26635 0.86577 -0.06832
0.09537 -0.17891 0.48634 -0.26112 0.87528 -0.06511
0.10102 -0.18499 0.49774 -0.25572 0.88464 -0.06211
0.10700 -0.19130 0.50913 -0.25017 0.89385 -0.05935
0.11333 -0.19785 0.52049 -0.24448 0.90288 -0.05686
0.12002 -0.20462 0.53182 -0.23868 0.91174 -0.05465
0.12708 -0.21158 0.54308 -0.23279 0.92039 -0.05276
0.13452 -0.21870 0.55427 -0.22682 0.92884 -0.05122
0.14234 -0.22591 0.56536 -0.22081 0.93705 -0.05005
0.15056 -0.23317 0.57634 -0.21476 0.94503 -0.04927
0.15917 -0.24040 0.58719 -0.20869 0.95273 -0.04890
0.16817 -0.24754 0.59790 -0.20262 0.96218 -0.04900
0.17756 -0.25451 0.60847 -0.19656 0.97164 -0.04975
0.18733 -0.26126 0.61890 -0.19052 0.98109 -0.05114
0.19747 -0.26770 0.62918 -0.18451 0.99055 -0.05302
0.20795 -0.27377 0.63933 -0.17856 1.00000 -0.05500
0.21876 -0.27941 0.64935 -0.17266
0.22986 -0.28458 0.65927 -0.16683
Wherein, on the pressure side of x/c value representation the 4th aerofoil profile 180 certain point with respect to the length x of leading edge and the ratio of chord length c, the y/c value is then represented the height y of certain point from the string of a musical instrument to the four aerofoil profiles 180 pressure sides and the ratio of chord length c on string of a musical instrument direction.
The above; it only is preferred embodiment of the present utility model; protection domain of the present utility model is not limited thereto; any people who is familiar with this technology can understand conversion or the replacement of expecting in the disclosed technical scope of the utility model; all should be encompassed in of the present utility model comprising within the scope; therefore, protection domain of the present utility model should be as the criterion with the protection domain of claims.

Claims (8)

1. wind turbine blade airfoil family, described family of aerofoil sections (A) comprises the aerofoil profile (150,160,170,180) of first to fourth different relative thicknesses, described relative thickness is ultimate range between each aerofoil profile upper and lower surfaces and the ratio of chord length c, described chord length c is the length of aerofoil profile leading edge to the string of a musical instrument (A40) of trailing edge, it is characterized in that:
Each aerofoil profile is formed by leading edge (A00), trailing edge (A10), suction surface (A20), pressure side (A30);
The trailing edge thickness of described family of aerofoil sections (A) is 5% ~ 11% chord length;
The pressure side of described family of aerofoil sections (A) is to load after the S shape;
The relative thickness of described family of aerofoil sections (A) is 45%-60%;
The position of the maximum relative thickness of described family of aerofoil sections (A) is at distance leading edge 32.1% ~ 33.2% chord length place;
Wherein, the geometric shape of each aerofoil profile forms the abscissa that described dimensionless two-dimensional coordinate is an each point and the ratio of y coordinate and chord length by the dimensionless two-dimensional coordinate smooth connection of each point on pressure side and the suction surface.
2. wind turbine blade airfoil family according to claim 1, wherein, the suction surface of first aerofoil profile (150) and the dimensionless two-dimensional coordinate of pressure side are respectively:
First aerofoil profile (150) suction surface
x/c y/c x/c y/c x/c y/c 1.00000 0.02500 0.67180 0.15305 0.22271 0.20538 0.99376 0.02753 0.65814 0.15764 0.21309 0.20269 0.98753 0.03005 0.64416 0.16217 0.20344 0.19975 0.98129 0.03257 0.62988 0.16662 0.19379 0.19656 0.97505 0.03510 0.61535 0.17096 0.18418 0.19314 0.96882 0.03761 0.60059 0.17517 0.17463 0.18948 0.96196 0.04038 0.58566 0.17923 0.16520 0.18561 0.95499 0.04318 0.57062 0.18312 0.15593 0.18156 0.94791 0.04602 0.55551 0.18681 0.14687 0.17733 0.94072 0.04890 0.54039 0.19031 0.13807 0.17297 0.93344 0.05182 0.52534 0.19360 0.12956 0.16852 0.92605 0.05478 0.51041 0.19667 0.12141 0.16400 0.91856 0.05778 0.49565 0.19953 0.11365 0.15946 0.91096 0.06082 0.48114 0.20218 0.10631 0.15494 0.90326 0.06390 0.46691 0.20462 0.09943 0.15048 0.89545 0.06703 0.45302 0.20686 0.09301 0.14612 0.88751 0.07020 0.43949 0.20890 0.08708 0.14189 0.87946 0.07341 0.42637 0.21075 0.08161 0.13782 0.87127 0.07668 0.41366 0.21241 0.07662 0.13390 0.86293 0.07999 0.40138 0.21389 0.07205 0.13013 0.85444 0.08337 0.38953 0.21518 0.06786 0.12650 0.84578 0.08680 0.37809 0.21628 0.06400 0.12296 0.83693 0.09031 0.36705 0.21720 0.06038 0.11946 0.82789 0.09389 0.35638 0.21793 0.05689 0.11589 0.81863 0.09754 0.34604 0.21847 0.05343 0.11217 0.80914 0.10129 0.33599 0.21880 0.04984 0.10815 0.79940 0.10513 0.32618 0.21893 0.04600 0.10367 0.78940 0.10907 0.31658 0.21885 0.04177 0.09855 0.77912 0.11310 0.30712 0.21855 0.03702 0.09257 0.76854 0.11723 0.29777 0.21803 0.03168 0.08548 0.75765 0.12147 0.28847 0.21728 0.02577 0.07702 0.74643 0.12579 0.27920 0.21630 0.01939 0.06686 0.73488 0.13021 0.26992 0.21509 0.01286 0.05461 0.72298 0.13469 0.26060 0.21364 0.00672 0.03983
0.71072 0.13924 0.25122 0.21195 0.00190 0.02189 0.69810 0.14383 0.24178 0.21001 0.00000 0.00000 0.68513 0.14844 0.23228 0.20782 ? ?
Wherein, on the suction surface of x/c value representation first aerofoil profile (150) certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of certain point and the ratio of chord length c on the y/c value is then represented from the string of a musical instrument to first aerofoil profile (150) suction surface;
First aerofoil profile (150) pressure side
x/c y/c x/c y/c x/c y/c 0.00000 0.00000 0.21360 -0.21144 0.69181 -0.10808 0.00221 -0.01909 0.22507 -0.21526 0.70316 -0.10306 0.00704 -0.03485 0.23705 -0.21876 0.71447 -0.09813 0.01306 -0.04805 0.24951 -0.22189 0.72574 -0.09330 0.01935 -0.05916 0.26243 -0.22463 0.73694 -0.08857 0.02536 -0.06853 0.27578 -0.22692 0.74805 -0.08394 0.03083 -0.07643 0.28952 -0.22873 0.75906 -0.07942 0.03568 -0.08308 0.30360 -0.23004 0.76996 -0.07501 0.03997 -0.08869 0.31797 -0.23081 0.78071 -0.07070 0.04378 -0.09348 0.33257 -0.23104 0.79131 -0.06652 0.04724 -0.09763 0.34732 -0.23071 0.80175 -0.06246 0.05049 -0.10131 0.36217 -0.22982 0.81200 -0.05853 0.05363 -0.10469 0.37704 -0.22838 0.82205 -0.05475 0.05677 -0.10789 0.39187 -0.22641 0.83191 -0.05112 0.06000 -0.11103 0.40661 -0.22394 0.84156 -0.04766 0.06339 -0.11420 0.42119 -0.22098 0.85100 -0.04437 0.06697 -0.11747 0.43559 -0.21759 0.86022 -0.04126 0.07080 -0.12088 0.44975 -0.21378 0.86922 -0.03836 0.07489 -0.12446 0.46365 -0.20962 0.87802 -0.03566 0.07926 -0.12823 0.47729 -0.20514 0.88660 -0.03319 0.08391 -0.13218 0.49065 -0.20038 0.89498 -0.03094 0.08884 -0.13633 0.50372 -0.19538 0.90316 -0.02893 0.09406 -0.14065 0.51653 -0.19020 0.91115 -0.02716 0.09957 -0.14512 0.52909 -0.18485 0.91894 -0.02564 0.10537 -0.14974 0.54141 -0.17939 0.92655 -0.02436 0.11147 -0.15448 0.55353 -0.17383 0.93398 -0.02334 0.11787 -0.15931 0.56547 -0.16821 0.94124 -0.02256 0.12460 -0.16421 0.57725 -0.16257 0.94832 -0.02202 0.13165 -0.16917 0.58892 -0.15691 0.95523 -0.02171 0.13906 -0.17415 0.60049 -0.15126 0.96197 -0.02163 0.14685 -0.17913 0.61199 -0.14564 0.96854 -0.02176 0.15503 -0.18409 0.62344 -0.14006 0.97484 -0.02207 0.16363 -0.18898 0.63486 -0.13454 0.98113 -0.02257 0.17267 -0.19379 0.64627 -0.12908 0.98742 -0.02325 0.18217 -0.19848 0.65766 -0.12370 0.99371 -0.02407 0.19215 -0.20301 0.66905 -0.11840 1.00000 -0.02500 0.20262 -0.20734 0.68044 -0.11320
Wherein, on the pressure side of x/c value representation first aerofoil profile (150) certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of certain point and the ratio of chord length c on the y/c value is then represented from the string of a musical instrument to first aerofoil profile (150) pressure side.
3. wind turbine blade airfoil family according to claim 1, wherein, the dimensionless two-dimensional coordinate of second aerofoil profile (160) suction surface and pressure side is respectively:
Second aerofoil profile (160) suction surface
x/c y/c x/c y/c x/c y/c 1.00000 0.03500 0.70467 0.15528 0.22093 0.23331 0.99518 0.03681 0.69209 0.16022 0.21234 0.23060 0.99036 0.03876 0.67927 0.16522 0.20391 0.22771 0.98553 0.04073 0.66622 0.17027 0.19563 0.22463 0.98071 0.04270 0.65295 0.17535 0.18751 0.22138 0.97589 0.04466 0.63943 0.18045 0.17956 0.21797 0.97091 0.04669 0.62567 0.18556 0.17178 0.21441 0.96576 0.04877 0.61168 0.19064 0.16421 0.21071 0.96045 0.05093 0.59744 0.19568 0.15686 0.20691 0.95496 0.05315 0.58296 0.20064 0.14976 0.20302 0.94929 0.05545 0.56826 0.20551 0.14295 0.19907 0.94342 0.05784 0.55334 0.21023 0.13645 0.19509 0.93736 0.06031 0.53823 0.21479 0.13029 0.19113 0.93108 0.06288 0.52296 0.21914 0.12448 0.18722 0.92459 0.06555 0.50756 0.22327 0.11905 0.18341 0.91787 0.06833 0.49208 0.22713 0.11400 0.17972 0.91092 0.07121 0.47658 0.23070 0.10933 0.17620 0.90373 0.07420 0.46111 0.23397 0.10503 0.17287 0.89629 0.07730 0.44574 0.23691 0.10107 0.16972 0.88860 0.08052 0.43053 0.23950 0.09739 0.16674 0.88065 0.08385 0.41554 0.24176 0.09394 0.16389 0.87244 0.08729 0.40083 0.24366 0.09063 0.16108 0.86396 0.09084 0.38647 0.24522 0.08733 0.15819 0.85520 0.09449 0.37250 0.24644 0.08391 0.15508 0.84617 0.09825 0.35895 0.24732 0.08020 0.15155 0.83687 0.10211 0.34585 0.24789 0.07603 0.14735 0.82728 0.10607 0.33323 0.24814 0.07120 0.14221 0.81742 0.11012 0.32108 0.24809 0.06552 0.13584 0.80729 0.11426 0.30941 0.24774 0.05882 0.12793 0.79690 0.11848 0.29818 0.24712 0.05098 0.11817 0.78623 0.12280 0.28739 0.24624 0.04199 0.10624 0.77531 0.12720 0.27699 0.24509 0.03201 0.09182 0.76414 0.13168 0.26696 0.24370 0.02155 0.07453 0.75272 0.13624 0.25725 0.24206 0.01160 0.05393 0.74106 0.14089 0.24782 0.24020 0.00376 0.02939 0.72916 0.14561 0.23865 0.23811 0.00000 0.00000 0.71703 0.15041 0.22970 0.23581
Wherein, on the suction surface of x/c value representation second aerofoil profile (160) certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of certain point and the ratio of chord length c on the y/c value is then represented from the string of a musical instrument to second aerofoil profile (160) suction surface;
Second aerofoil profile (160) pressure side
x/c y/c x/c y/c x/c y/c 0.00000 0.00000 0.25119 -0.24188 0.72650 -0.10020 0.00098 -0.01534 0.26444 -0.24519 0.73798 -0.09527 0.00392 -0.02842 0.27790 -0.24788 0.74922 -0.09051 0.00787 -0.03981 0.29152 -0.24993 0.76021 -0.08592 0.01224 -0.04985 0.30524 -0.25132 0.77095 -0.08152 0.01674 -0.05877 0.31900 -0.25203 0.78144 -0.07730
0.02119 -0.06673 0.33275 -0.25209 0.79169 -0.07328 0.02550 -0.07386 0.34644 -0.25149 0.80169 -0.06946 0.02966 -0.08029 0.36002 -0.25026 0.81145 -0.06583 0.03369 -0.08614 0.37346 -0.24842 0.82098 -0.06240 0.03763 -0.09152 0.38674 -0.24601 0.83028 -0.05918 0.04154 -0.09656 0.39984 -0.24307 0.83936 -0.05615 0.04550 -0.10137 0.41277 -0.23963 0.84822 -0.05332 0.04956 -0.10604 0.42554 -0.23574 0.85686 -0.05069 0.05378 -0.11068 0.43816 -0.23143 0.86529 -0.04825 0.05822 -0.11536 0.45067 -0.22677 0.87352 -0.04599 0.06292 -0.12013 0.46309 -0.22178 0.88154 -0.04392 0.06793 -0.12507 0.47546 -0.21651 0.88937 -0.04202 0.07327 -0.13019 0.48781 -0.21101 0.89700 -0.04029 0.07896 -0.13553 0.50018 -0.20531 0.90445 -0.03873 0.08502 -0.14110 0.51260 -0.19945 0.91170 -0.03732 0.09147 -0.14689 0.52509 -0.19346 0.91877 -0.03607 0.09831 -0.15291 0.53766 -0.18739 0.92567 -0.03497 0.10555 -0.15912 0.55031 -0.18126 0.93239 -0.03401 0.11320 -0.16552 0.56306 -0.17510 0.93894 -0.03320 0.12127 -0.17205 0.57589 -0.16893 0.94532 -0.03253 0.12976 -0.17867 0.58877 -0.16277 0.95154 -0.03202 0.13867 -0.18535 0.60169 -0.15665 0.95760 -0.03165 0.14802 -0.19203 0.61463 -0.15058 0.96352 -0.03145 0.15780 -0.19864 0.62754 -0.14457 0.96929 -0.03142 0.16802 -0.20513 0.64040 -0.13863 0.97493 -0.03157 0.17868 -0.21144 0.65317 -0.13279 0.97994 -0.03188 0.18978 -0.21750 0.66583 -0.12705 0.98496 -0.03237 0.20130 -0.22324 0.67834 -0.12141 0.98997 -0.03304 0.21323 -0.22861 0.69069 -0.11590 0.99499 -0.03391 0.22554 -0.23354 0.70284 -0.11052 1.00000 -0.03500 0.23821 -0.23798 0.71478 -0.10529
Wherein, on the pressure side of x/c value representation second aerofoil profile (160) certain the point on string of a musical instrument direction with respect to the length x of leading edge and the ratio of chord length c, the height y of certain point and the ratio of chord length c on the y/c value is then represented from the string of a musical instrument to second aerofoil profile (160) pressure side.
4. wind turbine blade airfoil family according to claim 1, wherein, the dimensionless two-dimensional coordinate of the 3rd aerofoil profile (170) suction surface and pressure side is respectively:
The 3rd aerofoil profile (170) suction surface
x/c y/c x/c y/c x/c y/c 1.00000 0.04500 0.67907 0.19104 0.23077 0.25606 0.99411 0.04743 0.66581 0.19610 0.22202 0.25319 0.98899 0.04984 0.65237 0.20112 0.21329 0.25007 0.98389 0.05226 0.63875 0.20607 0.20462 0.24670 0.97877 0.05466 0.62499 0.21093 0.19600 0.24310 0.97366 0.05708 0.61108 0.21569 0.18745 0.23927 0.96790 0.05983 0.59706 0.22033 0.17900 0.23525 0.96199 0.06266 0.58294 0.22483 0.17066 0.23106 0.95592 0.06560 0.56876 0.22918 0.16250 0.22669 0.94968 0.06864 0.55454 0.23335 0.15453 0.22220 0.94327 0.07180 0.54030 0.23733 0.14679 0.21761 0.93665 0.07505 0.52608 0.24112 0.13931 0.21292
0.92985 0.07843 0.51191 0.24470 0.13213 0.20819 0.92283 0.08190 0.49782 0.24806 0.12526 0.20342 0.91559 0.08549 0.48385 0.25119 0.11873 0.19863 0.90814 0.08917 0.47002 0.25409 0.11252 0.19384 0.90045 0.09297 0.45637 0.25675 0.10663 0.18904 0.89253 0.09685 0.44292 0.25917 0.10104 0.18424 0.88436 0.10084 0.42971 0.26136 0.09568 0.17940 0.87594 0.10492 0.41676 0.26329 0.09053 0.17448 0.86726 0.10909 0.40410 0.26499 0.08551 0.16944 0.85832 0.11336 0.39173 0.26646 0.08054 0.16421 0.84912 0.11772 0.37967 0.26768 0.07553 0.15869 0.83964 0.12216 0.36794 0.26866 0.07040 0.15280 0.82990 0.12668 0.35653 0.26940 0.06504 0.14641 0.81988 0.13129 0.34543 0.26990 0.05937 0.13940 0.80958 0.13598 0.33466 0.27016 0.05334 0.13162 0.79901 0.14074 0.32418 0.27017 0.04689 0.12296 0.78817 0.14558 0.31400 0.26993 0.04005 0.11323 0.77706 0.15047 0.30406 0.26944 0.03287 0.10232 0.76567 0.15543 0.29437 0.26871 0.02549 0.09005 0.75404 0.16045 0.28488 0.26769 0.01815 0.07625 0.74213 0.16550 0.27557 0.26642 0.01124 0.06071 0.72999 0.17059 0.26642 0.26489 0.00530 0.04313 0.71759 0.17569 0.25738 0.26309 0.00117 0.02310 0.70497 0.18082 0.24845 0.26102 0.00000 0.00000 0.69212 0.18593 0.23958 0.25867
Wherein, on the suction surface of x/c value representation the 3rd aerofoil profile (170) certain point with respect to the length x of leading edge and the ratio of chord length c, the y/c value is then represented the height y of certain point from the string of a musical instrument to the three aerofoil profiles (170) suction surface and the ratio of chord length c on string of a musical instrument direction;
The 3rd aerofoil profile (170) pressure side
x/c y/c x/c y/c x/c y/c 0.00000 0.00000 0.23785 -0.26460 0.71665 -0.11547 0.00234 -0.02054 0.25061 -0.26894 0.72744 -0.11042 0.00703 -0.03803 0.26375 -0.27264 0.73808 -0.10551 0.01307 -0.05310 0.27724 -0.27563 0.74854 -0.10075 0.01970 -0.06618 0.29102 -0.27789 0.75882 -0.09614 0.02645 -0.07765 0.30502 -0.27936 0.76892 -0.09168 0.03299 -0.08776 0.31918 -0.28003 0.77885 -0.08737 0.03915 -0.09672 0.33347 -0.27993 0.78862 -0.08322 0.04484 -0.10471 0.34782 -0.27902 0.79820 -0.07923 0.05006 -0.11184 0.36216 -0.27737 0.80762 -0.07542 0.05487 -0.11825 0.37648 -0.27497 0.81685 -0.07178 0.05932 -0.12404 0.39072 -0.27188 0.82593 -0.06833 0.06350 -0.12932 0.40488 -0.26816 0.83484 -0.06506 0.06749 -0.13419 0.41889 -0.26384 0.84358 -0.06199 0.07136 -0.13873 0.43278 -0.25898 0.85216 -0.05913 0.07522 -0.14304 0.44650 -0.25366 0.86058 -0.05648 0.07910 -0.14722 0.46009 -0.24794 0.86884 -0.05403 0.08309 -0.15134 0.47350 -0.24186 0.87694 -0.05181 0.08724 -0.15550 0.48678 -0.23551 0.88488 -0.04980 0.09159 -0.15975 0.49992 -0.22895 0.89266 -0.04800 0.09618 -0.16418 0.51292 -0.22221 0.90029 -0.04643
0.10106 -0.16881 0.52578 -0.21537 0.90776 -0.04506 0.10625 -0.17372 0.53854 -0.20846 0.91510 -0.04389 0.11179 -0.17889 0.55117 -0.20153 0.92228 -0.04291 0.11769 -0.18438 0.56371 -0.19463 0.92933 -0.04212 0.12400 -0.19014 0.57614 -0.18778 0.93623 -0.04152 0.13072 -0.19619 0.58848 -0.18100 0.94299 -0.04108 0.13790 -0.20247 0.60072 -0.17433 0.94963 -0.04080 0.14555 -0.20897 0.61286 -0.16777 0.95612 -0.04068 0.15369 -0.21561 0.62489 -0.16136 0.96249 -0.04071 0.16235 -0.22232 0.63681 -0.15508 0.96873 -0.04087 0.17154 -0.22903 0.64863 -0.14897 0.97509 -0.04121 0.18126 -0.23568 0.66031 -0.14300 0.98146 -0.04173 0.19154 -0.24214 0.67187 -0.13719 0.98782 -0.04249 0.20235 -0.24836 0.68330 -0.13153 0.99419 -0.04356 0.21369 -0.25423 0.69456 -0.12602 1.00000 -0.04500 0.22553 -0.25967 0.70569 -0.12068
Wherein, on the pressure side of x/c value representation the 3rd aerofoil profile (170) certain point with respect to the length x of leading edge and the ratio of chord length c, the y/c value is then represented the height y of certain point from the string of a musical instrument to the three aerofoil profiles (170) pressure side and the ratio of chord length c on string of a musical instrument direction.
5. wind turbine blade airfoil family according to claim 1, wherein, the dimensionless two-dimensional coordinate of the 4th aerofoil profile (180) suction surface and pressure side is respectively:
The 4th aerofoil profile (180) suction surface
x/c y/c x/c y/c x/c y/c 1.00000 0.05500 0.63406 0.22843 0.22839 0.27607 0.99276 0.05870 0.62145 0.23310 0.22028 0.27285 0.98552 0.06236 0.60886 0.23765 0.21227 0.26940 0.97827 0.06598 0.59632 0.24208 0.20438 0.26576 0.97103 0.06955 0.58384 0.24639 0.19661 0.26195 0.96379 0.07309 0.57143 0.25057 0.18897 0.25797 0.95655 0.07661 0.55911 0.25461 0.18148 0.25387 0.94724 0.08109 0.54687 0.25851 0.17417 0.24968 0.93798 0.08554 0.53471 0.26226 0.16707 0.24543 0.92876 0.08996 0.52263 0.26586 0.16021 0.24116 0.91958 0.09437 0.51063 0.26929 0.15363 0.23690 0.91044 0.09879 0.49869 0.27255 0.14735 0.23271 0.90133 0.10323 0.48680 0.27563 0.14142 0.22860 0.89224 0.10769 0.47497 0.27851 0.13584 0.22463 0.88315 0.11221 0.46319 0.28120 0.13063 0.22081 0.87403 0.11677 0.45144 0.28367 0.12579 0.21716 0.86488 0.12140 0.43975 0.28593 0.12131 0.21368 0.85567 0.12611 0.42810 0.28796 0.11716 0.21037 0.84636 0.13089 0.41652 0.28976 0.11329 0.20718 0.83695 0.13575 0.40502 0.29131 0.10964 0.20406 0.82739 0.14069 0.39362 0.29263 0.10610 0.20092 0.81768 0.14571 0.38234 0.29369 0.10256 0.19765 0.80778 0.15080 0.37119 0.29450 0.09889 0.19410 0.79769 0.15597 0.36021 0.29506 0.09492 0.19010 0.78737 0.16119 0.34940 0.29537 0.09047 0.18544 0.77682 0.16647 0.33880 0.29542 0.08535 0.17987 0.76603 0.17178 0.32842 0.29522 0.07937 0.17313
0.75499 0.17711 0.31826 0.29475 0.07237 0.16493 0.74372 0.18245 0.30834 0.29404 0.06421 0.15494 0.73220 0.18778 0.29865 0.29306 0.05486 0.14283 0.72047 0.19309 0.28920 0.29183 0.04440 0.12821 0.70853 0.19836 0.27996 0.29034 0.03314 0.11069 0.69641 0.20358 0.27094 0.28860 0.02169 0.08977 0.68413 0.20872 0.26211 0.28659 0.01113 0.06488 0.67172 0.21379 0.25346 0.28434 0.00037 0.01707 0.65922 0.21877 0.24497 0.28183 0.00006 0.00947 0.64666 0.22366 0.23661 0.27907 0.00000 0.00000
Wherein, on the suction surface of x/c value representation the 4th aerofoil profile (180) certain point with respect to the length x of leading edge and the ratio of chord length c, the y/c value is then represented the height y of certain point from the string of a musical instrument to the four aerofoil profiles (180) suction surface and the ratio of chord length c on string of a musical instrument direction;
The 4th aerofoil profile (180) pressure side
x/c y/c x/c y/c x/c y/c 0.00000 0.00000 0.24121 -0.28922 0.66910 -0.16108 0.00029 -0.00580 0.25278 -0.29329 0.67886 -0.15540 0.00092 -0.01344 0.26452 -0.29677 0.68858 -0.14982 0.00186 -0.02108 0.27639 -0.29964 0.69827 -0.14432 0.00647 -0.03926 0.28834 -0.30189 0.70796 -0.13893 0.01233 -0.05497 0.30034 -0.30351 0.71766 -0.13364 0.01875 -0.06882 0.31235 -0.30450 0.72739 -0.12846 0.02527 -0.08116 0.32434 -0.30489 0.73716 -0.12338 0.03159 -0.09220 0.33628 -0.30468 0.74697 -0.11842 0.03757 -0.10210 0.34815 -0.30390 0.75683 -0.11357 0.04316 -0.11102 0.35995 -0.30257 0.76674 -0.10883 0.04837 -0.11907 0.37168 -0.30073 0.77669 -0.10421 0.05325 -0.12639 0.38332 -0.29841 0.78668 -0.09971 0.05787 -0.13310 0.39490 -0.29563 0.79668 -0.09532 0.06233 -0.13933 0.40641 -0.29244 0.80669 -0.09106 0.06670 -0.14520 0.41788 -0.28887 0.81668 -0.08692 0.07109 -0.15083 0.42931 -0.28494 0.82664 -0.08291 0.07555 -0.15634 0.44072 -0.28069 0.83655 -0.07903 0.08016 -0.16183 0.45213 -0.27616 0.84639 -0.07530 0.08497 -0.16738 0.46353 -0.27137 0.85613 -0.07172 0.09003 -0.17305 0.47493 -0.26635 0.86577 -0.06832 0.09537 -0.17891 0.48634 -0.26112 0.87528 -0.06511 0.10102 -0.18499 0.49774 -0.25572 0.88464 -0.06211 0.10700 -0.19130 0.50913 -0.25017 0.89385 -0.05935 0.11333 -0.19785 0.52049 -0.24448 0.90288 -0.05686 0.12002 -0.20462 0.53182 -0.23868 0.91174 -0.05465 0.12708 -0.21158 0.54308 -0.23279 0.92039 -0.05276 0.13452 -0.21870 0.55427 -0.22682 0.92884 -0.05122 0.14234 -0.22591 0.56536 -0.22081 0.93705 -0.05005 0.15056 -0.23317 0.57634 -0.21476 0.94503 -0.04927 0.15917 -0.24040 0.58719 -0.20869 0.95273 -0.04890 0.16817 -0.24754 0.59790 -0.20262 0.96218 -0.04900 0.17756 -0.25451 0.60847 -0.19656 0.97164 -0.04975 0.18733 -0.26126 0.61890 -0.19052 0.98109 -0.05114 0.19747 -0.26770 0.62918 -0.18451 0.99055 -0.05302 0.20795 -0.27377 0.63933 -0.17856 1.00000 -0.05500
0.21876 -0.27941 0.64935 -0.17266 0.22986 -0.28458 0.65927 -0.16683
Wherein, on the pressure side of x/c value representation the 4th aerofoil profile (180) certain point with respect to the length x of leading edge and the ratio of chord length c, the y/c value is then represented the height y of certain point from the string of a musical instrument to the four aerofoil profiles (180) pressure side and the ratio of chord length c on string of a musical instrument direction.
6. according to each described wind turbine blade airfoil family of claim 1 to 5, it is characterized in that described wind turbine blade airfoil family (A) is used for the horizontal-shaft wind turbine blade.
7. according to each described wind turbine blade airfoil family of claim 1 to 5, it is characterized in that described family of aerofoil sections (A) is applicable to that length of blade more than 20 meters, power megawatt are above, Stall Type or become the wind energy conversion system of oar type.
8. according to each described wind turbine blade airfoil family of claim 1 to 5, it is characterized in that described family of aerofoil sections (A) is applicable to the medial area of pneumatic equipment blades made.
CN2010206771537U 2010-12-23 2010-12-23 Wind-power machine vane-aerofoil family Expired - Lifetime CN201943900U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN2010206771537U CN201943900U (en) 2010-12-23 2010-12-23 Wind-power machine vane-aerofoil family

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN2010206771537U CN201943900U (en) 2010-12-23 2010-12-23 Wind-power machine vane-aerofoil family

Publications (1)

Publication Number Publication Date
CN201943900U true CN201943900U (en) 2011-08-24

Family

ID=44471246

Family Applications (1)

Application Number Title Priority Date Filing Date
CN2010206771537U Expired - Lifetime CN201943900U (en) 2010-12-23 2010-12-23 Wind-power machine vane-aerofoil family

Country Status (1)

Country Link
CN (1) CN201943900U (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102062044A (en) * 2010-12-23 2011-05-18 中国科学院工程热物理研究所 Wind machine blade airfoil family
CN103277245A (en) * 2013-06-14 2013-09-04 中国科学院工程热物理研究所 Large-thickness blunt-trailing-edge wind-power airfoil profiles and a design method thereof

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102062044A (en) * 2010-12-23 2011-05-18 中国科学院工程热物理研究所 Wind machine blade airfoil family
CN102062044B (en) * 2010-12-23 2012-06-27 中国科学院工程热物理研究所 Wind machine blade airfoil family
CN103277245A (en) * 2013-06-14 2013-09-04 中国科学院工程热物理研究所 Large-thickness blunt-trailing-edge wind-power airfoil profiles and a design method thereof

Similar Documents

Publication Publication Date Title
CN102062044B (en) Wind machine blade airfoil family
CN102003332B (en) Blade airfoil family of wind turbine
CN101876291B (en) Wind turbine blade airfoil family
CN101813070B (en) Vane airfoil profile of low power wind driven generator
CN202023688U (en) Wind turbine blade with blunt trailing edge
US20130236327A1 (en) Advanced aerodynamic and structural blade and wing design
CN104405596B (en) Wind turbine generator system low-wind-speed airfoil section family
CN203374428U (en) Family of wind-power airfoil profiles with large thickness and blunt trailing edges
CN102094767B (en) Airfoil group for megawatt-class wind turbine blade
CN103711655B (en) The blunt trailing edge pneumatic equipment blades made of a kind of heavy thickness
CN102444540B (en) Wind turbine blade aerofoil of horizontal axis wind turbine
CN203685493U (en) Big-thickness blunt trailing edge blade for wind turbine
CN201943900U (en) Wind-power machine vane-aerofoil family
CN103133272A (en) Thin airfoil type blade of large-scale fan
CN104819106A (en) Wind turbine blade wing section group
CN103306907B (en) A kind of heavy thickness aerofoil with blunt tail edge blade of large fan
CN210317591U (en) Wind turbine blade power increasing structure
CN201818426U (en) Vertical axis wind turbine
CN106321347A (en) Wind driven generator eddy generator
CN202348553U (en) Wind wheel vane wing profile of horizontal axis wind turbine
CN203175769U (en) Thin wing type blade of large-scale fan
CN103321856B (en) A kind of heavy thickness airfoil fan of large fan
CN112065651B (en) Airfoil for wind turbine blade layer of wind generating set
CN203321757U (en) Medium-thickness airfoil blade for large turbines
CN206129493U (en) Wind energy conversion system vortex generator

Legal Events

Date Code Title Description
C14 Grant of patent or utility model
GR01 Patent grant
AV01 Patent right actively abandoned

Granted publication date: 20110824

Effective date of abandoning: 20120627

AV01 Patent right actively abandoned

Granted publication date: 20110824

Effective date of abandoning: 20120627