CN103277245A - Large-thickness blunt-trailing-edge wind-power airfoil profiles and a design method thereof - Google Patents

Large-thickness blunt-trailing-edge wind-power airfoil profiles and a design method thereof Download PDF

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CN103277245A
CN103277245A CN2013102345492A CN201310234549A CN103277245A CN 103277245 A CN103277245 A CN 103277245A CN 2013102345492 A CN2013102345492 A CN 2013102345492A CN 201310234549 A CN201310234549 A CN 201310234549A CN 103277245 A CN103277245 A CN 103277245A
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aerofoil profile
thickness
aerofoil
trailing edge
attack
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CN103277245B (en
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杨科
李星星
张磊
白井艳
徐建中
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Institute of Engineering Thermophysics of CAS
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    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract

The invention discloses a group of large-thickness blunt-trailing-edge wind-power airfoil profiles and a design method thereof. The airfoil profiles have high lift coefficients under operation angles of attack. The airfoil profile group includes four airfoil profiles with relative thicknesses of 45%, 50%, 55% and 60% in sequence and with trailing edge thicknesses of 7%, 9%, 12% and 16% in sequence. Variable working condition design is adopted by the airfoil profile group, design Reynolds numbers of the four airfoil profiles are 4.0*106, 3.5*106, 3.0*106 and 2.5*106 in sequence according to the relative thicknesses, and the design objective mainly aims to take stability, changed along with the Reynolds numbers, of the lift coefficients as main constraint according to change features of the lifting coefficients within the range of large angles of attack in vane root areas. Numerical prediction results indicate that when the four large-thickness blunt-trailing-edge airfoil profiles are in the range of large angles of attack, the lift coefficients ascend continuously and stably and are in a high level. By the airfoil profile group, vane structural strength and stiffness can be improved, and a wind turbine can have high-efficient and stable output.

Description

The blunt trailing edge wind mill airfoil of the big thickness of gang and design method thereof
Technical field
The invention belongs to horizontal-shaft wind turbine Airfoil Design field, be specifically related to be applicable to gang's thick wing type profile and the design method thereof of large-scale horizontal-shaft wind turbine root of blade.
Background technique
The wind energy conversion system special airfoil family that develops excellent performance is a key of pneumatic equipment blades made energy capture rate of improving the standard, and the growth requirement of the research and development target of wind mill airfoil and wind energy conversion system is closely related.In recent years, the fast development of Chinese wind-powered electricity generation industry, the wind field of various scales is set up in different regions, and the capacity of new clothes wind energy conversion system constantly increases, and blade dimensions is significantly elongated.
At first, different wind-resources environment requires different to pneumatic equipment blades made.Southern china wide geographic area wind-resources sleepiness, northern area and coastal area belong to the abundant area of wind-resources but have various disadvantageous conditions.North China and the Northwest's dust storm are serious, very easily the pneumatic equipment blades made surface are polluted and corrode.The coastal area humidity of the air is on the verge of frequently than big and tropical depression.Warm and humid air causes its geometric profile of corrosion failure to blade surface easily on the one hand; On the other hand, the structural strength invaded pneumatic equipment blades made of tropical depression is a huge test frequently.Excellent performance and stable profile set under the variable working condition condition are designed in this requirement.
Secondly, the blade of wind energy conversion system maximizes day by day the material of blade and structural characteristics has been proposed requirements at the higher level; Simultaneously, the phenomenal growth of blade dimensions, the influence of wind shear effect is more obvious, and the wind speed of blade different parts is linear distribution and makes that the mobile reynolds' number of each position aerofoil profile of blade is widely different in the wind energy conversion system running in addition.These requirements are developed function admirable and along with the big thickness profile set that is applicable to blade middle part and afterbody of Re vary stable.
On the other hand, increase profile thickness and trailing edge thickness and can increase the cross-section area of aerofoil profile, improve the thickness distribution of aerofoil profile, significantly improve the structural rigidity of aerofoil profile.The trailing edge thickness that suitably improves aerofoil profile simultaneously can reduce the suction surface adverse pressure gradient, thereby postpones turbulent separation, improves maximum lift coefficient.Although resistance coefficient also can increase, the ratio of lift coefficient to drag coefficient of aerofoil profile increases, so the pneumatic efficiency of aerofoil profile has obtained reinforcement.Usually, big thickness aerofoil profile is applicable to root of blade, and flowing and usually be in the flow separation flowing state of the big angle of attack in this place, has stronger Three-dimensional Flow characteristic, therefore the big thickness of function admirable, the design of aerofoil with blunt tail edge, significant for research and development high-performance large-scale wind electricity blade.
The relative thickness that is applied to the aerofoil profile of pneumatic equipment blades made inboard at present mostly is 30%～40%, and trailing edge thickness is also less.And the design reynolds' number of existing thick wing type is single; The design angle of attack is less, the residing angle of attack scope of root area aerofoil profile when moving well below wind energy conversion system; Lift coefficient stall is violent, and is less under the big angle of attack.These defectives are unfavorable for improving the wind energy capture rate of large scale wind power machine.
Summary of the invention
Goal of the invention: in view of above problem, the object of the invention is to propose gang and has high coefficient of lift combined and the stable big thickness aerofoil with blunt tail edge of off design performance in operation under the angle of attack, can satisfy the large scale wind power machine blade structure and pneumatic aspect to the demand of aerofoil profile.
The present invention is achieved by the following technical solutions.
The blunt trailing edge wind mill airfoil of the big thickness of gang, has high coefficient of lift combined under the angle of attack and off design performance is stable in operation, comprise four kinds big thickness aerofoil profiles, it is characterized in that, the maximum relative thickness of described four kinds of big thickness aerofoil profiles is followed successively by 45%, 50%, 55% and 60%, and the trailing edge relative thickness is followed successively by 7%, 9%, 12% and 16%; The tangential relative position of the maximum ga(u)ge of described four kinds of aerofoil profiles is between 30%～35%, and the tangential relative position of upper surface maximum ga(u)ge is between 28%～33%, and the tangential relative position of lower surface maximum ga(u)ge is between 33%～37%; The mean camber line of described four kinds of aerofoil profiles all on the string of a musical instrument, and is having a protruding peak that makes progress respectively near the leading edge place with near the trailing edge place; Between 2%～3.2%, the tangential relative position of maximum camber is between 74%～79% to the camber value for the maximal phase of described four kinds of aerofoil profiles; The leading-edge radius of described four kinds of aerofoil profiles is between 0.099～0.125 times of chord length; Wherein, described maximum relative thickness is maximum ga(u)ge between each aerofoil profile upper and lower surfaces and the ratio of chord length, and each described tangential relative position refers to the ratio of the relative chord length of chordwise location.
Preferably, the mean camber line of described four aerofoil profiles is along the distribution characteristics unanimity of chord length, and near the mean camber line at the leading edge place peak that raises up, its tangential relative position is between 22%～23%; Near the mean camber line at the trailing edge place peak that raises up, its tangential relative position is between 75%～78%.
Preferably, described four kinds big thickness aerofoil with blunt tail edge are used for the root area of pneumatic equipment blades made, in the operation angle of attack is 15 °～30 ° scope, have high coefficient of lift combined and stable off design performance.
Preferably, the design reynolds' number of described four kinds of big thickness aerofoil with blunt tail edge is followed successively by 4.0 * 10 6, 3.5 * 10 6, 3.0 * 10 6, 2.5 * 10 6
Preferably, the design reynolds' number of the aerofoil profile of 45% relative thickness is 4 * 10 6, the dimensionless geometric coordinate of this aerofoil profile suction surface and pressure side is respectively:
The suction surface coordinate of table one 45% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c
1.000000 0.035000 0.414653 0.230451 0.107549 0.183861
0.989624 0.039100 0.392082 0.235319 0.098558 0.176440
0.980193 0.042445 0.370305 0.239611 0.089745 0.168644
0.969412 0.045937 0.349202 0.243383 0.081331 0.160650
0.954883 0.050761 0.329661 0.246510 0.073246 0.152412
0.935447 0.057529 0.314431 0.248661 0.065700 0.144148
0.913417 0.065109 0.303183 0.249887 0.058481 0.135599
0.891532 0.072891 0.293580 0.250521 0.051402 0.126593
0.869918 0.080967 0.284332 0.250715 0.044799 0.117574
0.846718 0.089698 0.275147 0.250534 0.038697 0.108522
0.820549 0.099367 0.266042 0.249976 0.032776 0.098983
0.793449 0.109529 0.256804 0.249032 0.027250 0.089420
0.765816 0.120046 0.247425 0.247690 0.022401 0.080258
0.739541 0.129944 0.237784 0.245923 0.018081 0.071272
0.715636 0.138644 0.227930 0.243727 0.014279 0.062543
0.690821 0.147322 0.217950 0.241105 0.010988 0.054095
0.662488 0.157033 0.207848 0.238039 0.008187 0.046004
0.632550 0.167310 0.197598 0.234509 0.005871 0.038341
0.604598 0.176922 0.187286 0.230533 0.004004 0.031110
0.582893 0.184208 0.176998 0.226129 0.002546 0.024279
0.560502 0.191255 0.166682 0.221261 0.001461 0.017809
0.536592 0.198439 0.156366 0.215936 0.000714 0.011594
0.511795 0.205497 0.146080 0.210158 0.000238 0.005577
0.484167 0.213146 0.135974 0.204012 0.000000 0.000000
0.460346 0.219484 0.126125 0.197538 ? ?
0.437835 0.225081 0.116618 0.190803 ? ?
Wherein, on the x/c value representation aerofoil profile suction surface certain point on string of a musical instrument direction with respect to the position of leading edge, the y/c value representation from the string of a musical instrument to the aerofoil profile suction surface on the height of certain point;
The pressure side coordinate of table two 45% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c
0.000000 0.000000 0.137478 -0.159660 0.581087 -0.139693
0.000024 -0.005207 0.150047 -0.164890 0.606114 -0.128291
0.000282 -0.010307 0.163133 -0.169812 0.634012 -0.115393
0.000773 -0.015300 0.177803 -0.174809 0.660952 -0.102995
0.001567 -0.020235 0.193804 -0.179808 0.685393 -0.091980
0.002800 -0.025523 0.209493 -0.184280 0.707822 -0.082196
0.004593 -0.031829 0.224351 -0.188056 0.728438 -0.073597
0.006822 -0.039219 0.238998 -0.191293 0.747840 -0.065938
0.009095 -0.046239 0.254116 -0.194156 0.766177 -0.059144
0.011508 -0.052632 0.269461 -0.196617 0.783459 -0.053201
0.014140 -0.058754 0.284406 -0.198570 0.799987 -0.047986
0.016850 -0.064432 0.299105 -0.200031 0.815898 -0.043432
0.019676 -0.069747 0.313960 -0.201045 0.831255 -0.039501
0.022479 -0.074523 0.328801 -0.201624 0.846167 -0.036144
0.025454 -0.078952 0.343150 -0.201749 0.860682 -0.033333
0.028681 -0.083380 0.356989 -0.201428 0.874868 -0.031036
0.031819 -0.087655 0.370698 -0.200650 0.888723 -0.029239
0.035001 -0.091548 0.384712 -0.199398 0.902320 -0.027913
0.038680 -0.095418 0.398980 -0.197677 0.915385 -0.027058
0.043509 -0.099962 0.413234 -0.195510 0.927823 -0.026660
0.049794 -0.105585 0.427520 -0.192877 0.939584 -0.026682
0.057097 -0.111828 0.442099 -0.189722 0.950454 -0.027088
0.064828 -0.117990 0.456940 -0.186042 0.960594 -0.027861
0.073180 -0.124110 0.472125 -0.181802 0.970473 -0.029013
0.082403 -0.130368 0.487650 -0.176986 0.979994 -0.030510
0.092172 -0.136529 0.503647 -0.171533 0.989366 -0.032411
0.102231 -0.142381 0.520497 -0.165286 1.000000 -0.035000
0.113002 -0.148115 0.538674 -0.158046 ? ?
0.124914 -0.153957 0.558716 -0.149579 ? ?
Wherein, on the x/c value representation aerofoil profile pressure side certain point on string of a musical instrument direction with respect to the position of leading edge, the y/c value representation from the string of a musical instrument to the aerofoil profile pressure side on the height of certain point.
Further, the aerofoil profile of 45% relative thickness, its stall angle is about 8 °, and after the stall, lift coefficient changes mild, and lift coefficient elder generation slightly rises the decline back in 8 °～15 ° angle of attack scopes, and the stalling characteristics parameter is M Stall=85.56 * 10 -5The definition of stalling characteristics parameter is as follows:
M stall = max { ( cl - cl max ) 2 &alpha; - &alpha; stall , &alpha; stall < &alpha; < 15 , &alpha; &Element; Z }
Wherein, cl is lift coefficient, cl MaxBe maximum lift coefficient, α is the angle of attack, α StallBe stall angle.
Further, the aerofoil profile of described 45% relative thickness, in 15 °～30 ° big angle of attack scopes, the lift coefficient of aerofoil profile slightly descends since 1.6, begins stable the rising then, reaches 1.7387 in the time of 30 °.
Preferably, the design reynolds' number of 50% relative thickness aerofoil profile is 3.5 * 10 6, the dimensionless geometric coordinate of this aerofoil profile suction surface and pressure side is respectively
The suction surface coordinate of table three 50% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c
1.000000 0.045000 0.388304 0.258891 0.109817 0.185041
0.987360 0.049555 0.373331 0.261155 0.099992 0.177164
0.972355 0.054789 0.359560 0.262756 0.090575 0.169102
0.950159 0.062484 0.347468 0.263757 0.081892 0.161145
0.922588 0.072513 0.336057 0.264258 0.073694 0.153066
0.893875 0.083372 0.324729 0.264342 0.065717 0.144629
0.865241 0.094616 0.313777 0.264026 0.058122 0.136027
0.838292 0.105415 0.303062 0.263321 0.051024 0.127409
0.810717 0.116661 0.292433 0.262254 0.044372 0.118730
0.782619 0.128287 0.281929 0.260845 0.038307 0.110168
0.753456 0.140513 0.271426 0.259078 0.032843 0.101675
0.726311 0.151930 0.260884 0.256946 0.027762 0.092977
0.697922 0.163892 0.250324 0.254448 0.022906 0.083838
0.675778 0.173139 0.239619 0.251543 0.018358 0.074396
0.654023 0.181839 0.228724 0.248214 0.014422 0.065328
0.629263 0.191411 0.217683 0.244460 0.011073 0.056672
0.605313 0.200327 0.206769 0.240372 0.008293 0.048452
0.582737 0.208313 0.195812 0.235860 0.005962 0.040517
0.560711 0.215659 0.184885 0.230968 0.004065 0.033139
0.537503 0.222881 0.174013 0.225671 0.002589 0.026166
0.511931 0.230330 0.162950 0.219853 0.001447 0.019429
0.485540 0.237449 0.152080 0.213697 0.000663 0.013288
0.457375 0.244437 0.141417 0.207192 0.000224 0.007639
0.430299 0.250687 0.130681 0.200153 0.000023 0.002217
0.407925 0.255329 0.120009 0.192676 0.000000 0.000000
The pressure side coordinate of table four 50% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c
0.000000 0.000000 0.151987 -0.182089 0.578967 -0.185534
0.000040 -0.002899 0.167106 -0.189085 0.599019 -0.176495
0.000279 -0.008104 0.183651 -0.196119 0.619649 -0.166781
0.000761 -0.013399 0.201566 -0.203101 0.641027 -0.156281
0.001528 -0.018839 0.220232 -0.209749 0.665649 -0.143864
0.002562 -0.024387 0.239067 -0.215835 0.690205 -0.131457
0.004005 -0.030357 0.258020 -0.221333 0.712183 -0.120544
0.006046 -0.037427 0.276686 -0.226116 0.732834 -0.110618
0.008352 -0.044940 0.294541 -0.230088 0.752959 -0.101286
0.010688 -0.051717 0.310150 -0.233040 0.772030 -0.092776
0.013258 -0.058201 0.322925 -0.234962 0.789558 -0.085311
0.016114 -0.064648 0.334011 -0.236191 0.805729 -0.078795
0.019086 -0.070739 0.344443 -0.236982 0.820581 -0.073176
0.022183 -0.076470 0.354984 -0.237436 0.834376 -0.068328
0.025504 -0.082018 0.366349 -0.237569 0.847834 -0.063985
0.029223 -0.087666 0.378923 -0.237302 0.861344 -0.059990
0.033166 -0.093244 0.392142 -0.236571 0.874662 -0.056403
0.037105 -0.098330 0.405253 -0.235416 0.887721 -0.053232
0.041468 -0.103388 0.418256 -0.233847 0.900119 -0.050554
0.046869 -0.109080 0.431353 -0.231878 0.911716 -0.048385
0.053785 -0.115881 0.444730 -0.229480 0.922833 -0.046637
0.061963 -0.123435 0.458277 -0.226681 0.933648 -0.045249
0.070734 -0.131003 0.471804 -0.223519 0.943961 -0.044226
0.079924 -0.138355 0.485300 -0.219985 0.953625 -0.043561
0.089839 -0.145677 0.498688 -0.216089 0.962703 -0.043230
0.100687 -0.153108 0.512388 -0.211684 0.971401 -0.043205
0.112253 -0.160455 0.527066 -0.206531 0.980029 -0.043476
0.124838 -0.167866 0.543054 -0.200487 0.989178 -0.044090
0.138007 -0.175054 0.560404 -0.193485 1.000000 -0.045000
Further, 50% relative thickness aerofoil profile, its stall angle is 5 °, it is 1.2258 that lift coefficient reaches maximum numerical value for the first time, and after the stall, lift coefficient descends earlier in 5 °～15 ° angle of attack scopes and afterwards rises, whole lift coefficient value maintains 1.08～1.22, and the stalling characteristics parameter is M Stall=101.25 * 10 -5Further, described 50% relative thickness aerofoil profile, in 15 °～31 ° big angle of attack scopes, lift coefficient reaches 1.6209 since 1.17 stable risings in the time of 31 °.
Preferably, the design reynolds' number of the aerofoil profile of 55% relative thickness is 3 * 10 6, the dimensionless geometric coordinate of this aerofoil profile suction surface and pressure side is respectively:
The suction surface coordinate of table five 55% relative thickness aerofoil profile (x/c, y/c)
Figure BDA00003342259300081
Figure BDA00003342259300091
The pressure side coordinate of table six 55% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c
0.000000 0.000000 0.151981 -0.211280 0.578951 -0.196942
0.000040 -0.003437 0.167099 -0.219052 0.599002 -0.187452
0.000279 -0.008576 0.183644 -0.226690 0.619633 -0.177378
0.000761 -0.015939 0.201559 -0.234066 0.641010 -0.166676
0.001528 -0.021306 0.220224 -0.240826 0.665632 -0.154149
0.002562 -0.027986 0.239059 -0.246674 0.690187 -0.141847
0.004005 -0.034836 0.258012 -0.251591 0.712165 -0.131233
0.006045 -0.043262 0.276678 -0.255516 0.732815 -0.121609
0.008351 -0.051924 0.294533 -0.258280 0.752940 -0.112572
0.010687 -0.059721 0.310140 -0.259832 0.772011 -0.104378
0.013257 -0.067200 0.322914 -0.260486 0.789539 -0.097233
0.016113 -0.074667 0.334001 -0.260632 0.805710 -0.091018
0.019085 -0.081700 0.344433 -0.260439 0.820562 -0.085686
0.022182 -0.088272 0.354972 -0.259961 0.834356 -0.081112
0.025502 -0.094708 0.366338 -0.259161 0.847814 -0.077013
0.029221 -0.101303 0.378912 -0.257948 0.861324 -0.073240
0.033164 -0.107726 0.392131 -0.256331 0.874641 -0.069862
0.037103 -0.113518 0.405241 -0.254364 0.887700 -0.066892
0.041466 -0.119369 0.418244 -0.252056 0.900098 -0.064404
0.046866 -0.126110 0.431340 -0.249420 0.911695 -0.062403
0.053782 -0.134218 0.444718 -0.246390 0.922810 -0.060802
0.061960 -0.143201 0.458263 -0.242952 0.933626 -0.059548
0.070730 -0.152128 0.471790 -0.239108 0.943938 -0.058652
0.079920 -0.160727 0.485286 -0.234879 0.953602 -0.058103
0.089835 -0.169316 0.498673 -0.230326 0.962679 -0.057870
0.100683 -0.178020 0.512373 -0.225322 0.971377 -0.057929
0.112249 -0.186580 0.527051 -0.219597 0.980005 -0.058277
0.124833 -0.195171 0.543038 -0.212975 0.989154 -0.058960
0.138001 -0.203370 0.560388 -0.205398 1.000000 -0.060000
Further, 55% relative thickness aerofoil profile, its stall angle is 5 °, it is 1.1543 that lift coefficient reaches maximum numerical value for the first time, lift coefficient after the stall steadily maintains 1.02～1.08 levels drop to about 1 in 5 °～15 ° angle of attack scopes after, and the stalling characteristics parameter is M Stall=46.41 * 10 -5Further, described 55% relative thickness aerofoil profile, in 15 °～30 ° big angle of attack scopes, lift coefficient rises from 1.0308 modes that change with approximately linear, reaches 1.6797 in the time of 30 °.
Preferably, the design reynolds' number of 60% relative thickness aerofoil profile is 2.5 * 10 6, the dimensionless geometric coordinate of this aerofoil profile suction surface and pressure side is respectively:
The suction surface coordinate of table seven 60% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c
1.000000 0.080000 0.388331 0.309008 0.109826 0.218478
0.987413 0.084403 0.373357 0.311410 0.100001 0.209090
0.972407 0.089551 0.359585 0.313100 0.090582 0.199491
0.950211 0.097223 0.347493 0.314121 0.081899 0.190036
0.922638 0.107395 0.336081 0.314620 0.073701 0.180460
0.893924 0.118569 0.324752 0.314622 0.065723 0.170459
0.865289 0.130280 0.313799 0.314164 0.058128 0.160269
0.838338 0.141625 0.303084 0.313231 0.051028 0.150075
0.810762 0.153534 0.292454 0.311835 0.044376 0.139832
0.782663 0.165947 0.281950 0.310024 0.038311 0.129773
0.753497 0.179092 0.271446 0.307797 0.032848 0.119806
0.726352 0.191433 0.260904 0.305140 0.027765 0.109554
0.697962 0.204412 0.250343 0.302052 0.022909 0.098822
0.675817 0.214525 0.239637 0.298483 0.018361 0.087635
0.654062 0.224110 0.228741 0.294408 0.014425 0.076920
0.629300 0.234681 0.217699 0.289829 0.011076 0.066687
0.605349 0.244569 0.206785 0.284857 0.008294 0.056996
0.582772 0.253436 0.195827 0.279395 0.005963 0.047521
0.560745 0.261616 0.184900 0.273483 0.004066 0.038834
0.537536 0.269660 0.174027 0.267109 0.002590 0.030849
0.511963 0.277938 0.162964 0.260115 0.001448 0.022708
0.485570 0.285846 0.152092 0.252731 0.000663 0.015617
0.457405 0.293494 0.141429 0.244948 0.000224 0.008839
0.430328 0.300232 0.130692 0.236533 0.000023 0.002615
0.407953 0.305215 0.120020 0.227592 0.000000 0.000000
The pressure side coordinate of table eight 60% relative thickness aerofoil profile (x/c, y/c)
Figure BDA00003342259300101
Figure BDA00003342259300111
Further, the aerofoil profile of 60% relative thickness, its stall angle is about 2 °, and the maximum lift coefficient value is 0.8165, and after the stall, the back is stable lift coefficient slightly drops to 0.63 in 2 °～15 ° angle of attack scopes about rises, and the mild characteristic of stall is M Stall=179.17 * 10 -5Further, the aerofoil profile of described 60% relative thickness, in 14 °～30 ° big angle of attack scopes, lift coefficient rises from 1.0779 modes that change with approximately linear, reaches 1.783 in the time of 30 °.
According to a further aspect in the invention, a kind of design method for the above-mentioned aerofoil profile of design also is provided, comprise positive design procedure and anti-design procedure, it is characterized in that, in the described positive design procedure, from original aerofoil profile, at first keep camber distribution and the maximum ga(u)ge position of original aerofoil profile constant substantially, the relative thickness of regulating aerofoil profile reaches the target relative thickness; Keep the relative thickness of aerofoil profile constant afterwards, the trailing edge thickness of regulating aerofoil profile reaches target trailing edge thickness; After finishing described positive design procedure, carry out anti-design procedure, in the described anti-design procedure, by regulating the pressure distribution of airfoil surface, finely tune leading edge shape, relative thickness and the distribution thereof of aerofoil profile, camber and distribution thereof relatively.
Preferably, in the positive design procedure, the trailing edge thickness of described adjusting aerofoil profile reaches target trailing edge thickness, and by keeping relative thickness constant, the mode of amplifying trailing edge along the mean camber line symmetry realizes.Preferably, the pressure distribution of described adjusting airfoil surface mainly is that the height to leading edge suction surface pressure peak in the boundary layer of aerofoil profile, the chordwise location of pressure spike and three principal elements such as gradient that pressure spike falls after rise are regulated.
Useful result: the scarcity of the thick family of aerofoil sections that the big thickness aerofoil with blunt tail edge that gang provided by the invention has high coefficient of lift combined under the angle of attack in operation faces in the time of can remedying the design of large scale wind power machine blade.Big relative thickness and trailing edge thickness can effectively improve the structure attribute of blade.The more important thing is, the design object of this family of aerofoil sections during clearly the blade actual motion lift coefficient under the residing reynolds' number separately of aerofoil profile condition, the big angle of attack as pneumatic target, rather than picture before single reynolds' number, than the maximum lift-drag ratio under the Low Angle Of Attack and maximum lift coefficient as pneumatic target, more press close to the performance requirement of large scale wind power machine root of blade blade.
Description of drawings
Fig. 1 is the basic molded lines of proposed by the invention big thickness aerofoil with blunt tail edge family;
Fig. 2 is the mean camber line scatter chart of each aerofoil profile proposed by the invention;
Fig. 3 for each aerofoil profile proposed by the invention at the lift coefficient curve that designs separately under the reynolds' number;
Fig. 4 is the plotted curve that 45% wing section lift coefficient changes with Re for relative thickness;
Fig. 5 is the plotted curve that 50% wing section lift coefficient changes with Re for relative thickness;
Fig. 6 is the plotted curve that 55% wing section lift coefficient changes with Re for relative thickness;
Fig. 7 is the plotted curve that 60% wing section lift coefficient changes with Re for relative thickness;
Among the figure, 45% to represent relative thickness be 45% aerofoil profile; 50% to represent relative thickness be 50% aerofoil profile; 55% to represent relative thickness be 55% aerofoil profile; 60% to represent relative thickness be 60% aerofoil profile.
Embodiment
For making purpose of the present invention, technological scheme and advantage clearer, below with reference to the accompanying drawing embodiment that develops simultaneously, invention is further described.
Aerofoil profile proposed by the invention is that the mode that adopts positive and negative method to combine obtains.From original aerofoil profile, adopt positive design method, at first keep camber distribution and the maximum ga(u)ge position of aerofoil profile constant substantially, design obtains the aerofoil profile of four kinds of relative thicknesses; Further realize thick trailing edge shape-designing.The design of thick trailing edge has two kinds of main thinkings: directly block the tail region of former aerofoil profile or keep relative thickness constant, symmetry is amplified trailing edge.Directly block thickness and camber distribution that trailing edge can change aerofoil profile significantly, to the airfoil aerodynamic performances influence greatly, especially can make the lift coefficient of aerofoil profile degenerate.Adopt a kind of formative method in back at this, keep relative thickness and maximum ga(u)ge position constant substantially, symmetry is amplified trailing edge, can effectively reduce the border adverse pressure gradient, improves airfoil aerodynamic performances.Like this, obtain meeting the initial aerofoil profile of relative thickness, the basic desired extent of trailing edge thickness and maximum relative thickness position through initial shape-designing.
In just designing, keep relative thickness constant, the trailing edge thickness of raising aerofoil profile can reduce the pressure gradient under a certain flox condition, postpones the separation in boundary layer, obtains higher maximum lift coefficient.Anti-this stage of design is revised the pressure distribution feature of aerofoil profile further with the core that is optimized for of aeroperformance, improves the aerodynamic parameter of aerofoil profile.Big thickness aerofoil profile will take place to change when the angle of attack is very little twists, and (perhaps can be accompanied by the attached again of separate bubble) forms turbulent boundary layer; Turbulent boundary layer is difficult the separation, when trailing edge thickness is big, and the more close trailing edge of separation point.The aerofoil profile aeroperformance is influenced the height that the most significant pressure distribution feature is leading edge suction surface pressure peak in the boundary layer, the chordwise location of pressure spike and the gradient that pressure spike falls after rise.By the modification to this three, come fine to regulate indirectly leading edge shape, relative thickness and the distribution thereof of aerofoil profile, camber and distribution thereof relatively, the speed that moves to leading edge from trailing edge along with the increase of the angle of attack with the flow separation point that reduces aerofoil profile, thereby make that aerofoil profile is tending towards changing gently after stall, even follow a lift coefficient to continue the process that increases.Big thickness aerofoil profile is in complete turbulence state usually when the big angle of attack, be subjected to the influence of Re less, has higher Re stability.Optimize so repeatedly, obtain meeting four kinds of aerofoil profiles of expected design, as shown in Figure 1.
Fig. 1 is the basic molded lines of proposed by the invention big thickness aerofoil with blunt tail edge family, the basic geometric parameters of each aerofoil profile as shown in Table 9, the dimensionless profile coordinate of four kinds of corresponding aerofoil profiles as table one to shown in the table eight. major parameter is the concrete relative thickness, maximum relative thickness position of aerofoil profile, (numerical value are the comparison value with respect to chord length) such as camber, maximum camber position, leading-edge radius, trailing edge thickness relatively.Wherein, X (Y+), X (Y-) represent the chordwise location of upper and lower surface maximum ga(u)ge position respectively.
The basic geometric parameters of the big thickness aerofoil with blunt tail edge of table nine gang
Figure BDA00003342259300141
Between 30%～35%, particularly, upper surface maximum ga(u)ge position is between (0.28～0.33) times chord length at the relative position of chord length direction for the maximum ga(u)ge of four kinds of big thickness aerofoil profiles, and lower surface maximum ga(u)ge position is between (0.33～0.37) times chord length; As shown in Figure 2, the mean camber line of four aerofoil profiles all on chord length, just says that also the aerofoil profile upper surface is thicker along the distribution characteristics unanimity of chord length; Mean camber line is going out with the trailing edge place peak that raises up is all arranged near leading edge, and chordwise location is respectively between (0.22～0.23) times chord length and (0.75～0.78) times chord length; Maximal phase is close to the camber value, and between (0.020～0.032) chord length, the chordwise location of maximum camber is between 74%～79%; Between (0.099～0.125) chord length, trailing edge thickness increases according to the increase of relative thickness the leading-edge radius of four kinds of aerofoil profiles gradually successively; These how much of effectively having guaranteed family of aerofoil sections are compatible.
Big thickness aerofoil with blunt tail edge proposed by the invention is to be particularly useful for the large scale wind power machine blade.According to the distribution of China's wind-resources distribution characteristics and large scale wind power machine blade (5MW wind energy conversion system) each several part reynolds' number, four kinds of design reynolds' number drafting 45% to 60% 4 kind of big thickness aerofoil profile are respectively: 4.0 * 10 6, 3.5 * 10 6, 3.0 * 10 6, 2.5 * 10 6
On the other hand, for the pneumatic equipment blades made of 5MW capacity, 45% and the aerofoil profile of above thickness be applicable to that basically the blade exhibition is to 10%～30% position of position.Because the maximum torsional angle of this position blade is restricted, so cause the maximum chord length position with the actual flow angle of attack of interior especially root area cross section aerofoil profile excessive (angle of attack scope of the pneumatic equipment blades made root aerofoil profile of 5MW is 12 °～25 °).For big thickness aerofoil profile, under this angle of attack, lift curve is in the stall rear region usually, and flow boundary layer also is generally turbulent boundary layer, and resistance coefficient is big unusually.Therefore, in this invention, be main pneumatic target with maximum lift coefficient, the big interior lift coefficient of angle of attack scope (15 °～30 °), limiting lift coefficient simultaneously will be along with the vary stable of reynolds number Re.
The explanation of the aerodynamic characteristics of family of aerofoil sections proposed by the invention all is based on the numerical result of the vortex sheet unit method (RFOIL as known in the art) of the sticking iteration of viscosity-nothing, and design conditions are twisted situation for the commentaries on classics naturally that designs separately under the reynolds' number.Table two has provided the key aerodynamic parameter of family of aerofoil sections.Wherein maximum lift coefficient is the maximum value that wing section lift coefficient is obtained for the first time.The angle of attack scope that the mild special parameter of the stall of aerofoil profile is investigated here is from stall angle to the 15 ° angle of attack.Because under the big angle of attack, the lift coefficient of aerofoil profile increases (based on numerical result) in the mode of approximately linear again, the lift feature of aerofoil profile under the big angle of attack mainly characterized by the constant interval of lift.Provided lift coefficient separately under 15 ° and the 30 ° of angles of attack in the table.Because stall angle is less, and what investigate is the stability that lift coefficient changes along with Re in the big angle of attack scope, thus this with lift curve section under the different Reynolds number to qualitative explanation recently.The condition of twisting of commentaries on classics naturally that Fig. 3 obtains for family of aerofoil sections numerical solution proposed by the invention designs the lift coefficient curve under the reynolds' number separately.
The definition of stalling characteristics parameter is as follows:
M stall = max { ( cl - cl max ) 2 &alpha; - &alpha; stall , &alpha; stall < &alpha; < 15 , &alpha; &Element; Z }
The basic aerodynamic parameter of each aerofoil profile of table ten
Figure BDA00003342259300152
Figure BDA00003342259300161
In conjunction with Fig. 3 and table ten, the aeroperformance feature of proposed by the invention big thickness aerofoil with blunt tail edge family is described.
The design reynolds' number of 45% relative thickness aerofoil profile is 4 * 10 6The stall angle of this aerofoil profile higher (8 °), so the numerical value of lift coefficient when reaching maximum for the first time also maximum (1.6427) in four kinds of aerofoil profiles.After the stall, the lift coefficient of aerofoil profile changes comparatively mild, the process that in (8 °～15 °) angle of attack scope, has the back that slightly descends to rise, but whole lift coefficient value maintains high level, and the stalling characteristics parameter only is M Stall=85.56 * 10 -5In big angle of attack scope (15 °～30 °), the lift coefficient of aerofoil profile slightly descends since 1.6, begins a stable uphill process then, reaches 1.7387. in the time of 30 °
The design reynolds' number of 50% relative thickness aerofoil profile is 3.5 * 10 6Increase along with relative thickness, the stall angle that this aerofoil profile is changeed under the condition of twisting naturally is 5 ° in advance, it is that lift coefficient after the 1.2258. stall has the process that rises after the decline in (5 °～15 °) angle of attack scope that lift coefficient reaches maximum numerical value for the first time, but whole lift coefficient value maintains (1.08～1.22), and the stalling characteristics parameter is M Stall=101.25 * 10 -5In big angle of attack scope (15 °～31 °), the lift coefficient of aerofoil profile reaches 1.6209. since 1.17 stable risings in the time of 31 °
The design reynolds' number of 55% relative thickness aerofoil profile is 3 * 10 6The stall angle that this aerofoil profile is changeed under the condition of twisting naturally also is 5 °, it is that the back changes extremely steady lift coefficient after the 1.1543. stall drops to 1 in (5 °～15 °) angle of attack scope about that lift coefficient reaches maximum numerical value for the first time, maintain 1.02～1.08 levels, so the mild characteristic of stall only is M Stall=46.41 * 10 -5In big angle of attack scope (15 °～30 °), the lift coefficient of aerofoil profile rises from 1.0308 modes that change with approximately linear, reaches 1.6797. in the time of 30 °
The design reynolds' number of 60% relative thickness aerofoil profile is 2.5 * 10 6Because relative thickness and trailing edge thickness are excessive, this aerofoil profile changes naturally under the condition of twisting lift coefficient the angle of attack very as a child (2 °) reached maximum with regard to the first time, value is 0.8165.Lift coefficient after the stall slightly drops to 0.63(4 ° in (2 °～15 °) angle of attack scope) about the back is stable rises, the mild characteristic of stall is M Stall=179.17 * 10 -5In big angle of attack scope (14 °～30 °), the lift coefficient of aerofoil profile rises from 1.0779 modes that change with approximately linear, reaches 1.783. in the time of 30 °
To sum up, family of aerofoil sections proposed by the invention reaches maximum value for the first time by going through a mild stall process, and lift coefficient continues to increase.In big angle of attack scope, the rising that lift coefficient is continual and steady also is in higher level.Between 15 ° to the 30 ° angles of attack, the roughly variation of approximately linear between 1.0 to 1.7 of the lift coefficient of this family of aerofoil sections (45% thickness airfoil performance excellence, the lift coefficient in this scope is 1.3812～1.7387).So reached the pneumatic target that in big angle of attack scope, has than high coefficient of lift combined.
The lift coefficient of aerofoil profile with Re change stable aspect, according to numerical result, Fig. 4 has showed that the lift curve of 45% aerofoil profile is along with the variation of Re, Fig. 5 has showed that the lift curve of 50% aerofoil profile is along with the variation of Re, Fig. 6 has showed the lift curve of 55% aerofoil profile along with the variation of Re, and Fig. 7 has then showed the variation of the lift curve of 60% aerofoil profile.Can find out significantly that from figure this of the present invention's proposition organized big thickness aerofoil with blunt tail edge and have excellent reynolds' number stability in operation angle of attack scope, is conducive to wind-driven generator and obtains more stable output.
The above only is preferred embodiment of the present invention, and is in order to limit the present invention, within the spirit and principles in the present invention not all, any modification of making, is equal to replacement, improvement etc., all should be included within the scope of the present invention.

Claims (10)

1. the blunt trailing edge wind mill airfoil of the big thickness of gang has high coefficient of lift combined under the operation angle of attack and off design performance is stable, comprises four kinds big thickness aerofoil profiles, it is characterized in that,
The maximum relative thickness of described four kinds of big thickness aerofoil profiles is followed successively by 45%, 50%, 55% and 60%, and the trailing edge relative thickness is followed successively by 7%, 9%, 12% and 16%;
The tangential relative position of the maximum ga(u)ge of described four kinds of aerofoil profiles is between 30%～35%, and the tangential relative position of upper surface maximum ga(u)ge is between 28%～33%, and the tangential relative position of lower surface maximum ga(u)ge is between 33%～37%;
The mean camber line of described four kinds of aerofoil profiles all on the string of a musical instrument, and is having a protruding peak that makes progress respectively near the leading edge place with near the trailing edge place;
Between 2%～3.2%, the tangential relative position of maximum camber is between 74%～79% to the camber value for the maximal phase of described four kinds of aerofoil profiles;
The leading-edge radius of described four kinds of aerofoil profiles is between 0.099～0.125 times of chord length;
Wherein, described maximum relative thickness is maximum ga(u)ge between each aerofoil profile upper and lower surfaces and the ratio of chord length, and each described tangential relative position refers to the ratio of the relative chord length of chordwise location.
2. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 1, it is characterized in that: the mean camber line of described four aerofoil profiles is along the distribution characteristics unanimity of chord length, near the mean camber line at the leading edge place peak that raises up, its tangential relative position is between 22%～23%; Near the mean camber line at the trailing edge place peak that raises up, its tangential relative position is between 75%～78%.
3. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 1, it is characterized in that, described four kinds big thickness aerofoil with blunt tail edge are used for the root area of pneumatic equipment blades made, in the operation angle of attack is 15 °～30 ° scope, have high coefficient of lift combined and stable off design performance.
4. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 1, it is characterized in that: the design reynolds' number of described four kinds of big thickness aerofoil with blunt tail edge is followed successively by 4.0 * 10 6, 3.5 * 10 6, 3.0 * 10 6, 2.5 * 10 6
5. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 4, it is characterized in that: the design reynolds' number of the aerofoil profile of 45% relative thickness is 4 * 10 6, the dimensionless geometric coordinate of this aerofoil profile suction surface and pressure side is respectively:
The suction surface coordinate of 45% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c 1.000000 0.035000 0.414653 0.230451 0.107549 0.183861 0.989624 0.039100 0.392082 0.235319 0.098558 0.176440 0.980193 0.042445 0.370305 0.239611 0.089745 0.168644 0.969412 0.045937 0.349202 0.243383 0.081331 0.160650 0.954883 0.050761 0.329661 0.246510 0.073246 0.152412 0.935447 0.057529 0.314431 0.248661 0.065700 0.144148 0.913417 0.065109 0.303183 0.249887 0.058481 0.135599 0.891532 0.072891 0.293580 0.250521 0.051402 0.126593 0.869918 0.080967 0.284332 0.250715 0.044799 0.117574 0.846718 0.089698 0.275147 0.250534 0.038697 0.108522 0.820549 0.099367 0.266042 0.249976 0.032776 0.098983 0.793449 0.109529 0.256804 0.249032 0.027250 0.089420 0.765816 0.120046 0.247425 0.247690 0.022401 0.080258 0.739541 0.129944 0.237784 0.245923 0.018081 0.071272 0.715636 0.138644 0.227930 0.243727 0.014279 0.062543 0.690821 0.147322 0.217950 0.241105 0.010988 0.054095 0.662488 0.157033 0.207848 0.238039 0.008187 0.046004 0.632550 0.167310 0.197598 0.234509 0.005871 0.038341 0.604598 0.176922 0.187286 0.230533 0.004004 0.031110 0.582893 0.184208 0.176998 0.226129 0.002546 0.024279 0.560502 0.191255 0.166682 0.221261 0.001461 0.017809 0.536592 0.198439 0.156366 0.215936 0.000714 0.011594
0.511795 0.205497 0.146080 0.210158 0.000238 0.005577 0.484167 0.213146 0.135974 0.204012 0.000000 0.000000 0.460346 0.219484 0.126125 0.197538 ? ? 0.437835 0.225081 0.116618 0.190803 ? ?
Wherein, on the x/c value representation aerofoil profile suction surface certain point on string of a musical instrument direction with respect to the position of leading edge, the y/c value representation from the string of a musical instrument to the aerofoil profile suction surface on the height of certain point;
The pressure side coordinate of 45% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c 0.000000 0.000000 0.137478 -0.159660 0.581087 -0.139693 0.000024 -0.005207 0.150047 -0.164890 0.606114 -0.128291 0.000282 -0.010307 0.163133 -0.169812 0.634012 -0.115393 0.000773 -0.015300 0.177803 -0.174809 0.660952 -0.102995 0.001567 -0.020235 0.193804 -0.179808 0.685393 -0.091980 0.002800 -0.025523 0.209493 -0.184280 0.707822 -0.082196 0.004593 -0.031829 0.224351 -0.188056 0.728438 -0.073597 0.006822 -0.039219 0.238998 -0.191293 0.747840 -0.065938 0.009095 -0.046239 0.254116 -0.194156 0.766177 -0.059144 0.011508 -0.052632 0.269461 -0.196617 0.783459 -0.053201 0.014140 -0.058754 0.284406 -0.198570 0.799987 -0.047986 0.016850 -0.064432 0.299105 -0.200031 0.815898 -0.043432 0.019676 -0.069747 0.313960 -0.201045 0.831255 -0.039501 0.022479 -0.074523 0.328801 -0.201624 0.846167 -0.036144 0.025454 -0.078952 0.343150 -0.201749 0.860682 -0.033333 0.028681 -0.083380 0.356989 -0.201428 0.874868 -0.031036 0.031819 -0.087655 0.370698 -0.200650 0.888723 -0.029239 0.035001 -0.091548 0.384712 -0.199398 0.902320 -0.027913 0.038680 -0.095418 0.398980 -0.197677 0.915385 -0.027058 0.043509 -0.099962 0.413234 -0.195510 0.927823 -0.026660 0.049794 -0.105585 0.427520 -0.192877 0.939584 -0.026682 0.057097 -0.111828 0.442099 -0.189722 0.950454 -0.027088
0.064828 -0.117990 0.456940 -0.186042 0.960594 -0.027861 0.073180 -0.124110 0.472125 -0.181802 0.970473 -0.029013 0.082403 -0.130368 0.487650 -0.176986 0.979994 -0.030510 0.092172 -0.136529 0.503647 -0.171533 0.989366 -0.032411 0.102231 -0.142381 0.520497 -0.165286 1.000000 -0.035000 0.113002 -0.148115 0.538674 -0.158046 ? ? 0.124914 -0.153957 0.558716 -0.149579 ? ?
Wherein, on the x/c value representation aerofoil profile pressure side certain point on string of a musical instrument direction with respect to the position of leading edge, the y/c value representation from the string of a musical instrument to the aerofoil profile pressure side on the height of certain point.
6. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 5, it is characterized in that: the aerofoil profile of 45% relative thickness, its stall angle are about 8 °, after the stall, lift coefficient changes mild, and lift coefficient elder generation slightly rises the decline back in 8 °～15 ° angle of attack scopes, and the stalling characteristics parameter is M Stall=85.56 * 10 -5
7. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 6, it is characterized in that: the aerofoil profile of described 45% relative thickness, in 15 °～30 ° big angle of attack scopes, the lift coefficient of aerofoil profile slightly descends since 1.6, begin stable the rising then, in the time of 30 °, reach 1.7387.
8. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 4, it is characterized in that: the design reynolds' number of 50% relative thickness aerofoil profile is 3.5 * 10 6, the dimensionless geometric coordinate of this aerofoil profile suction surface and pressure side is respectively
The suction surface coordinate of 50% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c 1.000000 0.045000 0.388304 0.258891 0.109817 0.185041 0.987360 0.049555 0.373331 0.261155 0.099992 0.177164 0.972355 0.054789 0.359560 0.262756 0.090575 0.169102 0.950159 0.062484 0.347468 0.263757 0.081892 0.161145 0.922588 0.072513 0.336057 0.264258 0.073694 0.153066 0.893875 0.083372 0.324729 0.264342 0.065717 0.144629
0.865241 0.094616 0.313777 0.264026 0.058122 0.136027 0.838292 0.105415 0.303062 0.263321 0.051024 0.127409 0.810717 0.116661 0.292433 0.262254 0.044372 0.118730 0.782619 0.128287 0.281929 0.260845 0.038307 0.110168 0.753456 0.140513 0.271426 0.259078 0.032843 0.101675 0.726311 0.151930 0.260884 0.256946 0.027762 0.092977 0.697922 0.163892 0.250324 0.254448 0.022906 0.083838 0.675778 0.173139 0.239619 0.251543 0.018358 0.074396 0.654023 0.181839 0.228724 0.248214 0.014422 0.065328 0.629263 0.191411 0.217683 0.244460 0.011073 0.056672 0.605313 0.200327 0.206769 0.240372 0.008293 0.048452 0.582737 0.208313 0.195812 0.235860 0.005962 0.040517 0.560711 0.215659 0.184885 0.230968 0.004065 0.033139 0.537503 0.222881 0.174013 0.225671 0.002589 0.026166 0.511931 0.230330 0.162950 0.219853 0.001447 0.019429 0.485540 0.237449 0.152080 0.213697 0.000663 0.013288 0.457375 0.244437 0.141417 0.207192 0.000224 0.007639 0.430299 0.250687 0.130681 0.200153 0.000023 0.002217 0.407925 0.255329 0.120009 0.192676 0.000000 0.000000
Wherein, on the x/c value representation aerofoil profile suction surface certain point on string of a musical instrument direction with respect to the position of leading edge, the y/c value representation from the string of a musical instrument to the aerofoil profile suction surface on the height of certain point;
The pressure side coordinate of 50% relative thickness aerofoil profile (x/c, y/c)
x/c y/c x/c y/c x/c y/c 0.000000 0.000000 0.151987 -0.182089 0.578967 -0.185534 0.000040 -0.002899 0.167106 -0.189085 0.599019 -0.176495 0.000279 -0.008104 0.183651 -0.196119 0.619649 -0.166781 0.000761 -0.013399 0.201566 -0.203101 0.641027 -0.156281 0.001528 -0.018839 0.220232 -0.209749 0.665649 -0.143864 0.002562 -0.024387 0.239067 -0.215835 0.690205 -0.131457 0.004005 -0.030357 0.258020 -0.221333 0.712183 -0.120544
0.006046 -0.037427 0.276686 -0.226116 0.732834 -0.110618 0.008352 -0.044940 0.294541 -0.230088 0.752959 -0.101286 0.010688 -0.051717 0.310150 -0.233040 0.772030 -0.092776 0.013258 -0.058201 0.322925 -0.234962 0.789558 -0.085311 0.016114 -0.064648 0.334011 -0.236191 0.805729 -0.078795 0.019086 -0.070739 0.344443 -0.236982 0.820581 -0.073176 0.022183 -0.076470 0.354984 -0.237436 0.834376 -0.068328 0.025504 -0.082018 0.366349 -0.237569 0.847834 -0.063985 0.029223 -0.087666 0.378923 -0.237302 0.861344 -0.059990 0.033166 -0.093244 0.392142 -0.236571 0.874662 -0.056403 0.037105 -0.098330 0.405253 -0.235416 0.887721 -0.053232 0.041468 -0.103388 0.418256 -0.233847 0.900119 -0.050554 0.046869 -0.109080 0.431353 -0.231878 0.911716 -0.048385 0.053785 -0.115881 0.444730 -0.229480 0.922833 -0.046637 0.061963 -0.123435 0.458277 -0.226681 0.933648 -0.045249 0.070734 -0.131003 0.471804 -0.223519 0.943961 -0.044226 0.079924 -0.138355 0.485300 -0.219985 0.953625 -0.043561 0.089839 -0.145677 0.498688 -0.216089 0.962703 -0.043230 0.100687 -0.153108 0.512388 -0.211684 0.971401 -0.043205 0.112253 -0.160455 0.527066 -0.206531 0.980029 -0.043476 0.124838 -0.167866 0.543054 -0.200487 0.989178 -0.044090 0.138007 -0.175054 0.560404 -0.193485 1.000000 -0.045000
Wherein, on the x/c value representation aerofoil profile pressure side certain point on string of a musical instrument direction with respect to the position of leading edge, the y/c value representation from the string of a musical instrument to the aerofoil profile pressure side on the height of certain point.
9. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 8, it is characterized in that: 50% relative thickness aerofoil profile, its stall angle is 5 °, it is 1.2258 that lift coefficient reaches maximum numerical value for the first time, after the stall, lift coefficient descends earlier in 5 °～15 ° angle of attack scopes and afterwards rises, and whole lift coefficient value maintains 1.08～1.22, and the stalling characteristics parameter is M Stall=101.25 * 10 -5
10. the blunt trailing edge wind mill airfoil of the big thickness of gang according to claim 8 is characterized in that: described 50% relative thickness aerofoil profile, in 15 °～31 ° big angle of attack scopes, lift coefficient reaches 1.6209 since 1.17 stable risings in the time of 31 °.
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