CN103277245B - 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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CN103277245B
CN103277245B CN201310234549.2A CN201310234549A CN103277245B CN 103277245 B CN103277245 B CN 103277245B CN 201310234549 A CN201310234549 A CN 201310234549A CN 103277245 B CN103277245 B CN 103277245B
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aerofoil profile
thickness
relative
trailing edge
aerofoil
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CN103277245A (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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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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    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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    • Y02E10/72—Wind turbines with rotation axis in wind direction

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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 gang's heavy thickness and design method thereof
Technical field
The invention belongs to horizontal-shaft wind turbine Airfoil Design field, be specifically related to the thick aerofoil profile of gang and the design method thereof that are applicable to large-scale Blades For Horizontal Axis Wind root.
Background technique
The Special Airfoil of Wind Turbine race developing excellent performance is the key of axle pneumatic equipment blades made energy capture rate of improving the standard, and the growth requirement of the R&D target of wind mill airfoil and wind energy conversion system is closely related.In recent years, the fast development of Wind Power In China industry, the wind field of various scale is set up in different regions, and the capacity of new clothes wind energy conversion system constantly increases, and blade dimensions is significantly elongated.
First, different wind-resources environment requires different to pneumatic equipment blades made.Southern china wide geographic area wind-resources is tired, and northern area and coastal area belong to the abundant area of wind-resources but there is various disadvantageous condition.North China and the Northwest's dust storm seriously, very easily pollute pneumatic equipment blades made surface and corrode.Humidity of the air comparatively large and tropical depression in coastal area is on the verge of frequently.Warm and humid air easily causes its geometric profile of corrosion failure to blade surface on the one hand; On the other hand, tropical depression is invaded the structural strength of pneumatic equipment blades made is frequently a huge test.This requirement designs excellent performance under variable working condition condition and stable profile set.
Secondly, the blade of wind energy conversion system increasingly maximizes and proposes requirements at the higher level to the materials and structures characteristic of blade; Meanwhile, the remarkable growth of blade dimensions, the impact of wind shear effect is more obvious, linearly distributes in addition make the flowing reynolds' number of blade each position aerofoil profile widely different at the wind speed of wind energy conversion system running Leaf different parts.These require to develop function admirable and to be applicable in the middle part of blade and the heavy thickness profile set of afterbody along with Re vary stable.
On the other hand, increase profile thickness and trailing edge thickness 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 simultaneously suitably improving aerofoil profile can reduce suction surface adverse pressure gradient, thus 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 obtains reinforcement.Usually, heavy thickness aerofoil profile is applicable to root of blade, and the flowing of this place is usually in the flow separation flowing state of large attack angle, has stronger Three-dimensional Flow characteristic, therefore the heavy 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 being applied to the aerofoil profile inside pneumatic equipment blades made mostly at present 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, range of angles of attack when running well below wind energy conversion system residing for root area aerofoil profile; Lift coefficient stall is violent, less under large attack angle.These defects are unfavorable for the Wind energy extraction rate improving 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 running and has high coefficient of lift combined under the angle of attack and the stable heavy thickness aerofoil with blunt tail edge of off design performance, can meet large scale wind power machine blade structure and pneumatic in demand to aerofoil profile.
The present invention is achieved by the following technical solutions.
The blunt trailing edge wind mill airfoil of gang's heavy thickness, operation the angle of attack under there is high coefficient of lift combined and off design performance stablize, comprise four kinds of heavy thickness aerofoil profiles, it is characterized in that, the maximum relative thickness of described four kinds of heavy thickness aerofoil profiles is followed successively by 45%, 50%, 55% and 60%, and 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 upwards respectively near leading edge place with near trailing edge place; The maximal phase of described four kinds of aerofoil profiles is to camber value between 2% ~ 3.2%, and the tangential relative position of maximum camber is between 74% ~ 79%; 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 the ratio of maximum ga(u)ge between each aerofoil profile upper and lower surfaces and 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 consistent along the distribution characteristics of chord length, and the mean camber line near leading edge place raises up peak, and its tangential relative position is between 22% ~ 23%; To raise up peak near the mean camber line at trailing edge place, its tangential relative position is between 75% ~ 78%.
Preferably, described four kinds of heavy thickness aerofoil with blunt tail edge are used for the root area of pneumatic equipment blades made, be in the scope of 15 ° ~ 30 °, have high coefficient of lift combined and stable off design performance at the operation angle of attack.
Preferably, the design reynolds' number of described four kinds of heavy 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 (x/c, y/c) of table one 45% relative thickness aerofoil profile
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, x/c value represents that on aerofoil profile suction surface, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to aerofoil profile suction surface;
The pressure side coordinate (x/c, y/c) of table two 45% relative thickness aerofoil profile
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, x/c value represents that on profile pressure face, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to profile pressure face.
Further, the aerofoil profile of 45% relative thickness, its stall angle is about 8 °, after stall, and lift coefficient change is mild, and in 8 ° ~ 15 ° range of angles of attack, lift coefficient rises after first slightly declining, and stalling characteristics parameter is M stall=85.56 × 10 -5.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 }
Wherein, cl is lift coefficient, cl maxfor maximum lift coefficient, α is the angle of attack, α stallfor stall angle.
Further, the aerofoil profile of described 45% relative thickness, within the scope of 15 ° ~ 30 ° large attack angle, the lift coefficient of aerofoil profile slightly declines from 1.6, then starts stable rising, 30 ° time, reaches 1.7387.
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 (x/c, y/c) of table three 50% relative thickness aerofoil profile
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 (x/c, y/c) of table four 50% relative thickness aerofoil profile
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, after stall that lift coefficient first time reaches maximum numerical value, and lift coefficient first declines and rises afterwards in 5 ° ~ 15 ° range of angles of attack, overall lift coefficient value maintains 1.08 ~ 1.22, and stalling characteristics parameter is M stall=101.25 × 10 -5.Further, described 50% relative thickness aerofoil profile, within the scope of 15 ° ~ 31 ° large attack angle, lift coefficient is stable from 1.17 to rise, 31 ° time, reach 1.6209.
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 (x/c, y/c) of table five 55% relative thickness aerofoil profile
The pressure side coordinate (x/c, y/c) of table six 55% relative thickness aerofoil profile
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 first time reaches maximum numerical value, lift coefficient after stall steadily maintains 1.02 ~ 1.08 levels drop to about 1 in 5 ° ~ 15 ° range of angles of attack after, and stalling characteristics parameter is M stall=46.41 × 10 -5.Further, described 55% relative thickness aerofoil profile, within the scope of 15 ° ~ 30 ° large attack angle, lift coefficient rises from 1.0308 in the mode of approximately linear change, 30 ° time, reach 1.6797.
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 (x/c, y/c) of table seven 60% relative thickness aerofoil profile
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 (x/c, y/c) of table eight 60% relative thickness aerofoil profile
Further, the aerofoil profile of 60% relative thickness, its stall angle is about 2 °, and maximum lift coefficient value is 0.8165, after stall, and stable rising after lift coefficient slightly drops to about 0.63 in 2 ° ~ 15 ° range of angles of attack, the mild characteristic of stall is M stall=179.17 × 10 -5.Further, the aerofoil profile of described 60% relative thickness, within the scope of 14 ° ~ 30 ° large attack angle, lift coefficient rises from 1.0779 in the mode of approximately linear change, 30 ° time, reach 1.783.
According to a further aspect in the invention, additionally provide a kind of design method for designing above-mentioned aerofoil profile, comprise positive design procedure and mimetic design step, it is characterized in that, in described positive design procedure, from original aerofoil profile, first keep the camber of original aerofoil profile distribute and maximum ga(u)ge position substantially constant, adjustment aerofoil profile relative thickness reach target relative thickness; Keep the relative thickness of aerofoil profile constant afterwards, regulate the trailing edge thickness of aerofoil profile to reach target trailing edge thickness; After completing described positive design procedure, carrying out mimetic design step, in described mimetic design step, by regulating the pressure distribution of airfoil surface, finely tuning the leading edge shape of aerofoil profile, relative thickness and distribution, relatively camber and distribution thereof.
Preferably, in positive design procedure, the trailing edge thickness of described adjustment aerofoil profile reaches target trailing edge thickness, and by keeping relative thickness constant, the mode of amplifying trailing edge along mean camber line symmetry realizes.Preferably, the pressure distribution of described adjustment airfoil surface, mainly regulates three principal elements such as the gradients that the height at leading edge suction surface pressure peak, the chordwise location of pressure spike and pressure spike in the boundary layer of aerofoil profile fall after rise.
Beneficial outcomes: the scarcity of the thick family of aerofoil sections that gang provided by the invention faces when running the heavy thickness aerofoil with blunt tail edge under the angle of attack with high coefficient of lift combined and can making up large scale wind power machine blade design.Large relative thickness and trailing edge thickness effectively can improve the structure attribute of blade.The more important thing is, the design object of this family of aerofoil sections clearly using the respective Reynolds number residing for aerofoil profile during blade actual motion, lift coefficient under large attack angle as pneumatic target, instead of picture previously single reynolds' number, compared with the maximum lift-drag ratio under 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.
Accompanying drawing explanation
Fig. 1 is the basic molded line of heavy thickness aerofoil with blunt tail edge race proposed by the invention;
Fig. 2 is the mean camber line scatter chart of each aerofoil profile proposed by the invention;
Fig. 3 is that each aerofoil profile proposed by the invention is designing the lift coefficient curve under reynolds' number separately;
Fig. 4 to be relative thickness be 45% the plotted curve that changes with Re of wing section lift coefficient;
Fig. 5 to be relative thickness be 50% the plotted curve that changes with Re of wing section lift coefficient;
Fig. 6 to be relative thickness be 55% the plotted curve that changes with Re of wing section lift coefficient;
Fig. 7 to be relative thickness be 60% the plotted curve that changes with Re of wing section lift coefficient;
In figure, 45% represents the aerofoil profile that relative thickness is 45%; 50% represents the aerofoil profile that relative thickness is 50%; 55% represents the aerofoil profile that relative thickness is 55%; 60% represents the aerofoil profile that relative thickness is 60%.
Embodiment
For making object of the present invention, technological scheme and advantage clearly understand, to develop simultaneously embodiment referring to accompanying drawing, invention is further described.
Aerofoil profile proposed by the invention is that the mode adopting positive and negative method to combine obtains.From original aerofoil profile, adopt positive design method, first keep the camber of aerofoil profile to distribute and maximum ga(u)ge position substantially constant, design and obtain the aerofoil profile of four kinds of relative thicknesses; Realize thick trailing edge shape-designing further.Thick trailing edge be designed with two kinds of main thinkings: directly block the tail region of former aerofoil profile or keep relative thickness constant, symmetrically amplifying trailing edge.Directly block thickness and camber distribution that trailing edge can change aerofoil profile significantly, very big to the effect of aerodynamic performance of aerofoil profile, the lift coefficient of aerofoil profile especially can be made to degenerate.A kind of formative method after this adopts, keep relative thickness and maximum ga(u)ge position substantially constant, symmetrical amplify trailing edge, can effectively reduce border adverse pressure gradient, improve the aeroperformance of aerofoil profile.Like this, obtain through initial model design the initial aerofoil profile meeting relative thickness, the basic desired extent of trailing edge thickness and maximum relative thickness position.
In just designing, keep relative thickness constant, improve the trailing edge thickness of aerofoil profile can reduce a certain flox condition under pressure gradient, the separation of Delay boundary conditions layer, obtains higher maximum lift coefficient.This one-phase of mimetic design is optimized for core further with aeroperformance, and the Pressure Distribution of amendment aerofoil profile, improves the aerodynamic parameter of aerofoil profile.Heavy thickness aerofoil profile will occur when the angle of attack is very little to turn twists, and (perhaps can along with separate bubble attached again) forms turbulent boundary layer; The more difficult separation of turbulent boundary layer, when trailing edge thickness is larger, separation point is closer to trailing edge.It is the gradient of the height at leading edge suction surface pressure peak in boundary layer, the chordwise location of pressure spike and pressure spike falling on the most significant Pressure Distribution of Airfoil Aerodynamic Performance impact.By the amendment to this three, come indirectly fine to regulate the leading edge shape of aerofoil profile, relative thickness and distribution, relatively camber and distribution thereof, with the flow separation point reducing aerofoil profile along with the increase of the angle of attack from trailing edge to the speed of leading edge movement, thus it is mild to make aerofoil profile be tending towards change after stall, even continue the process increased with a lift coefficient.Heavy thickness aerofoil profile is in complete turbulence state usually when large attack angle, and the impact by Re is less, has higher Re stability.So repeatedly optimize, obtain the four kinds of aerofoil profiles meeting expected design, as shown in Figure 1.
Fig. 1 is the basic molded line of heavy thickness aerofoil with blunt tail edge race proposed by the invention, as shown in Table 9, the dimensionless profile coordinate of four kinds of corresponding aerofoil profiles is as shown in table one to table eight for the basic geometric parameters of each aerofoil profile. and major parameter is the concrete relative thickness, maximum relative thickness position, relatively camber, maximum camber position, leading-edge radius, trailing edge thickness etc. (numerical value is the comparison value relative to chord length) of aerofoil profile.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 table nine gang heavy thickness aerofoil with blunt tail edge
The maximum ga(u)ge of the four kinds of heavy thickness aerofoil profiles relative position in chord length direction is between 30% ~ 35%, and particularly, upper surface maximum ga(u)ge position is between (0.28 ~ 0.33) times chord length, 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 is consistent along the distribution characteristics of chord length, all on chord length, also just says that aerofoil profile upper surface is thicker; Mean camber line goes out in close leading edge all has the peak that raises up with trailing edge place, 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 camber value, and between (0.020 ~ 0.032) chord length, the chordwise location of maximum camber is between 74% ~ 79%; The leading-edge radius of four kinds of aerofoil profiles is successively between (0.099 ~ 0.125) chord length, and trailing edge thickness increases gradually according to the increase of relative thickness; These effectively ensure that the geometry of family of aerofoil sections is compatible.
Heavy thickness aerofoil with blunt tail edge proposed by the invention is particularly useful for 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, the four kinds of design reynolds' number drafting 45% to 60% four kind of heavy 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 substantially applicable to 10% ~ 30% position of blade exhibition to position.Because the Maximal twist angle of this position blade is restricted, so the especially actual flow angle of attack of root area cross section aerofoil profile excessive (range of angles of attack of the pneumatic equipment blades made root aerofoil profile of 5MW is 12 ° ~ 25 °) within causing maximum chord length position.For heavy thickness aerofoil profile, under this angle of attack, lift curve is in stall rear region usually, and flow boundary layer is also generally turbulent boundary layer, and resistance coefficient is abnormal large.Therefore, in this invention, be main pneumatic target with maximum lift coefficient, large attack angle scope (15 ° ~ 30 °) interior lift coefficient, will along with the vary stable of reynolds number Re with limit lift coefficient.
Are all numerical results of the whirlpool surface element method (RFOIL as known in the art) based on the sticky iteration of viscosity-nothing to the explanation of the aerodynamic characteristics of family of aerofoil sections proposed by the invention, design conditions are design separately naturally to turn the situation of twisting under reynolds' number.Table two gives the key aerodynamic parameter of family of aerofoil sections.Wherein maximum lift coefficient is the maximum value obtained wing section lift coefficient first time.The range of angles of attack that the mild special parameter of stall of aerofoil profile is investigated is here from stall angle to 15 ° of angles of attack.Due under large attack angle, the lift coefficient of aerofoil profile increases (based on numerical result) in the mode of approximately linear again, and the lift feature of aerofoil profile under large attack angle characterizes primarily of the constant interval of lift.Lift coefficient respective under giving 15 ° and 30 ° of angles of attack in table.Because stall angle is less, and what investigate is the stability that within the scope of large attack angle, lift coefficient changes along with Re, so carry out qualitative explanation in this contrast by lift curve section under different Reynolds number.Fig. 3 be family of aerofoil sections numerical solution proposed by the invention obtain naturally turn the condition of twisting design reynolds' number separately under lift coefficient curve.
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
Composition graphs 3 and table ten, illustrate the aeroperformance feature of heavy thickness aerofoil with blunt tail edge race proposed by the invention.
The design reynolds' number of 45% relative thickness aerofoil profile is 4 × 10 6.The stall angle of this aerofoil profile is higher (8 °), therefore lift coefficient first time numerical value when reaching maximum in four kinds of aerofoil profiles also maximum (1.6427).After stall, the lift coefficient change of aerofoil profile is comparatively mild, and in (8 ° ~ 15 °) range of angles of attack, have a process risen after slightly declining, but overall lift coefficient value maintains high level, stalling characteristics parameter is only M stall=85.56 × 10 -5.Within the scope of large attack angle (15 ° ~ 30 °), the lift coefficient of aerofoil profile slightly declines from 1.6, then starts a stable uphill process, 30 ° time, reaches 1.7387.
The design reynolds' number of 50% relative thickness aerofoil profile is 3.5 × 10 6.Along with the increase of relative thickness, the stall angle that this aerofoil profile turns under condition of twisting naturally is 5 ° in advance, it is the process that the lift coefficient after 1.2258. stall has a decline to rise afterwards in (5 ° ~ 15 °) range of angles of attack that lift coefficient first time reaches maximum numerical value, but overall lift coefficient value maintains (1.08 ~ 1.22), stalling characteristics parameter is M stall=101.25 × 10 -5.Within the scope of large attack angle (15 ° ~ 31 °), the lift coefficient of aerofoil profile is stable from 1.17 to rise, 31 ° time, reach 1.6209.
The design reynolds' number of 55% relative thickness aerofoil profile is 3 × 10 6.The stall angle that this aerofoil profile turns under condition of twisting naturally is also 5 °, it is that after lift coefficient after 1.1543. stall drops to about 1 in (5 ° ~ 15 °) range of angles of attack, change is extremely steady that lift coefficient first time reaches maximum numerical value, maintain 1.02 ~ 1.08 levels, so the mild characteristic of stall is only M stall=46.41 × 10 -5.Within the scope of large attack angle (15 ° ~ 30 °), the lift coefficient of aerofoil profile rises from 1.0308 in the mode of approximately linear change, 30 ° time, reach 1.6797.
The design reynolds' number of 60% relative thickness aerofoil profile is 2.5 × 10 6.Due to relative thickness and trailing edge thickness excessive, this aerofoil profile naturally turn lift coefficient under condition of twisting the angle of attack very as a child (2 °) just first time reaches maximum, value is 0.8165.Lift coefficient after stall slightly drops to 0.63(4 ° in (2 ° ~ 15 °) range of angles of attack) the rear stable rising in left and right, the mild characteristic of stall is M stall=179.17 × 10 -5.Within the scope of large attack angle (14 ° ~ 30 °), the lift coefficient of aerofoil profile rises from 1.0779 in the mode of approximately linear change, 30 ° time, reach 1.783.
To sum up, family of aerofoil sections first time proposed by the invention reach maximum value after through going through a mild stall process, lift coefficient continues to increase.Within the scope of large attack angle, the rising that lift coefficient is continual and steady is also in higher level.Between 15 ° to the 30 ° angles of attack, the roughly change (45% thickness airfoil performance is excellent, and the lift coefficient within the scope of this is 1.3812 ~ 1.7387) of approximately linear between 1.0 to 1.7 of the lift coefficient of this family of aerofoil sections.So reach the pneumatic target had within the scope of large attack angle compared with high coefficient of lift combined.
In the stability that the lift coefficient of aerofoil profile changes with Re, according to numerical result, Fig. 4 illustrates the change of lift curve along with Re of 45% aerofoil profile, Fig. 5 illustrates the change of lift curve along with Re of 50% aerofoil profile, Fig. 6 illustrates the change of lift curve along with Re of 55% aerofoil profile, and Fig. 7 then illustrates the change of the lift curve of 60% aerofoil profile.Can significantly find out from figure, this group heavy thickness aerofoil with blunt tail edge that the present invention proposes, running the reynolds' number stability in range of angles of attack with excellence, is conducive to wind-driven generator and obtains more stable output.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within the scope of the present invention.

Claims (19)

1. the blunt trailing edge wind mill airfoil of gang's heavy thickness, has high coefficient of lift combined under the operation angle of attack and off design performance is stablized, and comprises four kinds of heavy thickness aerofoil profiles, it is characterized in that,
The maximum relative thickness of described four kinds of heavy thickness aerofoil profiles is followed successively by 45%, 50%, 55% and 60%, and 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 upwards respectively near leading edge place with near trailing edge place;
The maximal phase of described four kinds of aerofoil profiles is to camber value between 2% ~ 3.2%, and the tangential relative position of maximum camber is between 74% ~ 79%;
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 the ratio of maximum ga(u)ge between each aerofoil profile upper and lower surfaces and 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 gang according to claim 1 heavy thickness, it is characterized in that: the mean camber line of described four aerofoil profiles is consistent along the distribution characteristics of chord length, to raise up peak near the mean camber line at leading edge place, its tangential relative position is between 22% ~ 23%; To raise up peak near the mean camber line at trailing edge place, its tangential relative position is between 75% ~ 78%.
3. the blunt trailing edge wind mill airfoil of gang according to claim 1 heavy thickness, it is characterized in that, described four kinds of heavy thickness aerofoil with blunt tail edge are used for the root area of pneumatic equipment blades made, be in the scope of 15 ° ~ 30 °, have high coefficient of lift combined and stable off design performance at the operation angle of attack.
4. the blunt trailing edge wind mill airfoil of gang according to claim 1 heavy thickness, is characterized in that: the design reynolds' number of described four kinds of heavy 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 gang according to claim 4 heavy thickness, 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 (x/c, y/c) of 45% relative thickness aerofoil profile
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, x/c value represents that on aerofoil profile suction surface, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to aerofoil profile suction surface;
The pressure side coordinate (x/c, y/c) of 45% relative thickness aerofoil profile
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, x/c value represents that on profile pressure face, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to profile pressure face.
6. the blunt trailing edge wind mill airfoil of gang according to claim 5 heavy thickness, it is characterized in that: the aerofoil profile of 45% relative thickness, its stall angle is about 8 °, after stall, lift coefficient change is mild, in 8 ° ~ 15 ° range of angles of attack, lift coefficient rises after first slightly declining, and stalling characteristics parameter is M stall=85.56 × 10 -5.
7. the blunt trailing edge wind mill airfoil of gang according to claim 6 heavy thickness, it is characterized in that: the aerofoil profile of described 45% relative thickness, within the scope of 15 ° ~ 30 ° large attack angle, the lift coefficient of aerofoil profile slightly declines from 1.6, then start stable rising, 30 ° time, reach 1.7387.
8. the blunt trailing edge wind mill airfoil of gang according to claim 4 heavy thickness, 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 (x/c, y/c) of 50% relative thickness aerofoil profile
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, x/c value represents that on aerofoil profile suction surface, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to aerofoil profile suction surface;
The pressure side coordinate (x/c, y/c) of 50% relative thickness aerofoil profile
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, x/c value represents that on profile pressure face, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to profile pressure face.
9. the blunt trailing edge wind mill airfoil of gang according to claim 8 heavy thickness, it is characterized in that: 50% relative thickness aerofoil profile, its stall angle is 5 °, it is 1.2258 that lift coefficient first time reaches maximum numerical value, after stall, lift coefficient first declines and rises afterwards in 5 ° ~ 15 ° range of angles of attack, and overall lift coefficient value maintains 1.08 ~ 1.22, and stalling characteristics parameter is M stall=101.25 × 10 -5.
10. the blunt trailing edge wind mill airfoil of gang according to claim 8 heavy thickness, is characterized in that: described 50% relative thickness aerofoil profile, and within the scope of 15 ° ~ 31 ° large attack angle, lift coefficient is stable from 1.17 to rise, 31 ° time, reach 1.6209.
The blunt trailing edge wind mill airfoil of 11. gang according to claim 4 heavy thickness, is characterized in that: 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 (x/c, y/c) of 55% relative thickness aerofoil profile
Wherein, x/c value represents that on aerofoil profile suction surface, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to aerofoil profile suction surface;
The pressure side coordinate (x/c, y/c) of 55% relative thickness aerofoil profile
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
Wherein, x/c value represents that on aerofoil profile suction surface, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to aerofoil profile suction surface.
The blunt trailing edge wind mill airfoil of 12. gang according to claim 11 heavy thickness, it is characterized in that: 55% relative thickness aerofoil profile, its stall angle is 5 °, it is 1.1543 that lift coefficient first time reaches maximum numerical value, after lift coefficient after stall drops to about 1 in 5 ° ~ 15 ° range of angles of attack, steadily maintain 1.02 ~ 1.08 levels, stalling characteristics parameter is M stall=46.41 × 10 -5.
The blunt trailing edge wind mill airfoil of 13. gang according to claim 11 heavy thickness, it is characterized in that: described 55% relative thickness aerofoil profile, within the scope of 15 ° ~ 30 ° large attack angle, lift coefficient rises from 1.0308 in the mode of approximately linear change, 30 ° time, reach 1.6797.
The blunt trailing edge wind mill airfoil of 14. gang according to claim 4 heavy thickness, is characterized in that: 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 (x/c, y/c) of 60% relative thickness aerofoil profile
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
Wherein, x/c value represents that on aerofoil profile suction surface, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to aerofoil profile suction surface;
The pressure side coordinate (x/c, y/c) of 60% relative thickness aerofoil profile
x/c y/c x/c y/c x/c y/c 0.000000 0.000000 0.151975 -0.221085 0.578931 -0.230821 0.000040 -0.004409 0.167092 -0.229772 0.598983 -0.221007 0.000279 -0.008441 0.183636 -0.238491 0.619612 -0.210463 0.000761 -0.016731 0.201550 -0.247123 0.640989 -0.199094 0.001527 -0.021985 0.220215 -0.255294 0.665611 -0.185684 0.002561 -0.028859 0.239049 -0.262722 0.690166 -0.172286 0.004004 -0.036012 0.258001 -0.269357 0.712143 -0.160561 0.006045 -0.044574 0.276666 -0.275060 0.732793 -0.149910 0.008351 -0.053444 0.294520 -0.279733 0.752918 -0.139896 0.010686 -0.061527 0.310128 -0.283106 0.771988 -0.130770 0.013255 -0.069269 0.322902 -0.285220 0.789514 -0.122778 0.016111 -0.076977 0.333988 -0.286542 0.805684 -0.115809 0.019083 -0.084269 0.344418 -0.287352 0.820535 -0.109806 0.022180 -0.091116 0.354959 -0.287792 0.834331 -0.104633 0.025501 -0.097826 0.366323 -0.287884 0.847787 -0.099998 0.029219 -0.104673 0.378897 -0.287516 0.861296 -0.095734 0.033161 -0.111432 0.392115 -0.286660 0.874614 -0.091905 0.037100 -0.117589 0.405225 -0.285348 0.887672 -0.088524 0.041464 -0.123748 0.418228 -0.283597 0.900070 -0.085675 0.046865 -0.130742 0.431324 -0.281418 0.911666 -0.083373 0.053780 -0.139134 0.444701 -0.278786 0.922782 -0.081522 0.061957 -0.148459 0.458247 -0.275735 0.933597 -0.080055 0.070728 -0.157795 0.471774 -0.272278 0.943910 -0.078984 0.079917 -0.166862 0.485270 -0.268402 0.953574 -0.078296 0.089832 -0.175908 0.498657 -0.264122 0.962652 -0.077971 0.100678 -0.185113 0.512356 -0.259297 0.971349 -0.077967 0.112243 -0.194222 0.527034 -0.253672 0.979977 -0.078279 0.124827 -0.203424 0.543021 -0.247094 0.989125 -0.078951 0.137995 -0.212354 0.560369 -0.239469 1.000000 -0.080000
Wherein, x/c value represents that on profile pressure face, certain point is relative to the position of leading edge on string of a musical instrument direction, and y/c value represents the height of certain point from the string of a musical instrument to profile pressure face.
The blunt trailing edge wind mill airfoil of 15. gang according to claim 14 heavy thickness, it is characterized in that: the aerofoil profile of 60% relative thickness, its stall angle is about 2 °, maximum lift coefficient value is 0.8165, after stall, stable rising after lift coefficient slightly drops to about 0.63 in 2 ° ~ 15 ° range of angles of attack, the mild characteristic of stall is M stall=179.17 × 10 -5.
The blunt trailing edge wind mill airfoil of 16. gang according to claim 14 heavy thickness, it is characterized in that: the aerofoil profile of described 60% relative thickness, within the scope of 14 ° ~ 30 ° large attack angle, lift coefficient rises from 1.0779 in the mode of approximately linear change, 30 ° time, reach 1.783.
17. 1 kinds of Airfoil Design methods, for designing the blunt trailing edge wind mill airfoil of gang's heavy thickness described in above-mentioned any one claim, comprising positive design procedure and mimetic design step, it is characterized in that,
In described positive design procedure, from original aerofoil profile, first keep the camber of original aerofoil profile distribute and maximum ga(u)ge position substantially constant, adjustment aerofoil profile relative thickness reach target relative thickness; Keep the relative thickness of aerofoil profile constant afterwards, regulate the trailing edge thickness of aerofoil profile to reach target trailing edge thickness;
After completing described positive design procedure, carrying out mimetic design step, in described mimetic design step, by regulating the pressure distribution of airfoil surface, finely tuning the leading edge shape of aerofoil profile, relative thickness and distribution thereof and relative camber and distribution thereof.
18. Airfoil Design methods according to claim 17, is characterized in that, in positive design procedure, the trailing edge thickness of described adjustment aerofoil profile reaches target trailing edge thickness, and by keeping relative thickness constant, the mode of amplifying trailing edge along mean camber line symmetry realizes.
19. Airfoil Design methods according to claim 17 or 18, it is characterized in that, the pressure distribution of described adjustment airfoil surface, mainly regulates the gradient that the height at leading edge suction surface pressure peak, the chordwise location of pressure spike and pressure spike in the boundary layer of aerofoil profile fall after rise.
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