CN203374428U - Family of wind-power airfoil profiles with large thickness and blunt trailing edges - Google Patents

Abstract

The utility model discloses a family of wind-power airfoil profiles with large thickness and blunt trailing edges. The family of wind-power airfoil profiles has high lift coefficient at the angle of attack. The family includes four types of wind-power airfoil profiles sequentially having relative thickness of 45%, 50%, 55% and 60% and trailing edge thickness of 7%, 9%, 12% and 16%. Designed Reynolds numbers of the four types of wind-power airfoil profiles are equal to 4.0*106, 3.5*106, 3.0*106 and 2.5*106 sequentially according to increase of the relative thickness. The stability of the lift coefficient varying along with the Reynolds numbers is the main consideration of the design objective according to variation characteristics of the lift coefficient of the root area within a large range of the angle of attack. As numerical prediction results proved, the lift coefficient of the four types of airfoil profiles with large thickness and blunt trailing edges is increased continuously stably and stays at a high level. With the family of wind-power airfoil profiles with large thickness and blunt trailing edges, structural strength and rigidity of blades can be improved and wind turbines have more efficient and stable outputs.

Description

The blunt trailing edge wind mill airfoil of the large thickness of gang

Technical field

The utility model belongs to horizontal-shaft wind turbine Airfoil Design field, is specifically related to be applicable to gang's thick wing type profile of large-scale Blades For Horizontal Axis Wind root.

Background technique

The Special Airfoil of Wind Turbine family that develops 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 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.Humidity of the air 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, the structural strength that tropical depression is invaded pneumatic equipment blades made frequently is a huge test.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 increasingly maximizes the material of blade and structural characteristics has been proposed to requirements at the higher level; Simultaneously, the phenomenal growth of blade dimensions, the impact of wind shear effect is more obvious, is linear distribution at the wind speed of wind energy conversion system running Leaf different parts in addition and makes the mobile reynolds' number of each position aerofoil profile of blade widely different.These requirements are developed function admirable and along with the large 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 simultaneously suitably improves aerofoil profile 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, large thickness aerofoil profile is applicable to root of blade, and the mobile usually flow separation flowing state in the large angle of attack in this place, have stronger Three-dimensional Flow characteristic, therefore the large 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 at present the aerofoil profile of pneumatic equipment blades made inboard 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 while moving well below wind energy conversion system; Lift coefficient stall is violent, less under the large angle of attack.These defects 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 utility model purpose is to propose gang and has high coefficient of lift combined and the stable large thickness aerofoil with blunt tail edge of off design performance in operation under the angle of attack, can meet the large scale wind power machine blade structure and pneumatic aspect to the demand of aerofoil profile.

The utility model is achieved through the following technical solutions.

The blunt trailing edge wind mill airfoil of the large thickness of gang, comprise four kinds of large thickness aerofoil profiles, it is characterized in that, the maximum relative thickness of described four kinds of large 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 having respectively a protruding peak made progress near the leading edge place with near the trailing edge place; The maximal phase of described four kinds of aerofoil profiles is to the 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 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, 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, 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, on 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 the height of certain point;

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, on 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 the height of certain point.

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

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

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

Useful result: the scarcity of the thick family of aerofoil sections that the large thickness aerofoil with blunt tail edge that the gang that the utility model provides has high coefficient of lift combined under the angle of attack in operation faces in the time of can making up the large scale wind power machine blade design.Large 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 using the blade actual motion lift coefficient under the residing reynolds' number separately of aerofoil profile condition, the large angle of attack as pneumatic target, rather than picture before single reynolds' number, than 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.

The accompanying drawing explanation

The basic molded line that Fig. 1 is the large thickness aerofoil with blunt tail edge family that proposes of the utility model;

The mean camber line scatter chart that Fig. 2 is each aerofoil profile of proposing of the utility model;

Fig. 3 is that each aerofoil profile of proposing of the utility model is at the lift coefficient curve designed separately under reynolds' number;

Fig. 4 is the plotted curve that the relative thickness wing section lift coefficient that is 45% changes with Re;

Fig. 5 is the plotted curve that the relative thickness wing section lift coefficient that is 50% changes with Re;

Fig. 6 is the plotted curve that the relative thickness wing section lift coefficient that is 55% changes with Re;

Fig. 7 is the plotted curve that the relative thickness wing section lift coefficient that is 60% changes with Re;

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 the purpose of this utility model, technological scheme and advantage clearer, referring to the accompanying drawing embodiment that develops simultaneously, invention is further described.

The basic molded line that Fig. 1 is the large thickness aerofoil with blunt tail edge family that proposes of the utility model, 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 as shown in table eight. the concrete relative thickness that major parameter is aerofoil profile, maximum relative thickness position, (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-) mean respectively the chordwise location of upper and lower surface maximum ga(u)ge position.

The basic geometric parameters of the large thickness aerofoil with blunt tail edge of table nine gang

The maximum ga(u)ge of four kinds of large thickness aerofoil profiles is at the relative position of chord length direction 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 the aerofoil profile upper surface is thicker; Mean camber line is all having the peak that raises up near leading edge place and 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 the 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 how much of effectively having guaranteed family of aerofoil sections are compatible.

The large thickness aerofoil with blunt tail edge that the utility model proposes 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 large 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 basically be applicable to 10%～30% position of blade exhibition to position.Because the Maximal twist angle of this position blade is restricted, so cause the maximum chord length position to take the actual flow angle of attack excessive (angle of attack scope of the pneumatic equipment blades made root aerofoil profile of 5MW is 12 °～25 °) of interior especially root area cross section aerofoil profile.For large thickness aerofoil profile, under this angle of attack, lift curve is usually in the stall rear region, and flow boundary layer also is generally turbulent boundary layer, and resistance coefficient is extremely large.Therefore, in this invention, take maximum lift coefficient, the large interior lift coefficient of angle of attack scope (15 °～30 °) is main pneumatic target, and limit lift coefficient will be along with the vary stable of reynolds number Re simultaneously.

The explanation of the aerodynamic characteristics of the family of aerofoil sections that the utility model is proposed all is based on the numerical result of the vortex sheet unit method (RFOIL as known in the art) of the sticky iteration of viscosity-nothing, and design conditions are to design separately naturally to turn the situation of twisting under 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 is here from stall angle to the 15 ° angle of attack.Due under the large angle of attack, 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 the large angle of attack mainly characterized by the constant interval of lift.Provided lift coefficient separately under 15 ° and 30 ° of angles of attack in table.Because stall angle is less, and what investigate is the stability that lift coefficient changes along with Re in large angle of attack scope, thus this with lift curve section under different Reynolds number to recently qualitative explanation.Fig. 3 is that the condition of twisting that naturally turns that family of aerofoil sections numerical solution that the utility model proposes obtains designs the lift coefficient curve under reynolds' number separately.

The definition of stalling characteristics parameter is as follows:

$M_{\mathrm{stall}}=\max \{\frac{{(\mathrm{cl}-{\mathrm{cl}}_{\max })}^2}{\mathrm{\&alpha;}-{\mathrm{\&alpha;}}_{\mathrm{stall}}},{\mathrm{\&alpha;}}_{\mathrm{stall}}<\mathrm{\&alpha;}<15,\mathrm{\&alpha;}\&Element;Z\}$

The basic aerodynamic parameter of each aerofoil profile of table ten

In conjunction with Fig. 3 and table ten, the aeroperformance feature of the large thickness aerofoil with blunt tail edge family that illustrates that the utility model proposes.

The design reynolds' number of 45% relative thickness aerofoil profile is 4 * 10 ⁶.The 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 stall, the lift coefficient of aerofoil profile changes comparatively mild, a process risen after slightly descending is arranged in (8 °～15 °) angle of attack scope, but whole lift coefficient value maintains high level, and the stalling characteristics parameter is only M _stal=85.56 * 10 ^-5.In large angle of attack scope (15 °～30 °), the lift coefficient of aerofoil profile slightly descends since 1.6, then starts a stable uphill process, reaches 1.7387. in the time of 30 °

The design reynolds' number of 50% relative thickness aerofoil profile is 3.5 * 10 ⁶.Increase along with relative thickness, the stall angle that this aerofoil profile turns under the 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 °) 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), the stalling characteristics parameter is M _stal=101.25 * 10 ^-5.In large angle of attack scope (15 °～31 °), the lift coefficient of aerofoil profile, since 1.17 stable risings, reaches 1.6209. in the time of 31 °

The design reynolds' number of 55% relative thickness aerofoil profile is 3 * 10 ⁶.The stall angle that this aerofoil profile turns under the condition of twisting naturally is also 5 °, lift coefficient reach for the first time maximum numerical value be after lift coefficient after 1.1543. stall drops to 1 left and right in (5 °～15 °) angle of attack scope, change extremely steady, maintain 1.02～1.08 levels, so the mild characteristic of stall is only M _stal=46.41 * 10 ^-5.In large 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 ⁶.Due to relative thickness and trailing edge thickness excessive, this aerofoil profile naturally turn lift coefficient under the condition of twisting the angle of attack very as a child (2 °) just reached maximum for the first time, value is 0.8165.Lift coefficient after stall slightly drops to 0.63(4 ° in (2 °～15 °) angle of attack scope) rear stable rising the in left and right, the mild characteristic of stall is M _stal=179.17 * 10 ^-5.In large 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, the family of aerofoil sections that the utility model proposes reaches maximum value for the first time by going through a mild stall process, and lift coefficient continues to increase.In large angle of attack scope, the rising that lift coefficient is continual and steady 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 in large angle of attack scope and there is the pneumatic target than high coefficient of lift combined.

Aspect the stability changed with Re at the lift coefficient of aerofoil profile, according to numerical result, Fig. 4 has showed the variation of the lift curve of 45% aerofoil profile along with Re, Fig. 5 has showed the variation of the lift curve of 50% aerofoil profile along with Re, Fig. 6 has showed the variation of the lift curve of 55% aerofoil profile along with Re, and Fig. 7 has showed the variation of the lift curve of 60% aerofoil profile.From figure, can significantly find out, this utility model proposes organized large 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 foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all within spirit of the present utility model and principle, any modification of making, be equal to replacement, improvement etc., within all should being included in scope of the present utility model.

Claims (6)

1. the blunt trailing edge wind mill airfoil of the large thickness of gang, comprise four kinds of large thickness aerofoil profiles, it is characterized in that,

The maximum relative thickness of described four kinds of large 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 having respectively a protruding peak made progress near the leading edge place with near the trailing edge place;

The maximal phase of described four kinds of aerofoil profiles is to the 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 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 large thickness of gang according to claim 1 is characterized in that: the mean camber line of each described four aerofoil profiles, 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%.

3. the blunt trailing edge wind mill airfoil of the large thickness of gang according to claim 1, 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:

Wherein, on 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 the height of certain point;

Wherein, on 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 the height of certain point.

4. the blunt trailing edge wind mill airfoil of the large thickness of gang according to claim 1, 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

Wherein, on 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 the height of certain point;

Wherein, on 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 the height of certain point.

5. the blunt trailing edge wind mill airfoil of the large thickness of gang according to claim 1, it 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:

Wherein, on 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 the height of certain point;

Wherein, on 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 the height of certain point.

6. the blunt trailing edge wind mill airfoil of the large thickness of gang according to claim 1, it 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:

Wherein, on 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 the height of certain point;

Wherein, on 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 the height of certain point.

Images