CN112922774B - High-lift wind power wing type - Google Patents
High-lift wind power wing type Download PDFInfo
- Publication number
- CN112922774B CN112922774B CN202110287274.3A CN202110287274A CN112922774B CN 112922774 B CN112922774 B CN 112922774B CN 202110287274 A CN202110287274 A CN 202110287274A CN 112922774 B CN112922774 B CN 112922774B
- Authority
- CN
- China
- Prior art keywords
- airfoil
- section
- profile
- naca4412
- unit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000008602 contraction Effects 0.000 claims description 25
- 230000008859 change Effects 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 4
- 238000000926 separation method Methods 0.000 abstract description 8
- 238000010521 absorption reaction Methods 0.000 abstract description 5
- 230000000052 comparative effect Effects 0.000 description 20
- 238000013461 design Methods 0.000 description 11
- 230000008901 benefit Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical class CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 108090000623 proteins and genes Proteins 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/0608—Rotors characterised by their aerodynamic shape
- F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a high-lift wind turbine airfoil, which takes an S809 airfoil as a basic contour, multiplies the chord length of an NACA4412 airfoil by a scale factor alpha and then reduces, and the contracted airfoil rotates by a fixed angle beta based on a trailing edge point; at the trailing edge, when the S809 airfoil upper surface ordinate is less than the NACA4412 airfoil ordinate, this portion of the S809 airfoil upper surface is replaced by the NACA4412 airfoil surface. The middle section of the upper surface of the airfoil is smooth and excessive, the reverse pressure gradient of the airfoil under a large attack angle is ensured to be smaller, the airflow separation is further inhibited, the airfoil has a larger lift coefficient and a larger stall attack angle, the resistance is smaller, and the wind energy absorption efficiency of the wind wheel of the wind generating set is improved.
Description
Technical Field
The invention belongs to the technical field of wind power generation, and particularly relates to a high-lift wind turbine airfoil for a wind generating set.
Background
For the geometric shape of a wind power blade, the aerofoil is a gene which forms the blade, and the aerodynamic performance of the aerofoil directly influences the aerodynamic performance of the wind turbine blade, so that the design of the aerodynamic shape of the wind turbine blade of the wind power generator set is not separated from the design of the aerofoil. Prior to the 80 s of the last century, aerofoils were commonly used for wind turbine airfoils. However, aerofoils are usually designed under the transonic condition, the aerodynamic performance cannot be effectively ensured under the low-speed condition, and in addition, the aerofoils have the defects of smaller thickness and incapability of meeting the structural requirements, and meanwhile, the aerofoils have serious stall under a large attack angle. Therefore, the current research on aerofoils is difficult to meet the design requirements of wind wheels. Therefore, from the beginning of the 80 th century, the demand for high performance wind turbine dedicated airfoils is increasing with the trend of increasing wind turbine blade size. The research of special wing profiles of large-scale wind turbines is carried out by a plurality of foreign institutions in the last century, great achievements are obtained, and a plurality of series of special wing profiles of wind turbines are formed, such as NACA series wing profiles designed by National Aviation Space Agency (NASA), NREL-S series wing profiles designed by National Renewable Energy Laboratory (NREL), DU series wing profiles designed by the university of Delft of Netherlands, denmarkSeries of wing profiles, FFA series of wing profiles designed by Swedish aviation institute, and the like are adopted by a plurality of wind power enterprises, and play a vital role in improving the performance of the wind driven generator.
At present, for example, an existing vertical axis wind turbine mostly adopts an S809 airfoil, and the vicinity of the trailing edge of the suction surface of the airfoil is in smooth transition, so that the aerodynamic performance of the airfoil can effectively improve the wind energy absorption efficiency of a wind wheel, thereby improving the economic efficiency of the wind turbine. However, although the wing type can ensure that the wing type has lower resistance coefficient under a small attack angle, air flow separation is easy to occur under a large attack angle, so that the lift coefficient is reduced, the resistance coefficient is increased, the economic benefit of the wind wheel of the wind turbine is reduced, and the aerodynamic efficiency of the vertical axis wind turbine is low under a low wind speed.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a high-lift wind turbine airfoil for a wind generating set, which can improve the lift coefficient, realize larger stall attack angle and smaller resistance, and further improve the wind energy absorption efficiency of a wind wheel of the wind generating set.
The invention is realized in such a way that a high-lift wind turbine airfoil takes the curve profile of an S809 airfoil as a prototype, and the structure of the high-lift wind turbine airfoil is described as follows:
Respectively carrying out front projection on the S809 airfoil profile and the NACA4412 airfoil profile in the same X-Y coordinate system to respectively obtain an S809 airfoil profile and an NACA4412 airfoil profile, and overlapping the S809 airfoil profile with the rear edge point O of the NACA4412 airfoil profile;
Shrinking the NACA4412 airfoil profile as a whole by a scaling factor alpha, and rotating the shrunk NACA4412 airfoil profile by an angle beta with the trailing edge point O as a center so that the NACA4412 airfoil profile intersects the upper chord of the S809 airfoil profile at a point A (x, y);
When the ordinate y value in point A is less than the maximum ordinate value of the NACA4412 airfoil profile, the face between NACA4412 airfoils O-A is substituted for the face between S809 airfoils O-A.
Preferably, the value range of the scale factor alpha is 0.2-0.5.
Preferably, the outer surface of the high-lift wind turbine airfoil consists of S1-S5 sections which are connected end to end in sequence, wherein the S1-S3 sections form the upper surface of the airfoil, and the S4-S5 sections form the lower surface of the airfoil; the S1 section and the S5 end are butted at a front edge point, the S3 section and the S4 section are butted at a rear edge point O, and the S3 section is a surface between the NACA4412 aerofoils O-A; wherein,
The S1 section and the S5 section are front edge contraction sections of the wing sections; s2, the upper surface smooth transition section of the wing section; s3 is the trailing edge section of the upper surface of the airfoil; s4, the section is a trailing edge section of the lower surface of the airfoil;
the S3 section is changed according to the scale factor, and the S1 section, the S2 section, the S4 section and the S5 section are changed along with the change of the S3 section on the premise of keeping the curve profile consistent with the curve profile of the S809 wing section.
Preferably, the camber line of the airfoil of the high-lift wind turbine is S-shaped, the front section of the camber line is concave, the rear section of the camber line is convex upwards, and the intersection point of the camber line and the chord line of the airfoil is positioned at 0.46 unit;
the maximum thickness of the airfoil is 0.199 unit, the chord direction position corresponding to the maximum thickness is 0.349 unit from the front edge point, and the included angle of the rear edge is 13.36 degrees;
The length of the S1 section is more than 0.0 unit and less than 0.39 unit; the length of the S2 section is more than 0.39 unit and less than 0.85 unit; the length of the S3 section is more than 0.85 unit and less than 1.0 unit; the length of the S4 section is more than 0.32 unit and less than 1.0 unit; s5 has a length of greater than 0.0 units and less than 0.32 units;
wherein 1 of said units is equal to the chord length of said airfoil.
Compared with the defects and shortcomings of the prior art, the invention has the following beneficial effects: the invention provides a high-lift wing profile suitable for a wind turbine, which is smooth and excessive in the middle section position of the upper surface of the wing profile, ensures that the reverse pressure gradient of the wing profile is smaller under a large attack angle, further inhibits air flow separation, has a larger lift coefficient, a larger stall attack angle and smaller resistance, and improves the wind energy absorption efficiency of a wind wheel of the wind turbine generator set.
Drawings
FIG. 1 is a geometric configuration of an airfoil of the present invention;
FIG. 2 is a geometric configuration of an airfoil of the present invention;
FIG. 3 is a geometric comparison of the airfoil of the present invention with a comparison airfoil 1; the comparative airfoil profile 1 is a classical wind turbine airfoil profile S809;
1-3 above, O (1.0, 0) is the trailing edge point, and point A (x, y) is the upper chord intersection of the NACA4412 airfoil profile and the S809 airfoil profile; the solid line indicated by an arrow 1 is the upper chord edge of the airfoil of the invention, the combined line of the solid line and the broken line indicated by an arrow 2 is the upper chord edge of the existing S809 airfoil, and the broken line indicated by an arrow NACA4412 is the whole outline of the NACA4412 airfoil which is contracted by a scale factor alpha and rotates by an angle beta with a trailing edge point O as the center;
FIG. 4 is a comparison of the turbulence viscosity of the airfoil of the present invention and a comparison airfoil 1; wherein, figure A is a comparative airfoil 1, and figure B is an airfoil of the present invention;
FIG. 5 is a surface pressure characteristic curve comparison of an airfoil of the present invention with a comparative airfoil 1;
FIG. 6 is a graph comparing the lift drag bit curves of the airfoil of the present invention with the comparative airfoil 1;
In the above fig. 5 to 6, the line 1 is the airfoil of the present invention, and the line 2 is the comparative airfoil 1; calculating the state: ma=0.108, re=1×10 6, incoming flow angle of attack 9 °;
FIG. 7 is a geometric profile of an airfoil of the present invention at different contraction scale factors;
FIG. 8 is a comparison of drag characteristics of airfoils of the present invention for different contraction scale factors;
FIG. 9 is a comparison of lift characteristics of airfoils of the present invention for different contraction scale factors;
FIG. 10 is a geometric profile of an airfoil of the present invention with different fixed angles of rotation;
FIG. 11 is a comparison of drag characteristics of an airfoil of the present invention at different angles of rotation;
FIG. 12 is a comparison of lift characteristics of airfoils of the present invention at different angles of rotation.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail with reference to the accompanying drawings and examples, wherein the examples are theoretical calculation analysis of the present invention. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The invention discloses a high-lift wind turbine airfoil, which is combined with the structures shown in figures 1-3, wherein the curve profile of an S809 airfoil is taken as a prototype, and the structure of the high-lift wind turbine airfoil is described as follows in the forming process:
Respectively carrying out front projection on the S809 airfoil profile and the NACA4412 airfoil profile in the same X-Y coordinate system to respectively obtain an S809 airfoil profile and an NACA4412 airfoil profile, and overlapping the S809 airfoil profile with the rear edge point O of the NACA4412 airfoil profile;
Shrinking the NACA4412 airfoil profile as a whole by a scaling factor alpha, and rotating the shrunk NACA4412 airfoil profile by an angle beta with the trailing edge point O as a center so that the NACA4412 airfoil profile intersects the upper chord of the S809 airfoil profile at a point A (x, y);
When the ordinate y value in point A is less than the maximum ordinate value of the NACA4412 airfoil profile, the face between NACA4412 airfoils O-A is substituted for the face between S809 airfoils O-A.
In the embodiment of the invention, main design indexes of the high-lift wind wing type are as follows: (1) The Reynolds number is designed to be 100 ten thousand orders, and the Mach number is designed to be 0.1; (2) has good airflow separation inhibition characteristics; (3) good surface pressure characteristics; (4) has good rise resistance characteristics; (5) stall characteristics are relaxed. The scale factor α can be set to a value ranging from 0.2 to 0.5 based on these indices.
In the practical application process of the invention, the outer surface of the high-lift wind turbine airfoil is composed of S1-S5 sections which are connected end to end in sequence, the S1-S3 sections form the upper surface of the airfoil, and the S4-S5 sections form the lower surface of the airfoil; the S1 section and the S5 end are butted at a front edge point, the S3 section and the S4 section are butted at a rear edge point O, and the S3 section is a surface between the NACA4412 aerofoils O-A; wherein, the S1 section and the S5 section are front edge contraction sections of the wing section; s2, the upper surface smooth transition section of the wing section; s3 is the trailing edge section of the upper surface of the airfoil; s4, the section is a trailing edge section of the lower surface of the airfoil; the S3 section is changed according to the scale factor, and the S1 section, the S2 section, the S4 section and the S5 section are changed along with the change of the S3 section on the premise of keeping the curve profile consistent with the curve profile of the S809 wing section.
More specifically, as a preferred embodiment, the high lift wind turbine airfoil provided by the invention has an S-shaped camber line, wherein the front section of the camber line is concave, the rear section of the camber line is convex upwards, and the intersection point of the camber line and the chord line of the airfoil is positioned at 0.46 unit; the maximum thickness of the airfoil is 0.199 unit, the chord direction position corresponding to the maximum thickness is 0.349 unit from the front edge point, and the included angle of the rear edge is 13.36 degrees; the length of the S1 section is more than 0.0 unit and less than 0.39 unit; the length of the S2 section is more than 0.39 unit and less than 0.85 unit; the length of the S3 section is more than 0.85 unit and less than 1.0 unit; the length of the S4 section is more than 0.32 unit and less than 1.0 unit; s5 has a length of greater than 0.0 units and less than 0.32 units; wherein 1 of said units is equal to the chord length of said airfoil.
In order to embody the airfoil characteristics of the high-lift wind turbine provided by the invention, the embodiment of the invention is compared by the following experimental examples, so that the advantages of the airfoil of the high-lift wind turbine provided by the invention are verified. The aerofoil aerodynamic analysis software (solving the RANS equation) is adopted to carry out aerodynamic performance analysis, and the calculated state parameters are as follows: angle of attack of incoming flow: 9 deg., mach number 0.108, reynolds number 1X 10 6.
1. Verification
The classical wind turbine airfoil S809 is taken as a comparison airfoil 1, compared with the airfoil of the invention, and the difference of aerodynamic performance of the airfoil of the invention and the comparison airfoil is analyzed and compared.
FIG. 3 shows the geometrical comparison of the airfoil of the invention (design with a contraction scale factor α of 0.3 and a rotation angle β of 9 °) with a comparative airfoil 1; FIG. 4 is a comparison of turbulence viscosity for an airfoil of the present invention versus a comparative airfoil 1; FIG. 5 is a surface pressure characteristic curve comparison of an airfoil of the present invention with a comparative airfoil 1; fig. 6 is a comparison of lift-drag ratio characteristics of the airfoil of the present invention and the comparative airfoil 1.
It can be seen from fig. 4 that the maximum turbulence viscosity of the comparative airfoil 1 is greater than 1000, whereas the maximum turbulence viscosity of the inventive airfoil is only around 700, which is significantly reduced. The airfoil of the present invention reduces the turbulence viscosity and thus the drag coefficient is also reduced.
As can be seen in FIG. 5, the airfoil of the present invention may change the velocity profile of the upper surface of the airfoil. The airfoil of the invention has a leading edge and a midsection Cp substantially smaller than the comparative airfoil 1 and a peak less than the comparative airfoil 1. However, the Cp of the airfoil of the invention near the trailing edge is greater than that of the comparative airfoil 1, for reasons of greater camber than that of the comparative airfoil 1. While this characteristic suggests that at smaller angles of attack of the incoming flow, the trailing edge separation of the airfoil of the invention is exacerbated, meaning that the drag coefficient is also increased, as compared to the comparative airfoil 1. But the larger bending range is limited to between 0.82-1.0c with less impact on flow separation at high incoming flow angles of attack due to the separation point moving to the airfoil leading edge.
As can be seen from FIG. 6, the airfoil of the present invention has a broader range of low drag than the comparative airfoil 1, and the maximum lift coefficient is also much higher than that of the S809 airfoil. Although the minimum drag coefficient of the airfoil of the present invention is somewhat higher than that of the comparative airfoil 1, it is more suitable for use in horizontal axis wind turbines, particularly in small tip speed ratios of the type. Because the change of wind speed brings about the change of attack angle, the wing profile of the invention is also suitable for the vertical axis wind turbine working under the unsteady wind conditions such as gusts, turbulence and the like.
After the above representative experimental examples are verified, the wing profile provided by the invention has the advantages that the maximum turbulence viscosity can be reduced under the working condition of 100 ten thousand-magnitude Reynolds numbers, the resistance coefficient is reduced, the low resistance range is wider, the maximum lift coefficient is increased, and the stall attack angle is increased, so that the wind energy absorption efficiency of the wind wheel of the wind turbine generator set is improved.
In the airfoil of the present invention, the contraction scale factor alpha and the rotation angle beta are key indexes of design, and the aerodynamic characteristics influence of the contraction scale factor alpha and the rotation angle beta on the airfoil of the present invention will be reflected. The aerofoil of the invention adopts aerofoil aerodynamic analysis software (solving RANS equation) to carry out aerodynamic performance analysis on the aerofoils with different contraction scale factors alpha and rotation angles beta, and the calculated state parameters are as follows: angle of attack of incoming flow: 9 deg., mach number 0.108, reynolds number 1X 10 6.
2. Comparative 1
The same rotation angle (beta is 10 degrees), different designs of the wing profile of the invention with different shrinkage proportion factors (alpha is 0.2,0.3,0.4,0.5) are compared, and the influence of the shrinkage proportion factors on the design of the wing profile of the invention is analyzed and compared.
FIG. 7 is a geometric profile of an airfoil of the present invention at different contraction scale factors; FIG. 8 is a comparison of drag characteristics of airfoils of the present invention for different contraction scale factors; FIG. 9 is a comparison of lift characteristics of airfoils of the present invention for different contraction scale factors.
Table 1 shows the maximum lift contrast of the inventive airfoil and S809 for different shrinkage ratio shadows, and the lift increment table:
Table 1 maximum lift contrast and lift increment table
| S809 | F-0.2-10 | F-0.3-10 | F-0.4-10 | F-0.5-10 | |
| Clmax | 0.996 | 1.085 | 1.157 | 1.174 | 1.101 |
| Increment of | 0.00％ | 8.94％ | 16.16％ | 17.87％ | 10.54％ |
From FIGS. 7-9 and Table 1, it can be seen that the range of influence of the NACA4412 airfoil increases with increasing contraction scale factor and the slope of the lift coefficient decreases with increasing contraction scale factor. At the same time, as the contraction scale factor α increases, the stall angle of attack is retarded. In addition to the contraction scale factor α of 0.5, the maximum lift Cl max of the airfoil of the present invention increases with increasing coefficient. The drag coefficient is less affected by the contraction scale factor α, but the general surface is that the airfoil of the invention has a smaller drag coefficient at stall than the comparative airfoil 1, while having a larger low drag range.
3. Comparative example 2
The same contraction scale factor (alpha is 0.3), different rotation angles (beta is 8 degrees, 9 degrees, 10 degrees and 11 degrees) are compared with different design schemes of the wing profile of the invention, and the influence of the rotation angles on the design of the wing profile of the invention is analyzed and compared.
FIG. 10 is a geometric profile of an airfoil of the present invention at different contraction scale factors; FIG. 11 is a comparison of drag characteristics of airfoils of the present invention for different contraction scale factors; FIG. 12 is a comparison of lift characteristics of airfoils of the present invention for different contraction scale factors.
As can be seen from fig. 10-12, as the angle of rotation increases, the camber of the airfoil of the present invention near the upper surface of the trailing edge also increases. The angle of attack of lift stall is retarded with increasing rotation angle. Under the condition of high attack angle, the wing section with large rotation angle can obviously reduce the resistance because the separation of the tail edge can be limited.
After the comparison, the influence of the contraction scale factor and the rotation angle of the airfoil of the invention on the aerodynamic characteristics of the airfoil is obtained. It is believed that the greater the contraction scale factor α in the airfoil design of the present invention, the higher the lift stall angle of attack. Whereas as the rotation angle beta increases, the aerodynamic load changes the same as the contraction scale factor alpha.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (3)
1. The high-lift wind turbine airfoil is characterized in that the high-lift wind turbine airfoil takes the curve profile of an S809 airfoil as a prototype, and the structure of the high-lift wind turbine airfoil is described as follows:
Respectively carrying out front projection on the S809 airfoil profile and the NACA4412 airfoil profile in the same X-Y coordinate system to respectively obtain an S809 airfoil profile and an NACA4412 airfoil profile, and overlapping the S809 airfoil profile with the rear edge point O of the NACA4412 airfoil profile;
Shrinking the NACA4412 airfoil profile as a whole by a scaling factor alpha, and rotating the shrunk NACA4412 airfoil profile by an angle beta with the trailing edge point O as a center so that the NACA4412 airfoil profile intersects the upper chord of the S809 airfoil profile at a point A (x, y);
when the ordinate y value in point A is less than the maximum ordinate value of the NACA4412 airfoil profile, replacing the S809 airfoil surface between O-A with the NACA4412 airfoil surface between O-A;
the value range of the proportion factor alpha is 0.2-0.5, and the value range of the rotation angle is 8 degrees, 9 degrees, 10 degrees and 11 degrees.
2. The high lift wind turbine airfoil of claim 1, wherein the outer surface of the high lift wind turbine airfoil is composed of S1-S5 sections connected end to end in sequence, the S1-S3 sections form the upper surface of the airfoil, and the S4-S5 sections form the lower surface of the airfoil; the S1 section and the S5 end are butted at a front edge point, the S3 section and the S4 section are butted at a rear edge point O, and the S3 section is a surface between the NACA4412 aerofoils O-A; wherein,
The S1 section and the S5 section are front edge contraction sections of the wing sections; s2, the upper surface smooth transition section of the wing section; s3 is the trailing edge section of the upper surface of the airfoil; s4, the section is a trailing edge section of the lower surface of the airfoil;
the S3 section is changed according to the scale factor, and the S1 section, the S2 section, the S4 section and the S5 section are changed along with the change of the S3 section on the premise of keeping the curve profile consistent with the curve profile of the S809 wing section.
3. The high lift wind turbine airfoil of claim 2, wherein the camber line of the high lift wind turbine airfoil is S-shaped, and the front section of the camber line is concave and the rear section is convex, and the intersection point of the camber line and the chord line of the airfoil is located at 0.46 unit;
the maximum thickness of the airfoil is 0.199 unit, the chord direction position corresponding to the maximum thickness is 0.349 unit from the front edge point, and the included angle of the rear edge is 13.36 degrees;
The length of the S1 section is more than 0.0 unit and less than 0.39 unit; the length of the S2 section is more than 0.39 unit and less than 0.85 unit; the length of the S3 section is more than 0.85 unit and less than 1.0 unit; the length of the S4 section is more than 0.32 unit and less than 1.0 unit; s5 has a length of greater than 0.0 units and less than 0.32 units;
wherein 1 of said units is equal to the chord length of said airfoil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110287274.3A CN112922774B (en) | 2021-03-17 | 2021-03-17 | High-lift wind power wing type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110287274.3A CN112922774B (en) | 2021-03-17 | 2021-03-17 | High-lift wind power wing type |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112922774A CN112922774A (en) | 2021-06-08 |
| CN112922774B true CN112922774B (en) | 2024-09-10 |
Family
ID=76175802
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110287274.3A Active CN112922774B (en) | 2021-03-17 | 2021-03-17 | High-lift wind power wing type |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112922774B (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN214660605U (en) * | 2021-03-17 | 2021-11-09 | 兰州理工大学 | High-lift wind turbine wing section |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100238774B1 (en) * | 1997-11-21 | 2000-01-15 | 유무성 | Wing of aircraft |
| DE102006017897B4 (en) * | 2006-04-13 | 2008-03-13 | Repower Systems Ag | Rotor blade of a wind turbine |
| RU2309290C1 (en) * | 2006-05-05 | 2007-10-27 | Иван Давыдович Востропятов | Vane-type wind-driven power plant |
| US7677862B2 (en) * | 2006-08-07 | 2010-03-16 | Boatner Bruce E | Vertical axis wind turbine with articulating rotor |
| US8197218B2 (en) * | 2007-11-08 | 2012-06-12 | Alliance For Sustainable Energy, Llc | Quiet airfoils for small and large wind turbines |
| CN101813070B (en) * | 2010-04-13 | 2012-07-25 | 南京航空航天大学 | Vane airfoil profile of low power wind driven generator |
| CN102094769B (en) * | 2011-02-24 | 2012-09-26 | 西北工业大学 | Wind machine blade airfoil profile capable of controlling flow stalling through standing vortex |
| DK178073B1 (en) * | 2011-06-17 | 2015-04-27 | Envision Energy Denmark Aps | A Wind Turbine Blade |
| ES2746119T3 (en) * | 2013-08-23 | 2020-03-04 | Eno Energy Systems Gmbh | Rotor blade profile for a wind turbine |
| JP6167051B2 (en) * | 2014-02-21 | 2017-07-19 | 三菱重工業株式会社 | Wind turbine blade, wind turbine rotor and wind power generator |
| US9708060B2 (en) * | 2014-07-15 | 2017-07-18 | Derek T. Schwartz | Flow diverting lift element |
| US10718311B2 (en) * | 2015-04-29 | 2020-07-21 | Universiti Brunei Darussalam | Low Reynolds number airfoil for a wind turbine blade and method thereof |
| CN106043688A (en) * | 2016-06-08 | 2016-10-26 | 南京航空航天大学 | Helicopter rotor airfoil |
| DE102017107465A1 (en) * | 2017-04-06 | 2018-10-11 | Teg Tubercle Engineering Group Gmbh | Profile body for generating dynamic buoyancy, rotor blade with the profile body and method for profiling the profile body |
| CN109583023A (en) * | 2018-10-29 | 2019-04-05 | 兰州理工大学 | A kind of pneumatic equipment bladess trailing edge modeling method |
| CN112065651B (en) * | 2020-07-21 | 2021-12-14 | 兰州理工大学 | Airfoil for wind turbine blade layer of wind generating set |
-
2021
- 2021-03-17 CN CN202110287274.3A patent/CN112922774B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN214660605U (en) * | 2021-03-17 | 2021-11-09 | 兰州理工大学 | High-lift wind turbine wing section |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112922774A (en) | 2021-06-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112883503B (en) | Numerical simulation method based on influence of PTFE (polytetrafluoroethylene) membrane on aerodynamic characteristics of fan blade | |
| CN109229364B (en) | Class ellipse aerofoil profile applied to high-speed helicopter rotor reversed flow region | |
| CN102094767B (en) | Airfoil group for megawatt-class wind turbine blade | |
| CN102444540B (en) | Wind turbine blade aerofoil of horizontal axis wind turbine | |
| CN214660605U (en) | High-lift wind turbine wing section | |
| CN103306907B (en) | A kind of heavy thickness aerofoil with blunt tail edge blade of large fan | |
| CN104819106A (en) | Wind turbine blade wing section group | |
| CN103133272A (en) | Thin airfoil type blade of large-scale fan | |
| CN203383990U (en) | Large-thickness airfoil blade of large fan | |
| CN112922774B (en) | High-lift wind power wing type | |
| CN112065651B (en) | Airfoil for wind turbine blade layer of wind generating set | |
| CN214499309U (en) | Airfoil profile applicable to wind driven generator blade under low Reynolds number working condition | |
| CN105781904A (en) | 30% thickness aerofoil suitable for megawatt-grade wind turbine blade | |
| CN203515955U (en) | Thickened high-aerodynamic-performance wind turbine blade | |
| CN202348553U (en) | Wind wheel vane wing profile of horizontal axis wind turbine | |
| CN105787217B (en) | A kind of optimum design method of aircraft ripple aerofoil profile | |
| CN203321756U (en) | Medium-thickness airfoil blade for large turbines | |
| CN209855956U (en) | Wind power blade and wind turbine generator system | |
| CN203175769U (en) | Thin wing type blade of large-scale fan | |
| CN103321856B (en) | A kind of heavy thickness airfoil fan of large fan | |
| CN102278272A (en) | Protrusive horizontal shaft wind turbine blade | |
| CN103321857B (en) | Large-thickness blunt-trailing-edge airfoil-shaped blade of large-scale wind turbine | |
| CN212360009U (en) | Bionic blade of horizontal axis wind turbine | |
| CN203383989U (en) | Large-thickness blunt trailing edge airfoil blade of large fan | |
| CN1757883A (en) | Strong curved wing section of sea temperature difference energy-solar energy reboil circulation power generating steam turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |