CN114738179A - Novel high-robustness laminar flow airfoil profile of high-lift-drag-ratio wind turbine - Google Patents

Novel high-robustness laminar flow airfoil profile of high-lift-drag-ratio wind turbine Download PDF

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CN114738179A
CN114738179A CN202210349234.1A CN202210349234A CN114738179A CN 114738179 A CN114738179 A CN 114738179A CN 202210349234 A CN202210349234 A CN 202210349234A CN 114738179 A CN114738179 A CN 114738179A
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徐家宽
杨家盛
吴轩霆
周伯霄
李艺
白俊强
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Northwestern Polytechnical University
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    • 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
    • F03D1/065—Rotors characterised by their construction elements
    • F03D1/0675—Rotors characterised by their construction elements of the blades
    • 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
    • F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor 
    • F03D3/06—Rotors
    • F03D3/062—Rotors characterised by their construction elements
    • 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

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Abstract

The invention provides a novel high-robustness laminar flow airfoil profile of a high-lift-drag-ratio wind turbine, which comprises a front edge, a rear edge, an upper arc line and a lower arc line, wherein the upper arc line and the lower arc line are positioned between the front edge and the rear edge; the ratio of the leading edge radius r to the airfoil chord length c of the airfoil is 0.942 percent, the ratio of the maximum thickness a to the airfoil chord length c of the airfoil is 20.25 percent, the maximum thickness position is positioned at the position where x/c is 30.62 percent, the ratio of the maximum camber b to the airfoil chord length c of the airfoil is 2.15 percent, the maximum camber position is positioned at the position where x/c is 70.8 percent, and the ratio of the trailing edge thickness w to the airfoil chord length c of the airfoil is 0.26 percent; x is the distance from the leading edge to the trailing edge along the airfoil chord direction, and the values of r/c, a/c, b/c, x/c and w/c can have a maximum error of + -3% respectively. The invention aims at the design of the rough airfoil shape state, simultaneously considers the performance of the smooth state, and has higher aerodynamic performance and robustness in the full service cycle of the blade.

Description

Novel high-robustness laminar flow airfoil profile of high-lift-drag-ratio wind turbine
Technical Field
The invention relates to the field of airfoil design in aerodynamic profile design of a wind turbine, in particular to a laminar flow airfoil of a wind turbine with high robustness and high lift-drag ratio, which has excellent aerodynamic characteristics in both smooth and rough surfaces.
Background
Among the clean energy developed and utilized by human beings at present, wind power generation is a mode with less influence on the environment. The wind energy has no pollution, belongs to renewable resources and has huge content. According to the estimation of China Meteorological science research institute, the total wind energy resource reserves are ranked the third world. If the wind energy can be fully and efficiently utilized, huge economic and environmental protection benefits can be generated.
The blade is one of the core components of the wind turbine, and the pneumatic performance of the blade directly influences the power generation efficiency, the load characteristic and the like of the wind turbine. The wing profile is the soul of the wind turbine blade, and the design of the wing profile is the basic and core technology of blade design. Generally, the surface boundary layer of the airfoil is in a laminar flow state under a low-speed working condition, and the adverse pressure gradient resistance of the surface boundary layer of the airfoil is weak, so that the flow separation is easily generated too early, and the performance of the airfoil is seriously influenced. The research on the aerodynamic optimization design of the high-performance wind turbine airfoil has important significance for improving the wind energy capturing capability of the blade, reducing the weight of the blade and corresponding system load.
Compared with an aviation wing profile, the wind turbine wing profile requires larger relative thickness and larger maximum lift force in the full wind speed range; for stall control, a wind turbine requires to limit the maximum lift force, the airfoil profile of the wind turbine requires to change and slow the lift force after stall, and the aerodynamic characteristics are required to be insensitive to roughness. The Swedish aviation research institute (FFA) designs three airfoil profiles of FFA-W3-211, FFA-W3-241 and FFA-W3-301, and the relative thicknesses are respectively 21.1%, 24.1% and 30.1%. The FFA series airfoils have a greater relative thickness and a higher lift coefficient than the NACA series airfoils.
As is known, the airfoil profile is calculated, analyzed and designed under the state of a smooth surface during design, but the surface of the wind turbine is in a rough surface state due to the fact that the actual working environment of the wind turbine is complex, corrosion, weathering, dust particles, insect corpse adhesion, surface water vapor condensation and icing, and the aerodynamic characteristics of the original design are greatly reduced.
Most of domestic patents on the design of the laminar flow airfoil of the wind turbine and considering the influence of roughness only highlight one of high lift-drag ratio and low roughness sensitivity. The consideration of the two conditions mainly focuses on the maximum lift coefficient working condition of the airfoil profile, and the airfoil profile optimized for the aerodynamic characteristic of a small attack angle is not available. And only the influence of the change of the flow in the boundary layer from laminar flow to turbulent flow is considered, and the situation that the surface roughness height is more than 100 μm in the engineering practice is not considered. When the flow in the boundary layer of the airfoil is all turbulent flow, the momentum of the flow is further consumed by continuously increasing the roughness, so that the flow is easier to separate, the lift force of the airfoil is reduced, and the resistance is increased. Therefore, airfoils that do not take into account the effects of large roughness have difficulty ensuring aerodynamic performance and robustness over the life cycle.
Disclosure of Invention
Technical problem to be solved
In order to solve the problem of the existing wind turbine airfoil profile, the invention provides a high-robustness high-lift-drag-ratio wind turbine laminar flow airfoil profile which is suitable for a complex operation environment and takes the rough element influence as a reference airfoil profile to optimize and design, and finally, a novel laminar flow airfoil profile with a smooth surface and a rough surface both having a high lift-drag ratio is obtained.
The technical scheme of the invention is as follows:
the novel high-robustness laminar flow airfoil profile of the high-lift-drag-ratio wind turbine is composed of a leading edge, a trailing edge and an upper arc line and a lower arc line which are positioned between the leading edge and the trailing edge; the ratio of the leading edge radius r to the airfoil chord length c of the airfoil is 0.942 percent, the ratio of the maximum thickness a to the airfoil chord length c of the airfoil is 20.25 percent, the maximum thickness position is positioned at the position where x/c is 30.62 percent, the ratio of the maximum camber b to the airfoil chord length c of the airfoil is 2.15 percent, the maximum camber position is positioned at the position where x/c is 70.8 percent, and the ratio of the trailing edge thickness w to the airfoil chord length c of the airfoil is 0.26 percent; x is the distance from the leading edge to the trailing edge along the airfoil chord direction, and the values of r/c, a/c, b/c, x/c and w/c, respectively, can have a maximum error of + -3%.
Further, the parameterized formula of the camber line of the airfoil is as follows:
y(x)＝a0+a1*cos(x*w)+b1*sin(x*w)+a2*cos(2*x*w)+b2*sin(2*x*w)+a3*cos(3*x*w)+b3*sin(3*x*w)+a4*cos(4*x*w)+b4*sin(4*x*w)+a5*cos(5*x*w)+b5*sin(5*x*w)+a6*cos(6*x*w)+b6*sin(6*x*w)+a7*cos(7*x*w)+b7*sin(7*x*w)+a8*cos(8*x*w)+b8*sin(8*x*w)
wherein the parameter values are:
w＝1.047；a0＝-5.358e+09；a1＝8.223e+09；b1＝4.889e+09；
a2＝-3.24e+09；b2＝-5.961e+09；a3＝-1.459e+08；b3＝3.779e+09；
a4＝8.836e+08；b4＝-1.363e+09；a5＝-4.66e+08；b5＝2.304e+08；
a6＝1.165e+08；b6＝9.048e+06；a7＝-1.348e+07；b7＝-9.508e+06；
a8＝4.49e+05；b8＝1.006e+06
and all parameter values can have a maximum error of ± 3%, respectively.
Further, the parameterized formula of the airfoil camber line is as follows:
y(x)＝A0+A1*cos(x*w)+B1*sin(x*w)+A2*cos(2*x*w)+B2*sin(2*x*w)+A3*cos(3*x*w)+B3*sin(3*x*w)+A4*cos(4*x*w)+B4*sin(4*x*w)+A5*cos(5*x*w)+B5*sin(5*x*w)+A6*cos(6*x*w)+B6*sin(6*x*w)+A7*cos(7*x*w)+B7*sin(7*x*w)+A8*cos(8*x*w)+B8*sin(8*x*w)
wherein the parameter values are:
w＝1.047；A0＝4.03e+09；A1＝-6.181e+09；B1＝-3.683e+09；
A2＝2.428e+09；B2＝4.488e+09；A3＝1.183e+08；B3＝-2.842e+09；
A4＝-6.688e+08；B4＝1.023e+09；A5＝3.515e+08；B5＝-1.715e+08；
A6＝-8.764e+07；B6＝-7.347e+06；A7＝1.009e+07；B7＝7.229e+06；
A8＝-3.316e+05；B8＝-7.6e+05
and all parameter values can have a maximum error of ± 3%, respectively.
Further, the numerical value pairs of the geometric coordinates of the camber line of the airfoil are x/c and yuThe/c is:
Figure BDA0003578709890000031
Figure BDA0003578709890000041
Figure BDA0003578709890000051
wherein y isuThe maximum error of the geometric coordinate value pair is +/-3 percent, and the maximum error is the vertical distance between the coordinate point of the upper arc line and the chord line.
Further, the numerical value pairs of the geometrical coordinates of the airfoil camber line x/c and ylThe/c is:
Figure BDA0003578709890000052
Figure BDA0003578709890000061
Figure BDA0003578709890000071
Figure BDA0003578709890000081
wherein y islThe maximum error of the geometric coordinate value pair is +/-3 percent, and the maximum error is the vertical distance between the coordinate point of the lower arc line and the chord line.
Advantageous effects
The invention takes FFA-W3-211 airfoil as initial airfoil, takes Ma as 0.1, Re as 1.8E6, AoA as 2 degrees and Tu as 0.15 percent as design state, and takesLift-drag ratio K ═ CL/CdMaximum design goal, in CL≥0.99CL0，Cm≤Cm0And optimally designing under the constraint condition that the ratio of the airfoil thickness to the airfoil chord length is between 20 and 24 percent to obtain the laminar flow airfoil (OPT2 airfoil) of the wind turbine with high robustness and high lift-drag ratio.
Compared with the initial airfoil, when the airfoil is smooth and has no roughness interference, the lift value of the optimized airfoil is greatly increased under the smooth (rough height is 0) calculation condition compared with the initial airfoil, and the resistance value is only slightly increased. The lift-drag ratio calculated for the optimized airfoil is 78.48 greater than 75.15 for the original airfoil. The lift coefficient of the airfoil optimized under the rough condition (average rough height of 130 mu m) is improved from 0.5609 to 0.6075, and the lift characteristic is obviously improved. While the drag and moment coefficients do not vary much compared to the initial airfoil shape. The lift-to-drag ratio increased from 39.49 to 43.65. Therefore, it can be considered that the airfoil obtained by optimizing the method under the condition of considering the effect of the leading edge roughness, namely adding the roughness in a given area has improved aerodynamic characteristics under the design condition that the leading edge is provided with the roughness, and the performance is better than that of the original airfoil under the condition that the surface of the airfoil is smooth.
In the using process of the wind turbine blade, the surface of the airfoil is in a rough state caused by pollution for more time, the design aiming at the rough airfoil state simultaneously considers the performance of a smooth state, and the blade has higher aerodynamic performance and robustness in the full service cycle of the blade.
The final optimized airfoil has a slightly reduced thickness compared to the initial airfoil, but satisfies given thickness constraints, and therefore has a less significant profile drag variation. The thickness of the lower surface of the airfoil is reduced, but the camber is increased, and the negative pressure peak of the upper surface is improved and the lift force is increased when the negative pressure peak is reflected on the pressure distribution. The pressure distribution of the lower surface has little change from the initial configuration, and the rear half section of the upper surface is basically consistent with the initial configuration.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: the invention designs an OPT2 airfoil profile and an FFA-W3-211 airfoil profile geometric shape comparison diagram;
FIG. 2 is a schematic diagram: the pressure distribution curve of the OPT2 airfoil designed by the invention at the design point;
FIG. 3: the invention designs the flow field distribution (coarse growth factor and effective intermittent factor) of the OPT2 airfoil and the FFA-W3-211 airfoil at the design point state;
FIG. 4 is a schematic view of: the lift-drag ratio characteristics of the OPT2 airfoil designed by the invention under different attack angles.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
The embodiment provides a high-robustness wind turbine laminar flow airfoil with a high lift-drag ratio, which is suitable for a complex operation environment and considers the influence of a rough element, and has an excellent high lift-drag ratio on both a smooth surface and a rough surface.
A high-precision transition prediction mode considering the influence of a rough element is adopted to predict the transition characteristic and the aerodynamic characteristic of the airfoil under the rough working condition, the laminar flow optimization design of the airfoil of the wind turbine is carried out by taking the airfoil of the Swedish FFA-W3-211 as a reference airfoil, and finally the novel laminar flow airfoil with the smooth surface and the rough surface both having high lift-drag ratio is obtained. The index requirements are as follows:
1. the working state is as follows: ma ═ 0.1, Re ═ 1.8E6, AoA ═ 2 °, Tu ═ 0.15%
2. Designing a target: lift-drag ratio K ═ CL/CdMaximum of
3. Constraint conditions are as follows: cL≥0.99CL0，Cm≤Cm0The ratio of the thickness of the airfoil to the chord length of the airfoil is in the range of 20-24 percent; wherein, CL0And Cm0The values of the lift coefficient and the pitching moment coefficient of the initial wing profile under the corresponding calculation state are obtained.
Based on the international publication of wind turbine airfoil FFA-W3-211 airfoil, smooth surface and rough surface are considered in design condition, a high-robustness high-lift-drag ratio wind turbine laminar flow airfoil OPT2 with excellent aerodynamic characteristics under both smooth surface and rough surface environment is provided, and the geometrical shape of the wind turbine airfoil FFA-W3-211 (identified by origin) is shown in FIG. 1.
The ratio of the leading edge radius r to the airfoil chord length c of the airfoil is 0.942%, the ratio of the maximum thickness a to the airfoil chord length c of the airfoil is 20.25%, the maximum thickness position is positioned at the position where x/c is 30.62%, the ratio of the maximum camber b to the airfoil chord length c of the airfoil is 2.15%, the maximum camber position is positioned at the position where x/c is 70.8%, and the ratio of the trailing edge thickness w to the airfoil chord length c of the airfoil is 0.26%; x is the distance from the leading edge to the trailing edge along the airfoil chord direction, and the values of r/c, a/c, b/c, x/c and w/c, respectively, can have a maximum error of + -3%.
If a parameterized formula is used for description, the parameterized formula of the camber line of the airfoil is as follows:
y(x)＝a0+a1*cos(x*w)+b1*sin(x*w)+a2*cos(2*x*w)+b2*sin(2*x*w)+a3*cos(3*x*w)+b3*sin(3*x*w)+a4*cos(4*x*w)+b4*sin(4*x*w)+a5*cos(5*x*w)+b5*sin(5*x*w)+a6*cos(6*x*w)+b6*sin(6*x*w)+a7*cos(7*x*w)+b7*sin(7*x*w)+a8*cos(8*x*w)+b8*sin(8*x*w)
wherein the parameter values are:
w＝1.047；a0＝-5.358e+09；a1＝8.223e+09；b1＝4.889e+09；
a2＝-3.24e+09；b2＝-5.961e+09；a3＝-1.459e+08；b3＝3.779e+09；
a4＝8.836e+08；b4＝-1.363e+09；a5＝-4.66e+08；b5＝2.304e+08；
a6＝1.165e+08；b6＝9.048e+06；a7＝-1.348e+07；b7＝-9.508e+06；
a8＝4.49e+05；b8＝1.006e+06
and all parameter values can have a maximum error of ± 3% respectively.
The parameterized formula of the airfoil camber line is as follows:
y(x)＝A0+A1*cos(x*w)+B1*sin(x*w)+A2*cos(2*x*w)+B2*sin(2*x*w)+A3*cos(3*x*w)+B3*sin(3*x*w)+A4*cos(4*x*w)+B4*sin(4*x*w)+A5*cos(5*x*w)+B5*sin(5*x*w)+A6*cos(6*x*w)+B6*sin(6*x*w)+A7*cos(7*x*w)+B7*sin(7*x*w)+A8*cos(8*x*w)+B8*sin(8*x*w)
wherein the parameter values are:
w＝1.047；A0＝4.03e+09；A1＝-6.181e+09；B1＝-3.683e+09；
A2＝2.428e+09；B2＝4.488e+09；A3＝1.183e+08；B3＝-2.842e+09；
A4＝-6.688e+08；B4＝1.023e+09；A5＝3.515e+08；B5＝-1.715e+08；
A6＝-8.764e+07；B6＝-7.347e+06；A7＝1.009e+07；B7＝7.229e+06；
A8＝-3.316e+05；B8＝-7.6e+05
and all parameter values can have a maximum error of ± 3%, respectively.
And the geometrical data parameter representation is adopted, the numerical value pairs of the geometrical coordinates of the camber line of the airfoil profile are x/c and yuThe/c is:
Figure BDA0003578709890000111
Figure BDA0003578709890000121
Figure BDA0003578709890000131
wherein y isuThe maximum error of the geometric coordinate value pair is +/-3 percent, and the maximum error is the vertical distance between the coordinate point of the upper arc line and the chord line.
The numerical value pairs of the geometric coordinates of the airfoil camber line x/c and ylThe/c is:
Figure BDA0003578709890000132
Figure BDA0003578709890000141
Figure BDA0003578709890000151
wherein y islThe maximum error of the geometric coordinate value pair is +/-3 percent, and the maximum error is the vertical distance between the coordinate point of the lower arc line and the chord line.
The airfoil designed by the present embodiment has a pressure distribution curve pair of the initial airfoil at the design point as shown in fig. 2. The final optimized airfoil has a slightly reduced thickness compared to the initial airfoil, but satisfies given thickness constraints, and therefore has a less significant profile drag variation. The thickness of the lower surface of the airfoil is reduced, but the camber is increased, and the negative pressure peak of the upper surface is improved and the lift force is increased when the negative pressure peak is reflected on the pressure distribution. The pressure distribution of the lower surface has little change from the initial configuration, and the second half section of the upper surface is basically consistent with the initial configuration.
The aerodynamic characteristics of the design airfoil are compared to the FFA-W3-211 airfoil (identified using origin) at the design point as shown in the following table.
Figure BDA0003578709890000161
Compared with the initial airfoil, the airfoil lift coefficient optimized under the rough condition (taking the average rough height of 130 mu m) is improved from 0.5609 to 0.6075, and the lift characteristic is obviously improved. While the drag and moment coefficients do not vary much compared to the initial airfoil shape. The lift-to-drag ratio increased from 39.49 to 43.65.
A comparison of lift-to-drag characteristics of the design airfoil versus the FFA-W3-211 airfoil (identified using origin) at different angles of attack is shown in FIG. 4. The result shows that the design method of optimizing the leading edge plus the roughness can increase the lift force of the airfoil, reduce the resistance and improve the lift-drag ratio. Thus, even in an actual operating environment, the airfoil can show better aerodynamic performance under the condition that the roughness problem is inevitable.
When the airfoil is smooth and has no roughness interference, the lift value of the optimized airfoil is greatly increased compared with that of the initial airfoil under the smooth (rough height is 0) calculation condition, and the resistance value is only slightly increased. The lift-drag ratio calculated for the optimized airfoil is 78.48 greater than 75.15 for the original airfoil. It is therefore believed that the present invention optimizes the resulting airfoil taking into account the effect of leading edge roughness, i.e., adding roughness to a given area, not only to improve aerodynamic characteristics in the design condition of leading edge with roughness, but also to perform better than the original airfoil under conditions of smooth airfoil surface.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.

Claims (5)

1. A novel high-robustness laminar flow airfoil profile of a high-lift-drag-ratio wind turbine is composed of a leading edge, a trailing edge and an upper arc line and a lower arc line which are positioned between the leading edge and the trailing edge; the method is characterized in that: the ratio of the leading edge radius r to the airfoil chord length c of the airfoil is 0.942%, the ratio of the maximum thickness a to the airfoil chord length c of the airfoil is 20.25%, the maximum thickness position is positioned at the position where x/c is 30.62%, the ratio of the maximum camber b to the airfoil chord length c of the airfoil is 2.15%, the maximum camber position is positioned at the position where x/c is 70.8%, and the ratio of the trailing edge thickness w to the airfoil chord length c of the airfoil is 0.26%; x is the distance from the leading edge to the trailing edge along the airfoil chord direction, and the values of r/c, a/c, b/c, x/c and w/c, respectively, can have a maximum error of + -3%.
2. The novel high-robustness high-lift-drag-ratio wind turbine laminar flow airfoil profile as claimed in claim 1, wherein: the parameterized formula of the camber line of the airfoil is as follows:
y(x)＝a0+a1*cos(x*w)+b1*sin(x*w)+a2*cos(2*x*w)+b2*sin(2*x*w)+a3*cos(3*x*w)+b3*sin(3*x*w)+a4*cos(4*x*w)+b4*sin(4*x*w)+a5*cos(5*x*w)+b5*sin(5*x*w)+a6*cos(6*x*w)+b6*sin(6*x*w)+a7*cos(7*x*w)+b7*sin(7*x*w)+a8*cos(8*x*w)+b8*sin(8*x*w)
wherein the parameter values are:
w＝1.047；a0＝-5.358e+09；a1＝8.223e+09；b1＝4.889e+09；
a2＝-3.24e+09；b2＝-5.961e+09；a3＝-1.459e+08；b3＝3.779e+09；
a4＝8.836e+08；b4＝-1.363e+09；a5＝-4.66e+08；b5＝2.304e+08；
a6＝1.165e+08；b6＝9.048e+06；a7＝-1.348e+07；b7＝-9.508e+06；
a8＝4.49e+05；b8＝1.006e+06
and all parameter values can have a maximum error of ± 3%, respectively.
3. The novel high-robustness wind turbine laminar flow airfoil profile with high lift-drag ratio as claimed in claim 2, wherein: the parameterized formula of the airfoil camber line is as follows:
y(x)＝A0+A1*cos(x*w)+B1*sin(x*w)+A2*cos(2*x*w)+B2*sin(2*x*w)+A3*cos(3*x*w)+B3*sin(3*x*w)+A4*cos(4*x*w)+B4*sin(4*x*w)+A5*cos(5*x*w)+B5*sin(5*x*w)+A6*cos(6*x*w)+B6*sin(6*x*w)+A7*cos(7*x*w)+B7*sin(7*x*w)+A8*cos(8*x*w)+B8*sin(8*x*w)
wherein the parameter values are:
w＝1.047；A0＝4.03e+09；A1＝-6.181e+09；B1＝-3.683e+09；
A2＝2.428e+09；B2＝4.488e+09；A3＝1.183e+08；B3＝-2.842e+09；
A4＝-6.688e+08；B4＝1.023e+09；A5＝3.515e+08；B5＝-1.715e+08；
A6＝-8.764e+07；B6＝-7.347e+06；A7＝1.009e+07；B7＝7.229e+06；
A8＝-3.316e+05；B8＝-7.6e+05
and all parameter values can have a maximum error of ± 3%, respectively.
4. The novel high-robustness high-lift-drag-ratio wind turbine laminar flow airfoil profile as claimed in claim 1, wherein: the numerical value pairs of the geometric coordinates of the camber line of the airfoil are x/c and yuThe/c is:
Figure FDA0003578709880000021
Figure FDA0003578709880000031
Figure FDA0003578709880000041
wherein y isuThe maximum error of the geometric coordinate value pair is +/-3 percent, and the maximum error is the vertical distance between the coordinate point of the upper arc line and the chord line.
5. The novel high-robustness wind turbine laminar flow airfoil profile with high lift-drag ratio as claimed in claim 4, wherein: the numerical value pairs of the geometric coordinates of the airfoil camber line x/c and ylThe/c is:
Figure FDA0003578709880000042
Figure FDA0003578709880000051
Figure FDA0003578709880000061
Figure FDA0003578709880000071
wherein y islThe maximum error of the geometric coordinate value pair is +/-3 percent, and the maximum error is the vertical distance between the coordinate point of the lower arc line and the chord line.
CN202210349234.1A 2022-04-01 2022-04-01 Novel high-robustness laminar flow airfoil profile of high-lift-drag-ratio wind turbine Pending CN114738179A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115593612A (en) * 2022-12-15 2023-01-13 中国空气动力研究与发展中心空天技术研究所（Cn） Self-leveling anti-stall high-performance airfoil

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115593612A (en) * 2022-12-15 2023-01-13 中国空气动力研究与发展中心空天技术研究所（Cn） Self-leveling anti-stall high-performance airfoil

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