Aerofoil with high lift-drag ratio

A high-lift-to-drag ratio, airfoil technology, applied in the direction of instruments, calculations, electrical digital data processing, etc., can solve the problems of geometric and mathematical characteristics that cannot be changed, cannot be optimized, performance constraints, etc., to promote vigorous development, stall late, The effect of increasing the output power

Inactive Publication Date: 2009-06-17
CHONGQING UNIV
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Problems solved by technology

[0004] In addition, once a specific geometric curve mathematical model is determined, its inherent geometric and mathematical properties cannot be changed, so the performance is fundamentally restricted
If the airfoil design is only based on the given airfoil shape, the optimization and improvement of parameters cannot optimize the fundamental factor that characterizes the essential characteristics of the blade airfoil profile—the shape function of the airfoil profile itself, so it is difficult A fundamental breakthrough in the research and innovation of blade airfoil profiles

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Embodiment Construction

[0041] In the design process of the airfoil given in the embodiment, the first 6 items are selected according to the TAYLOR series thought and the convergence principle of the series function, and a certain relative thickness is selected to design the airfoil shape. The airfoil with a maximum relative thickness of 18% is given here. Table 1 gives the coefficients of the functional integration equation of this airfoil. Substituting these coefficients into the integration equation can obtain the shape of the airfoil. The maximum relative thickness is 18%, and the maximum relative thickness is at 27% of the chord length. See figure 1 .

[0042] Table 1 Coefficients of airfoil functional integration equation

[0043] Maximum Relative Thickness X1 x2 x3 x4 x5 x6 18％ 0.1132 0.1328 0.0072 0.0261 0.0001 0.0189

[0044] The aerodynamic performance of the airfoil proposed by the present invention is calculated and analyzed by XFOIL software. Reynolds nu...

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Abstract

The invention relates to an airfoil model for general airfoil profile line shape design based on functional theory, comprising: establishing a functional integrated equation for airfoil profile line, establishing an optimization design model for the integrated equation, according to required target function, selecting different equation term number and coefficients to complete target airfoil designing. Comparing the inventive airfoil model of high lift-drag ratio for general airfoil profile lines based on functional theory with traditional wind turbine airfoil, in normal working power and angle ranges, the airfoil model has high lift coefficient, high lift-drag ratio and later stalling, while the established profile line can express the advantages of general airfoil profile lines and realize the unachievable technical indexes of single profile line, thereby improving the output power and reducing the generation cost of wind turbines.

Description

technical field [0001] The invention relates to the design of an airfoil of a wind turbine blade, in particular to an airfoil with a high lift-to-drag ratio. In addition to adapting to wind turbine blades, it is also applicable to the design and manufacture of aircraft wings. Background technique [0002] The airfoil design theory of wind turbine blades is the fundamental factor that determines the power characteristics and load characteristics of wind turbines, and has always been a hot spot for scholars from all over the world. At present, the research and design of the blade airfoil are based on the specific geometric contour surface to study its aerodynamic characteristics, and carry out the design and optimization of parameters. The special airfoils for wind turbines are developed on the basis of aviation airfoils. The aviation blade airfoils that have been researched include NASA's NACA230 series, NACA44 series, NACA63-2 series, NACALS series and the FX of Bell Corpor...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCY02E60/76Y04S40/22Y02E60/00
Inventor 陈进王旭东
Owner CHONGQING UNIV
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