Blade winglet control method and system for three-dimensional flow field analysis of wind turbine blade

Abstract

The invention provides a blade winglet control method and system for three-dimensional flow field analysis of a wind turbine blade, and relates to the technical field of intelligent control, and the method comprises the steps: solving a hydrodynamic equation through a numerical solution to generate three-dimensional speed, pressure and temperature distribution data of a blade surface; according to the speed, pressure and temperature data, the aerodynamic performance and the flow failure mode of the blade tip are recognized, so that the flow state of the blade area is obtained; the flow state of the blade area is analyzed to obtain geometric parameters of the winglet, and the geometric parameters comprise the length, the width, the installation angle and the shape; according to the geometric parameters of the winglets, the installation positions of the winglets are obtained, and the winglets comprise the pressure surface winglet and the suction surface winglet. According to the invention, the instability of airflow can be reduced, vortex and noise are reduced, noise emission during operation of the wind turbine is effectively reduced, and the environmental adaptability of the wind turbine is improved.

Description

Technical Field

[0001] The present invention relates to the field of intelligent control technology, and in particular to a blade winglet control method and system for three-dimensional flow field analysis of wind turbine blades. Background Art

[0002] There are some technical limitations in the existing wind turbine blade winglet control methods.

[0003] For example, traditional winglet design methods are often based on certain theoretical models or empirical formulas. Although these models or formulas can provide certain guidance for designers, their accuracy may be insufficient when faced with complex three-dimensional flow field characteristics.

[0004] In actual operation, the flow field around wind turbine blades is three-dimensional and dynamically changing, and is affected by many factors, such as wind speed, wind direction, blade shape, and rotation speed. Traditional methods may not be able to fully consider these factors, or even if they are considered, it is difficult to accurately reflect them in the model. Therefore, the designed winglet may not achieve the expected aerodynamic performance in actual operation, resulting in a difference between the design results and the actual operating conditions. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a blade winglet control method and system for three-dimensional flow field analysis of wind turbine blades, which can reduce the instability of airflow, reduce eddy currents and noise, effectively reduce noise emissions during wind turbine operation, and improve its environmental adaptability.

[0006] In order to solve the above technical problems, the technical solution of the present invention is as follows:

[0007] In a first aspect, a blade winglet control method for three-dimensional flow field analysis of a wind turbine blade comprises:

[0008] The fluid dynamics equations are solved numerically to generate three-dimensional velocity, pressure, and temperature distribution data on the blade surface;

[0009] Identify the aerodynamic performance and flow failure modes at the blade tip based on velocity, pressure and temperature data to obtain the flow state in the blade area;

[0010] Analyze the flow state in the blade area to obtain the geometric parameters of the winglet, including length, width, installation angle and shape;

[0011] According to the geometric parameters of the winglet, the installation position of the winglet is obtained. The winglet includes a pressure surface winglet and a suction surface winglet;

[0012] Obtain experimental data of cantilever plane cascades under high subsonic conditions, and analyze the effect of winglets on the aerodynamic performance of blades under different incoming flow Mach numbers and angles of attack to obtain analytical results and experimental data;

[0013] According to the analysis results and experimental data, the parameters are scanned, the flow field data is calculated, and the geometric parameters of the winglet are adjusted through multiple simulations to optimize the winglet design to obtain the optimized geometric parameters;

[0014] According to the optimized geometric parameters, the width and installation position of the winglet are adjusted to achieve the control of the winglet.

[0015] Furthermore, the fluid dynamics equations are solved numerically to generate three-dimensional velocity, pressure and temperature distribution data on the blade surface, including:

[0016] Create a three-dimensional geometric model of the wind turbine blade, mesh the three-dimensional geometric model, and form a computational mesh;

[0017] Based on the computational grid, define the boundary conditions of the blade surface, inflow and outflow areas, including the incoming flow velocity, pressure and temperature;

[0018] According to the fluid dynamics equations and boundary conditions, iterative calculations are performed to generate velocity, pressure and temperature distribution data on the blade surface. The fluid dynamics equations include the continuity equation, the Navier-Stokes equations and the heat transfer equation.

[0019] Furthermore, the aerodynamic performance and flow failure mode of the blade tip are identified based on the velocity, pressure and temperature data to obtain the flow state of the blade area, including:

[0020] According to the processing of velocity, pressure and temperature distribution data on the blade surface, three-dimensional images of velocity field, pressure field and temperature field are drawn to obtain the flow pattern and thermal distribution at the blade tip;

[0021] According to the flow pattern and heat distribution at the blade tip, Calculate the aerodynamic performance index of the blade tip to obtain the aerodynamic efficiency η of the blade tip l , where p s is the static pressure of gas on the blade tip surface, p a is the static pressure of the fluid in the flow area due to external environmental conditions, n is the surface normal vector for calculating the direction components of lift and drag; cos(θ) is the angle between the fluid flow direction and the surface normal vector, T s is the temperature of the blade tip surface, T a is the static temperature of the fluid in the flow area due to external environmental conditions, is the temperature correction factor, ρ is the density of the fluid, V lis the local velocity at the blade tip, ΔV 2 It refers to the square of the velocity change caused by the fluctuation of flow velocity or turbulence, C D is the dimensionless coefficient describing the resistance of the fluid at the blade tip, μ is the dynamic viscosity of the fluid, is the viscosity correction factor, It's resistance.

[0022] Based on the aerodynamic efficiency at the blade tip, flow failure modes are identified and temperature effects are evaluated to obtain the flow state in the blade area.

[0023] Furthermore, the flow state in the blade area is analyzed to obtain the geometric parameters of the winglet, including length, width, installation angle and shape, including:

[0024] According to the flow state in the blade area, the velocity and pressure changes on the winglet surface are analyzed to identify the velocity distribution, pressure distribution and flow separation;

[0025] Based on the velocity distribution, pressure distribution and flow separation, the wing length, width, mounting angle, and the curvature and twist of the wing shape are extracted from the CFD model.

[0026] Further, according to the geometric parameters of the winglet, the installation position of the winglet is obtained, and the winglet includes a pressure surface winglet and a suction surface winglet, including:

[0027] Obtaining geometric parameters of the winglets, including the length, width, installation angle and shape of the pressure side winglets and the suction side winglets;

[0028] Obtain the aerodynamic characteristics of the main wing, such as pressure distribution, flow state and lift distribution;

[0029] The installation position and angle of the winglet are obtained according to the geometric parameters of the winglet and the aerodynamic characteristics of the main wing.

[0030] Furthermore, the experimental data of cantilever plane cascade under high subsonic conditions are obtained, and the influence of winglets on the aerodynamic performance of blades under different incoming flow Mach numbers and angles of attack are analyzed to obtain analytical results and experimental data, including:

[0031] The cascade model is fixed on the cantilever frame in the wind tunnel test section, the position of the cascade model is adjusted to set the flow velocity of the wind tunnel, the flow velocity is controlled under the simulated high subsonic condition, and the angle of attack of the cascade is adjusted to obtain the experimental data of lift coefficient, drag coefficient, flow velocity, temperature and pressure parameters;

[0032] According to experimental data, the Mach number and angle of attack are adjusted;

[0033] According to the Mach number and angle of attack, Calculate the lift L1 of the winglet on the aerodynamic performance of the blade under different Mach numbers and angles of attack. Calculate the drag D1 of the winglet on the aerodynamic performance of the blade under different Mach numbers and angles of attack, where ρ1 is the mass density of the air, V2 is the air velocity, S is the projected area of ​​the blade, and C l，0 is the base lift coefficient when there is no lift, K l is the adjustment coefficient, Re is the Reynolds number, which represents the ratio of the inertial force to the viscous force of the flow; M is the ratio of the air flow velocity to the speed of sound, S ref is the projected area of ​​the blade, α is the angle of attack of the blade, a l 、b l and c l is the lift correction factor, C d，0 is the base drag coefficient in the absence of lift, K d is the coefficient for adjusting the drag coefficient, a d 、b d and c d is the drag correction factor.

[0034] Furthermore, based on the analysis results and experimental data, the parameters are scanned, the flow field data is calculated, and the geometric parameters of the winglet are adjusted through multiple simulations to optimize the winglet design to obtain the optimized geometric parameters, including:

[0035] According to the analysis results and experimental data, the flow field data of the winglet is obtained, including the lift coefficient, drag coefficient, and pressure distribution;

[0036] According to the experimental data, numerical simulation is carried out through CFD software to establish the mathematical model of the flow field of the winglet;

[0037] Perform a preliminary scan of the geometric parameters to obtain the flow field data and performance indicators under the geometric parameters;

[0038] According to the data of geometric parameters, the initial population is generated. Each individual represents a set of geometric parameters. The fitness of each individual is evaluated by the objective function. A new generation of population is generated through selection, crossover and mutation operations. The iterative process is used to optimize the objective function. When the maximum number of iterations is reached, the optimization process is terminated to obtain the best parameters.

[0039] The optimal parameters are applied to CFD simulation to obtain optimized geometric parameters.

[0040] In a second aspect, a blade winglet control system for three-dimensional flow field analysis of a wind turbine blade comprises:

[0041] An identification module is used to solve the fluid dynamics equations by numerical solution to generate three-dimensional velocity, pressure and temperature distribution data of the blade surface; based on the velocity, pressure and temperature data, the aerodynamic performance and flow failure mode of the blade tip are identified to obtain the flow state of the blade area;

[0042] The acquisition and analysis module is used to identify the aerodynamic performance and flow failure mode of the blade tip according to the speed, pressure and temperature data to obtain the flow state of the blade area; analyze the flow state of the blade area to obtain the geometric parameters of the winglet, including the length, width, installation angle and shape; obtain the installation position of the winglet according to the geometric parameters of the winglet, and the winglet includes a pressure surface winglet and a suction surface winglet; obtain the experimental data of the cantilever plane cascade under high subsonic conditions, and analyze the influence of the winglet on the aerodynamic performance of the blade under different incoming flow Mach numbers and angles of attack to obtain analysis results and experimental data;

[0043] The optimization and adjustment module is used to scan the parameters and calculate the flow field data according to the analysis results and experimental data, and adjust the geometric parameters of the winglet through multiple simulations. The winglet design is optimized through genetic algorithms and gradient descent methods to obtain optimized geometric parameters; according to the optimized geometric parameters, the width and installation position of the winglet are adjusted to achieve the control of the winglet.

[0044] According to a third aspect, a computing device includes:

[0045] one or more processors;

[0046] The storage device is used to store one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the method described.

[0047] In a fourth aspect, a computer-readable storage medium stores a program, and when the program is executed by a processor, the method described is implemented.

[0048] The above solution of the present invention includes at least the following beneficial effects:

[0049] By accurately calculating and optimizing the geometric parameters of the winglets, the airflow can be better controlled, flow failure and vortex can be reduced, and the aerodynamic performance of the blades can be improved. By combining numerical solutions and experimental data, the design parameters of the winglets can be adjusted more accurately through multiple simulations and optimization algorithms. By iteratively calculating the fluid dynamics equations to generate detailed velocity, pressure and temperature distribution data, the flow failure mode can be effectively identified and controlled, the stability of the blades under various working conditions can be improved, flow failure phenomena can be reduced, and the aerodynamic characteristics and operational reliability of the blades can be improved. By analyzing the performance of the winglets under different incoming flow Mach numbers and angles of attack, the design can maintain optimal performance under a variety of working conditions, improve the adaptability of the wind turbine under different environmental conditions, enable it to operate efficiently under a wider range of meteorological conditions, and enhance the versatility and flexibility of the wind turbine.

[0050] Optimizing the design of winglets can reduce the instability of airflow, reduce the generated vortices and noise, reduce the noise emission during the operation of wind turbines, and improve the environmental adaptability of wind turbines; optimized winglet design can reduce failures and maintenance requirements caused by poor aerodynamic efficiency or flow failure, reduce maintenance frequency and repair costs, and improve the economic benefits and long-term operation stability of wind turbines; using advanced CFD technology and optimization algorithms to promote innovation and progress in design and improve the level.

[0051] By adjusting the geometric parameters of the winglet through the optimization algorithm, precise airflow control can be achieved, the control accuracy of the wind turbine can be improved, and the overall performance of the wind turbine can be optimized, making it more stable and efficient under complex operating conditions; through effective parameter scanning and optimization algorithms, the best winglet design solution can be quickly obtained, shortening the design cycle and improving the efficiency of the design process; combining numerical simulation and experimental data to verify the accuracy and effect of the design, improve the reliability and practicality of the design, reduce the gap between the design and actual application, and ensure that the performance of the final product reaches the expected goal. BRIEF DESCRIPTION OF THE DRAWINGS

[0052] Figure 1 It is a flow chart of a blade winglet control method for three-dimensional flow field analysis of a wind turbine blade provided by an embodiment of the present invention.

[0053] Figure 2 It is a schematic diagram of a blade winglet control system for three-dimensional flow field analysis of a wind turbine blade provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0054] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in a form and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0055] like Figure 1 As shown, an embodiment of the present invention provides a blade winglet control method for three-dimensional flow field analysis of a wind turbine blade, the method comprising the following steps:

[0056] Step 11, solving the fluid dynamics equations by numerical solution to generate three-dimensional velocity, pressure and temperature distribution data on the blade surface;

[0057] Step 12, identifying the aerodynamic performance and flow failure mode of the blade tip according to the velocity, pressure and temperature data to obtain the flow state of the blade area;

[0058] Step 13, analyzing the flow state of the blade area to obtain the geometric parameters of the winglet, including length, width, installation angle and shape;

[0059] Step 14, obtaining the installation position of the winglet according to the geometric parameters of the winglet, the winglet including the pressure surface winglet and the suction surface winglet;

[0060] Step 15, obtaining the experimental data of the cantilever plane cascade under high subsonic conditions, analyzing the influence of the winglet on the aerodynamic performance of the blade under different incoming flow Mach numbers and angles of attack, so as to obtain analysis results and experimental data;

[0061] Step 16, based on the analysis results and experimental data, the parameters are scanned, the flow field data is calculated, and the geometric parameters of the winglet are adjusted through multiple simulations, and the winglet design is optimized through genetic algorithms and gradient descent methods to obtain optimized geometric parameters;

[0062] Step 17, adjusting the width and installation position of the winglet according to the optimized geometric parameters to achieve control of the winglet.

[0063] In the embodiments of the present invention, by accurately optimizing the geometric parameters and installation position of the winglet, the airflow can be more effectively controlled, flow failure and vortex can be reduced, and the aerodynamic performance of the wind turbine blade can be improved; optimizing the winglet design can improve the aerodynamic performance of the blade, reduce aerodynamic stall and flow separation, and ensure the stability of the blade under various operating conditions; the optimized winglet can reduce vortex and noise caused by airflow instability and improve the smoothness of aerodynamic flow; through experimental data and multiple simulations under high subsonic conditions, the performance of the winglet under different incoming flow Mach numbers and angles of attack can be optimized; the optimized winglet can reduce failures and maintenance requirements caused by aerodynamic failure and inefficiency; the use of genetic algorithm optimization technology can flexibly adjust the geometric parameters of the winglet to achieve multi-objective optimization; the design effect can be verified by combining numerical simulation and experimental data to ensure the accuracy of the design and practical application performance; through data analysis and algorithm application in the optimization process, the number of trial and error can be reduced, and the design iteration can be accelerated; the use of advanced numerical solutions, optimization algorithms and experimental verification technologies can promote the development of wind turbine design technology.

[0064] In a preferred embodiment of the present invention, the above step 11 may include:

[0065] Create a three-dimensional geometric model of the wind turbine blade, mesh the three-dimensional geometric model, and form a computational mesh;

[0066] Based on the computational grid, define the boundary conditions of the blade surface, inflow and outflow areas, including the incoming flow velocity, pressure and temperature;

[0067] According to the fluid dynamics equations and boundary conditions, iterative calculations are performed to generate velocity, pressure and temperature distribution data on the blade surface. The fluid dynamics equations include the continuity equation, the Navier-Stokes equations and the heat transfer equation.

[0068] In an embodiment of the present invention, accurate flow field data can be used to optimize the design of wind turbine blades, reduce aerodynamic drag, increase lift, and thereby improve the overall performance and efficiency of the wind turbine. Accurate fluid analysis helps identify and reduce possible energy loss areas. Analysis of fluid dynamics data can identify potential flow failure modes and structural weaknesses in advance, so that preventive measures can be taken to improve the reliability of the wind turbine. Optimized design can reduce material usage while maintaining performance, reduce manufacturing and maintenance costs, and reduce the need for actual wind tunnel testing through computer simulation. CFD simulation allows rapid design iterations and adjustments, and can simulate different operating conditions and environmental conditions, thereby optimizing the performance of blades under various actual operating conditions. Accurate speed, pressure, and temperature data can be used to understand the aerodynamic characteristics of wind turbine blades and enhance understanding of complex flow phenomena.

[0069] In a specific embodiment of the present invention, the design objectives of the blades are determined, such as rated power, rated wind speed, and rotor diameter; the basic parameters of the blades, including the number of blades, length, and airfoil selection, are determined, and professional CAD software, such as AutoCAD, SolidWorks, and Catia, are used to draw the blade contour, and different airfoils are selected along the span direction of the blade to meet the aerodynamic performance requirements. In the CAD software, the airfoil contours of each section are drawn according to the selected airfoil data. The lofting function of the CAD software is used to connect the airfoils of each section to form a continuous three-dimensional blade shape, and the key parts such as the root and tip of the blade are designed in detail. A meshing tool integrated with the CAD software is used, such as the Meshing module of ANSYS Workbench and ICEM CFD; a structured grid or an unstructured grid is selected according to the blade analysis requirements, and a higher grid density is set in key areas such as the leading edge, trailing edge, and tip of the blade to capture more complex flow phenomena. According to the set parameters, run the meshing software to generate the computational mesh, check the quality of the generated mesh, including the orthogonality and aspect ratio of the mesh, ensure that the mesh quality meets the computational requirements, and export the generated mesh file to a format supported by the fluid dynamics analysis software.

[0070] In another specific embodiment of the present invention, it is necessary to accurately identify and mark different boundary areas in the computational grid, including: the blade surface at the boundary where the fluid interacts with the solid, which needs special attention and is located in front of the wind turbine, where the airflow enters the computational domain; the outflow area located behind the wind turbine, where the airflow leaves the computational domain; and the boundary including the ground, sky, and side. The temperature, velocity, and pressure are defined according to the blade surface, specifically expressed as the velocity of the fluid on the blade surface is zero, because there is friction between the fluid and the solid surface, which makes the velocity of the fluid on the solid surface drop to zero; the pressure distribution on the blade surface is one of the key outputs of the simulation, so it is usually set as a free boundary condition, allowing the pressure to change freely during the calculation process, and setting a fixed temperature value for the inflow area. The temperature, velocity, and pressure are defined according to the inflow area, and the velocity of the outflow area is set as a free outflow condition, allowing the fluid to flow freely out of the computational domain without imposing any restrictions; the static pressure of the outflow area is usually set to the ambient pressure or adjusted according to the simulation requirements; the temperature setting of the outflow area can be similar to the inflow area or adjusted according to the simulation requirements. Define symmetric boundaries based on other boundaries, and use symmetric boundary conditions to reduce the amount of calculation. On the symmetric boundary, the velocity component perpendicular to the boundary is zero, and the gradient of other physical quantities is zero. Use fluid dynamics analysis software such as ANSYS Fluent and CFD++ to import the generated grid into the fluid dynamics software, set the time step and number of iterations calculation parameters, and perform iterative calculations. During the calculation process, the software will continuously update the velocity, pressure, and temperature distribution data on the blade surface until the convergence condition or the specified number of iterations is reached.

[0071] In a preferred embodiment of the present invention, the above step 12 may include:

[0072] According to the processing of velocity, pressure and temperature distribution data on the blade surface, three-dimensional images of velocity field, pressure field and temperature field are drawn to obtain the flow pattern and thermal distribution at the blade tip;

[0073] According to the flow pattern and heat distribution at the blade tip, Calculate the aerodynamic performance index of the blade tip to obtain the aerodynamic efficiency η of the blade tip l , where p s is the static pressure of gas on the blade tip surface, p a is the static pressure of the fluid in the flow area due to external environmental conditions, n is the surface normal vector for calculating the direction components of lift and drag; cos(θ) is the angle between the fluid flow direction and the surface normal vector, T s is the temperature of the blade tip surface, T a is the static temperature of the fluid in the flow area due to external environmental conditions, is the temperature correction factor, ρ is the density of the fluid, Vl is the local velocity at the blade tip, ΔV 2 It refers to the square of the velocity change caused by the fluctuation of flow velocity or turbulence, C D is the dimensionless coefficient describing the resistance of the fluid at the blade tip, μ is the dynamic viscosity of the fluid, is the viscosity correction factor, It is resistance;

[0074] Based on the aerodynamic efficiency at the blade tip, flow failure modes are identified and temperature effects are evaluated to obtain the flow state in the blade area.

[0075] In an embodiment of the present invention, the drawn velocity field, pressure field and temperature field images help to accurately identify the flow pattern at the tip of the blade, thereby optimizing the blade design and improving the aerodynamic efficiency. By analyzing the flow pattern and heat distribution, flow failures such as flow separation can be effectively reduced, resistance can be reduced, and overall aerodynamic performance can be improved; identifying flow failure modes helps to discover potential problems in the design stage; accurately assessing the impact of temperature on blade performance, ensuring that the blades maintain good performance and structural integrity under different operating conditions; by calculating the aerodynamic efficiency of the blade tip, the optimal design parameters can be found, the power generation efficiency of the wind turbine can be improved, energy can be saved, energy losses caused by flow failure or temperature effects can be identified and reduced, and the efficiency of the overall system can be improved.

[0076] In a specific embodiment of the present invention, by obtaining the velocity, pressure and temperature distribution data on the blade surface, a post-processing software such as ANSYS CFD-Post, Tecplot and ParaView is selected; the velocity, pressure and temperature distribution data on the blade surface are imported into the selected post-processing software, the velocity, pressure and temperature data are smoothed to reduce numerical noise and fluctuations to make the image clearer, and the areas of no concern are cropped to focus more on the flow pattern and thermal distribution at the tip of the blade, and interpolation processing is performed to improve the resolution and clarity of the image to obtain the processed data; according to the needs, an appropriate drawing type is selected, such as an isosurface map, a cloud map and a vector map; appropriate color mapping is set for the velocity, pressure and temperature, the viewing angle and lighting effect of the image are adjusted, and necessary annotations and descriptions are added to the image, such as a title, a coordinate axis and a legend; and the flow pattern and thermal distribution at the tip of the blade are analyzed according to the drawn three-dimensional image.

[0077] In another specific embodiment of the present invention, based on the drawn three-dimensional image, the density and dynamic viscosity of the fluid are calculated according to the temperature and pressure, and the dimensionless coefficient describing the resistance generated by the fluid at the tip of the blade is used. In combination with parameters such as the density, local flow velocity, and dynamic viscosity of the fluid, the resistance coefficient is calculated. The viscosity correction factor is calculated based on the dynamic viscosity of the fluid and the local flow velocity at the tip of the blade. The resistance on the tip of the blade is calculated by combining all parameters and correction factors.

[0078] Calculate the aerodynamic efficiency of the blade tip. The aerodynamic efficiency reflects the efficiency of the blade tip in converting wind energy into mechanical energy or electrical energy. Analyze the calculated aerodynamic efficiency and other related parameters to evaluate the performance of the blade tip. According to the flow characteristics of the wind turbine blade, define possible flow failure modes, such as boundary layer separation, vortex shedding, and stall. Correlate the aerodynamic efficiency data with the defined flow failure modes to assist in identifying flow failure modes. Analyze the change trend of aerodynamic efficiency under different temperature conditions, evaluate the effect of temperature on the aerodynamic performance of the blade tip, study how temperature affects flow parameters and thus affects aerodynamic efficiency, and comprehensively evaluate the effect of temperature effect on the flow state and performance of the blade tip in combination with the changes in aerodynamic efficiency and flow parameters. According to the analysis results of aerodynamic efficiency, flow parameters, and temperature effects, classify the flow state of the blade tip, such as normal flow, mild failure, and severe failure. Draw a flow state diagram of the blade tip to show the distribution and change trend of the flow state under different conditions.

[0079] In a preferred embodiment of the present invention, the above step 13 may include:

[0080] According to the flow state in the blade area, the velocity and pressure changes on the winglet surface are analyzed to identify the velocity distribution, pressure distribution and flow separation;

[0081] Based on the velocity distribution, pressure distribution and flow separation, the wing length, width, mounting angle, and the curvature and twist of the wing shape are extracted from the CFD model.

[0082] In an embodiment of the present invention, by analyzing the flow velocity distribution, the high flow velocity and low flow velocity areas on the winglet surface are identified, and the optimization of the airfoil design can reduce the uneven flow velocity and improve the aerodynamic performance; improving the flow velocity distribution helps to reduce the flow resistance and improve the aerodynamic efficiency of the winglet; optimizing the pressure distribution can enhance the lift of the airfoil under different flight conditions, ensure uniform lift distribution, reduce local pressure loss, reduce the negative pressure area and pressure gradient imbalance, help reduce the risk of flow separation, and improve flight stability. By analyzing the flow separation area, the airfoil design can be identified and optimized to reduce flow separation and improve the overall aerodynamic performance of the airfoil; improving the flow state on the winglet surface helps to optimize the boundary layer control and reduce the failure problem caused by separation; extracting the wing length, width, installation angle, curvature and twist from the CFD model helps to accurately describe the airfoil design characteristics. By comparing the CFD simulation results with the actual performance data, the accuracy of the airfoil design is verified, and the design parameters are adjusted in time to meet the performance requirements. The data-driven design optimization reduces the number of physical experiments and iterations, thereby shortening the design cycle and reducing costs. By optimizing the flow velocity and pressure distribution, the lift coefficient of the winglet is increased, the drag is reduced, and the overall aerodynamic efficiency of the aircraft is improved. By optimizing the flow state and reducing flow separation, the controllability and stability of the aircraft are improved, and the flight performance is improved.

[0083] In a specific embodiment of the present invention, a three-dimensional model of the winglet is established using CFD software, and simulation is performed to obtain velocity, pressure and temperature distribution data, the required velocity, pressure and temperature data are derived from the CFD simulation, the data on the winglet surface are screened out, and smoothing, interpolation and format conversion are performed. The velocity field map of the winglet surface is drawn by a visualization tool, and color mapping and vector diagrams are selected to display the change of velocity distribution. By observing the velocity field, high and low velocity areas are identified, and the uneven distribution of velocity is detected; and a pressure field image of the winglet surface is drawn, and the pressure distribution is displayed by isosurfaces or color maps, and the pressure distribution is analyzed, especially the pressure gradient and local high and low pressure areas, to identify possible pressure abnormal areas; through the velocity and pressure field images, the flow separation area is identified, and the flow separation is usually manifested as a sudden decrease in velocity or a sharp change in pressure; the streamline map is superimposed on the velocity field image to visualize the separation and reflow areas of the flow.

[0084] In another specific embodiment of the present invention, the wing length, referring to the chord length of the wing, is extracted through the geometric data in the CFD model, and the width of the winglet in the flow direction is calculated; the installation angle of the airfoil relative to the incoming flow direction is derived from the model geometry or flow field data; the twisting angle of the airfoil from the root to the tip is measured by curve fitting and measuring the actual bending of the airfoil, the chord directions at different positions of the airfoil are compared, the angle data at different positions of the airfoil are extracted from the CFD model, and the curvature is extracted from the airfoil profile data.

[0085] In a preferred embodiment of the present invention, the above step 14 may include:

[0086] Obtaining geometric parameters of the winglets, including the length, width, installation angle and shape of the pressure side winglets and the suction side winglets;

[0087] Obtain the aerodynamic characteristics of the main wing, such as pressure distribution, flow state and lift distribution;

[0088] The installation position and angle of the winglet are obtained according to the geometric parameters of the winglet and the aerodynamic characteristics of the main wing.

[0089] In an embodiment of the present invention, the optimal installation position and angle of the winglet are determined according to the aerodynamic characteristics of the main wing, which can significantly improve the lift effect of the winglet and reduce the resistance of the main wing. Reasonable design of the position and angle of the winglet can optimize the airflow management of the main wing and reduce turbulence and flow separation. By optimizing the geometric parameters and installation position of the winglet, the aerodynamic balance of the aircraft can be improved, the lateral and longitudinal aerodynamic instability can be reduced, and the stability and maneuverability of the aircraft can be enhanced. By conducting a detailed analysis of the geometric parameters and aerodynamic characteristics of the winglet and the main wing, the flight performance can be more accurately predicted in the design stage, thereby reducing the number of subsequent physical tests and iterations. The use of CFD simulation and aerodynamic characteristics analysis can quickly evaluate the effects of different design schemes, accelerate the design optimization process, and improve work efficiency.

[0090] In a specific embodiment of the present invention, the length, width, installation angle and shape of the winglet are extracted from the computer-aided design model, and the geometric data of the winglet, including its shape and size, are derived from the CFD software; the pressure distribution data of the main wing surface is extracted in the CFD simulation, usually displayed in the form of pressure coefficient, the flow state on the main wing surface is analyzed, including whether there is flow separation and boundary layer characteristics, the lift distribution data of the main wing is obtained through CFD simulation, and relevant data are extracted from the CFD results, usually including pressure field, streamline diagram, lift distribution diagram, and the existing aerodynamic database and experimental data are used to supplement the CFD simulation results. The high area and low area of ​​the lift distribution of the main wing are determined to select the best installation position of the winglet, and the installation position of the winglet with the most suitable pressure on the main wing is found to minimize interference and flow separation. According to the pressure distribution and lift requirements of the main wing, the installation position of the winglet is selected, for example, the wing root, the middle of the wing or the wing tip, and according to the flow state and lift distribution of the main wing, the installation angle of the winglet is adjusted to optimize lift and reduce drag, and the best position and installation angle of the winglet are determined.

[0091] In a preferred embodiment of the present invention, the above step 15 may include:

[0092] The cascade model is fixed on the cantilever frame in the wind tunnel test section, the position of the cascade model is adjusted to set the flow velocity of the wind tunnel, the flow velocity is controlled under the simulated high subsonic condition, and the angle of attack of the cascade is adjusted to obtain the experimental data of lift coefficient, drag coefficient, flow velocity, temperature and pressure parameters;

[0093] According to experimental data, the Mach number and angle of attack are adjusted;

[0094] According to the Mach number and angle of attack, Calculate the lift L1 of the winglet on the aerodynamic performance of the blade under different Mach numbers and angles of attack. Calculate the drag D1 of the winglet on the aerodynamic performance of the blade under different Mach numbers and angles of attack, where ρ1 is the mass density of the air, V2 is the air velocity, S is the projected area of ​​the blade, and C l，0 is the base lift coefficient when there is no lift, K l is the adjustment coefficient, Re is the Reynolds number, which represents the ratio of the inertial force to the viscous force of the flow; M is the ratio of the air flow velocity to the speed of sound, S ref is the projected area of ​​the blade, α is the angle of attack of the blade, a l 、b l and c l is the lift correction factor, C d，0 is the base drag coefficient in the absence of lift, K d is the coefficient for adjusting the drag coefficient, a d 、b d and c d is the drag correction factor.

[0095] In an embodiment of the present invention, experimental data is used to accurately understand the aerodynamic performance of the blade at different Mach numbers and angles of attack. By simulating the flow rate under high subsonic conditions, the performance of the blade under extreme conditions can be tested to ensure that it can withstand the impact of high-speed airflow in actual applications, reduce the risk of failure, and improve the safety of the equipment.

[0096] In a specific embodiment of the present invention, the blade model is mounted on a cantilever frame of the wind tunnel test section to ensure that it is in the correct position and angle in the wind tunnel, and accurate measurement tools are used to ensure the accurate position of the model to avoid test errors. The flow rate of the wind tunnel is set to simulate high subsonic conditions, the wind tunnel fan or airflow generator is adjusted to ensure that the airflow speed matches the experimental requirements, and a flow rate sensor is installed to monitor the airflow speed in the wind tunnel in real time. The angle of attack of the blade model is adjusted to cover different angles of attack within the experimental range, and the angle of attack value of each test is accurately recorded. The lift of the blade model is measured using a force sensor or a weighing device.

[0097] Lift coefficient = lift / (0.5×air density×air velocity 2× blade projection area), calculate the lift coefficient. According to the measured resistance of the cascade model, Get the drag coefficient, where F d The drag of the model in the wind tunnel is directly measured using a force sensor. ρ1 is the air density, V3 is the flow velocity, and A is the windward area of ​​the blade model. Appropriate sensors are installed to measure the flow velocity, airflow temperature and pressure in the wind tunnel. The lift coefficient, drag coefficient, flow velocity, temperature and pressure are recorded under different attack angles and wind tunnel flow rates.

[0098] In another specific embodiment of the present invention, using experimental data through Calculate the Reynolds number under different conditions, ρ1 is the mass density of the air, V3 is the air velocity, L1 is the characteristic length of the blade, μ1 is the dynamic viscosity of the air, and pass Calculate the Mach number, where V3 is the air velocity and a1 is the speed of sound. According to the geometric parameters and angle of attack of the winglet, the lift at different Mach numbers and angles of attack is calculated by formula. Arrange the data of angle of attack, Reynolds number and lift coefficient, and calculate the lift coefficient according to the data. Mathematical model is used to fit the lift coefficient to find the optimal correction factor a l 、b l and c l , where the resistance correction factor a d 、b d and c d Calculation method and correction factor a l 、b l and c l The same, so no further description.

[0099] In a preferred embodiment of the present invention, the above step 16 may include:

[0100] According to the analysis results and experimental data, the flow field data of the winglet is obtained, including the lift coefficient, drag coefficient, and pressure distribution.

[0101] According to the experimental data, numerical simulation is carried out through CFD software to establish the mathematical model of the flow field of the winglet;

[0102] Perform a preliminary scan of the geometric parameters to obtain the flow field data and performance indicators under the geometric parameters;

[0103] According to the data of geometric parameters, the initial population is generated. Each individual represents a set of geometric parameters. The fitness of each individual is evaluated by the objective function. A new generation of population is generated through selection, crossover and mutation operations. The iterative process is used to optimize the objective function. When the maximum number of iterations is reached, the optimization process is terminated to obtain the best parameters.

[0104] The optimal parameters are applied to CFD simulation to obtain optimized geometric parameters.

[0105] In the embodiments of the present invention, by optimizing the geometric parameters, the performance indicators such as the lift-to-drag ratio of the winglet can be improved, the drag coefficient can be reduced, etc.; the optimized winglet can reduce energy consumption and improve energy utilization efficiency in practical applications; reducing drag can reduce carbon emissions and other pollutant emissions, and the optimized winglet can reduce operating costs and improve economic benefits.

[0106] In a specific embodiment of the present invention, based on wind tunnel experiments, computational fluid dynamics (CFD) simulations or actual flight tests, experimental result data related to the winglet are collected, and pressure data on the winglet surface are extracted from the experimental results. Charts or graphic tools such as contour maps and cloud maps are used to visualize the pressure data on the winglet surface, and the characteristics of the pressure distribution, such as high-pressure areas, low-pressure areas, and pressure gradients, are analyzed; a geometric model of the winglet is established, and the geometric model is meshed. The mesh is refined to capture key features in the flow field, such as boundary layers and separation zones, and CFD simulations are run to obtain flow field data, lift, drag, and pressure distribution of the winglet under different conditions, extract lift coefficients, drag coefficients, and pressure distribution data, determine geometric parameters such as the range and step size of chord length, wingspan, and sweep angle, and generate models with different geometric parameter combinations.

[0107] In another specific embodiment of the present invention, CFD simulation is run for each set of parameters to obtain corresponding flow field data and performance indicators; geometric parameters and performance indicator data are organized into a data table to generate an initial population, each individual represents a set of geometric parameters, and the population is randomly initialized to ensure the diversity of the parameter space, and the objective function is defined, such as lift / drag ratio, and the fitness value of each individual is calculated through the CFD simulation results, and high-quality individuals are selected according to the fitness value. For example, the first 50% of individuals with high fitness are selected; crossover operations are performed on the selected individuals to generate new individuals. Crossover can be a single-point crossover, a multi-point crossover, etc., and mutation operations are performed on the new individuals to introduce randomness and increase the diversity of the population. Mutation can be a small adjustment of the parameters to generate a new generation of populations, repeat the evaluation, selection, crossover and mutation operations, set the maximum number of iterations or convergence criteria to determine the termination conditions of the optimization process, and select the optimal individual, that is, the optimal geometric parameters, according to the final iteration results.

[0108] In a preferred embodiment of the present invention, the above step 17 may include:

[0109] According to the optimized geometric parameters, the width of the winglet is adjusted and its shape is changed to determine the angle and position of the winglet relative to the blade;

[0110] The position of the winglet is applied to an actual wind turbine, and the performance of the wind turbine during operation is monitored to achieve control of the winglet.

[0111] In an embodiment of the present invention, by optimizing the design and position of the winglet, the winglet can effectively improve the aerodynamic performance of the wind turbine. Specific improvements may include increasing the lift of the blades, reducing air resistance, and ultimately achieving an increase in the total power generation capacity of the wind turbine; the optimized winglet design can reduce the energy loss of the wind turbine and improve the utilization efficiency of wind energy; adjusting the design and position of the winglet can improve the stability and operational reliability of the wind turbine at different wind speeds, and improving the stability of the system helps to reduce downtime and increase the service life of the equipment; the optimized wind turbine can operate efficiently within a wider wind speed range, improving the overall economic benefits, and improving power generation efficiency and system stability can increase the return on investment and reduce long-term operation and maintenance costs.

[0112] In a specific embodiment of the present invention, the winglet width, shape, and curvature geometric parameters provided by the optimization algorithm are obtained, the width and shape of the winglet are adjusted in the CAD software, and the installation angle and position of the winglet relative to the wind turbine blade are obtained based on the optimization data, including determining the angle of attack, installation position, such as the leading edge or trailing edge, and relative height of the winglet, marking and adjusting the installation position on the wind turbine blade, setting an adjustment device or bracket to ensure that the winglet can be accurately installed in the predetermined position and the angle is adjustable, and the winglet is installed on the wind turbine blade according to the design requirements. An automatic or manual control mode is set to adjust the angle and position of the winglet, and sensors and monitoring systems are installed on the wind turbine to track the operating status of the wind turbine and the winglet, monitor the impact of the winglet on the performance of the wind turbine in real time, collect operating data, analyze the contribution of the winglet to the aerodynamic performance of the wind turbine, pay attention to lift, drag, and power generation efficiency indicators, compare the actual performance with the optimization target, and evaluate the improvement effect.

[0113] like Figure 2 As shown, an embodiment of the present invention further provides a blade winglet control system 20 for three-dimensional flow field analysis of a wind turbine blade, comprising:

[0114] The identification module 21 is used to solve the fluid dynamics equations by numerical solution to generate three-dimensional velocity, pressure and temperature distribution data of the blade surface; according to the velocity, pressure and temperature data, the aerodynamic performance and flow failure mode of the blade tip are identified to obtain the flow state of the blade area;

[0115] The acquisition and analysis module 22 is used to identify the aerodynamic performance and flow failure mode of the blade tip according to the speed, pressure and temperature data to obtain the flow state of the blade area; analyze the flow state of the blade area to obtain the geometric parameters of the winglet, including the length, width, installation angle and shape; obtain the installation position of the winglet according to the geometric parameters of the winglet, and the winglet includes a pressure surface winglet and a suction surface winglet; obtain the cantilever plane cascade experimental data under high subsonic conditions, and analyze the influence of the winglet on the aerodynamic performance of the blade under different incoming flow Mach numbers and angles of attack to obtain analysis results and experimental data;

[0116] The optimization and adjustment module 23 is used to scan the parameters and calculate the flow field data according to the analysis results and experimental data, and adjust the geometric parameters of the winglet through multiple simulations, and optimize the winglet design through genetic algorithms and gradient descent methods to obtain optimized geometric parameters; according to the optimized geometric parameters, the width and installation position of the winglet are adjusted to achieve the control of the winglet.

[0117] It should be noted that the system is a system corresponding to the above method, and all implementation methods in the above method embodiment are applicable to this embodiment and can achieve the same technical effect.

[0118] The embodiment of the present invention further provides a computing device, comprising: a processor, a memory storing a computer program, wherein when the computer program is executed by the processor, the method described above is executed. All implementations in the above method embodiment are applicable to this embodiment and can achieve the same technical effect.

[0119] The embodiment of the present invention also provides a computer-readable storage medium storing instructions, which, when executed on a computer, enable the computer to execute the method described above. All implementations in the above method embodiment are applicable to this embodiment and can achieve the same technical effect.

[0120] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A blade winglet control method for three-dimensional flow field analysis of wind turbine blades, characterized in that: The method comprises: The fluid dynamics equations are solved numerically to generate three-dimensional velocity, pressure, and temperature distribution data on the blade surface; Identify the aerodynamic performance and flow failure modes at the blade tip based on velocity, pressure and temperature data to obtain the flow state in the blade area; Analyze the flow state in the blade area to obtain the geometric parameters of the winglet, including length, width, installation angle and shape; According to the geometric parameters of the winglet, the installation position of the winglet is obtained. The winglet includes a pressure surface winglet and a suction surface winglet; Obtain experimental data of cantilever plane cascades under high subsonic conditions, and analyze the effect of winglets on the aerodynamic performance of blades under different incoming flow Mach numbers and angles of attack to obtain analytical results and experimental data; According to the analysis results and experimental data, the parameters are scanned, the flow field data is calculated, and the geometric parameters of the winglet are adjusted through multiple simulations to optimize the winglet design to obtain the optimized geometric parameters; According to the optimized geometric parameters, the width and installation position of the winglet are adjusted to achieve the control of the winglet.

2. The blade winglet control method for three-dimensional flow field analysis of wind turbine blades according to claim 1 is characterized in that: The fluid dynamics equations are numerically solved to generate three-dimensional velocity, pressure and temperature distribution data on the blade surface, including: Create a three-dimensional geometric model of the wind turbine blade, mesh the three-dimensional geometric model, and form a computational mesh; Based on the computational grid, define the boundary conditions of the blade surface, inflow and outflow areas, including the incoming flow velocity, pressure and temperature; According to the fluid dynamics equations and boundary conditions, iterative calculations are performed to generate velocity, pressure and temperature distribution data on the blade surface. The fluid dynamics equations include the continuity equation, the Navier-Stokes equations and the heat transfer equation.

3. The blade winglet control method for three-dimensional flow field analysis of wind turbine blades according to claim 2 is characterized in that: Identify the aerodynamic performance and flow failure modes at the blade tip based on velocity, pressure and temperature data to obtain the flow state in the blade area, including: According to the processing of velocity, pressure and temperature distribution data on the blade surface, three-dimensional images of velocity field, pressure field and temperature field are drawn to obtain the flow pattern and thermal distribution at the blade tip; According to the flow pattern and heat distribution at the blade tip, Calculate the aerodynamic performance index of the blade tip to obtain the aerodynamic efficiency η of the blade tip l , where ps is the static pressure of the gas on the blade tip surface, p a is the static pressure of the fluid in the flow area due to external environmental conditions, n is the surface normal vector for calculating the direction components of lift and drag; cos(θ) is the angle between the fluid flow direction and the surface normal vector, T s is the temperature of the blade tip surface, T a is the static temperature of the fluid in the flow area due to external environmental conditions, is the temperature correction factor, ρ is the density of the fluid, V l is the local velocity at the blade tip, △V 2 It refers to the square of the velocity change caused by the fluctuation of flow velocity or turbulence, C D is the dimensionless coefficient describing the resistance of the fluid at the blade tip, μ is the dynamic viscosity of the fluid, is the viscosity correction factor, It's resistance. Based on the aerodynamic efficiency at the blade tip, flow failure modes are identified and temperature effects are evaluated to obtain the flow state in the blade area.

4. The blade winglet control method for three-dimensional flow field analysis of wind turbine blades according to claim 3 is characterized in that: The flow state in the blade area is analyzed to obtain the geometric parameters of the winglet, including length, width, installation angle and shape, including: According to the flow state in the blade area, the velocity and pressure changes on the winglet surface are analyzed to identify the velocity distribution, pressure distribution and flow separation; The wing length, width, mounting angle, and curvature and twist of the airfoil profile are extracted from the CFD model based on the velocity distribution, pressure distribution, and flow separation.

5. The blade winglet control method for three-dimensional flow field analysis of wind turbine blades according to claim 4 is characterized in that: According to the geometric parameters of the winglet, the installation position of the winglet is obtained. The winglet includes a pressure surface winglet and a suction surface winglet, including: Obtaining geometric parameters of the winglets, including the length, width, installation angle and shape of the pressure side winglets and the suction side winglets; Obtain the aerodynamic characteristics of the main wing, such as pressure distribution, flow state and lift distribution; The installation position and angle of the winglet are obtained according to the geometric parameters of the winglet and the aerodynamic characteristics of the main wing.

6. The blade winglet control method for three-dimensional flow field analysis of wind turbine blades according to claim 5 is characterized in that: Acquire the experimental data of cantilever plane cascade under high subsonic conditions, analyze the influence of winglets on the aerodynamic performance of blades under different incoming flow Mach numbers and angles of attack, and obtain analytical results and experimental data, including: The cascade model is fixed on the cantilever frame in the wind tunnel test section, the position of the cascade model is adjusted to set the flow velocity of the wind tunnel, the flow velocity is controlled under the simulated high subsonic condition, and the angle of attack of the cascade is adjusted to obtain the experimental data of lift coefficient, drag coefficient, flow velocity, temperature and pressure parameters; According to experimental data, the Mach number and angle of attack are adjusted; According to the Mach number and angle of attack, Calculate the lift L1 of the winglet on the aerodynamic performance of the blade under different Mach numbers and angles of attack. Calculate the drag D1 of the winglet on the aerodynamic performance of the blade under different Mach numbers and angles of attack, where ρ1 is the mass density of the air, V2 is the air velocity, S is the projected area of ​​the blade, and C l，0 is the base lift coefficient when there is no lift, K l is the adjustment coefficient, Re is the Reynolds number, which represents the ratio of the inertial force to the viscous force of the flow; M is the ratio of the air flow velocity to the speed of sound, S ref is the projected area of ​​the blade, α is the angle of attack of the blade, a l 、b l and c l is the lift correction factor, C d，0 is the base drag coefficient in the absence of lift, K d is the coefficient for adjusting the drag coefficient, a d 、b d and c d is the drag correction factor.

7. The blade winglet control method for three-dimensional flow field analysis of wind turbine blades according to claim 6 is characterized in that: According to the analysis results and experimental data, the parameters are scanned, the flow field data is calculated, and the geometric parameters of the winglet are adjusted through multiple simulations to optimize the winglet design to obtain the optimized geometric parameters, including: According to the analysis results and experimental data, the flow field data of the winglet is obtained, including the lift coefficient, drag coefficient, and pressure distribution; According to the experimental data, numerical simulation is carried out by cFD software to establish the mathematical model of the flow field of the winglet; Perform a preliminary scan of the geometric parameters to obtain the flow field data and performance indicators under the geometric parameters; According to the data of geometric parameters, the initial population is generated. Each individual represents a set of geometric parameters. The fitness of each individual is evaluated by the objective function. A new generation of population is generated through selection, crossover and mutation operations. The iterative process is used to optimize the objective function. When the maximum number of iterations is reached, the optimization process is terminated to obtain the best parameters. The optimal parameters are applied to CFD simulation to obtain optimized geometric parameters.

8. A blade winglet control system for three-dimensional flow field analysis of wind turbine blades, characterized in that: Applied to the method according to any one of claims 1 to 7, comprising: An identification module is used to solve the fluid dynamics equations by numerical solution to generate three-dimensional velocity, pressure and temperature distribution data of the blade surface; based on the velocity, pressure and temperature data, the aerodynamic performance and flow failure mode of the blade tip are identified to obtain the flow state of the blade area; The acquisition and analysis module is used to identify the aerodynamic performance and flow failure mode of the blade tip according to the speed, pressure and temperature data to obtain the flow state of the blade area; analyze the flow state of the blade area to obtain the geometric parameters of the winglet, including the length, width, installation angle and shape; obtain the installation position of the winglet according to the geometric parameters of the winglet, and the winglet includes a pressure surface winglet and a suction surface winglet; obtain the experimental data of the cantilever plane cascade under high subsonic conditions, and analyze the influence of the winglet on the aerodynamic performance of the blade under different incoming flow Mach numbers and angles of attack to obtain analysis results and experimental data; The optimization and adjustment module is used to scan the parameters and calculate the flow field data according to the analysis results and experimental data, and adjust the geometric parameters of the winglet through multiple simulations. The winglet design is optimized through genetic algorithms and gradient descent methods to obtain optimized geometric parameters; according to the optimized geometric parameters, the width and installation position of the winglet are adjusted to achieve the control of the winglet.

9. A computing device, characterized in that include: one or more processors; A storage device for storing one or more programs, when the one or more programs are executed by the one or more processors, the one or more processors implement the method as claimed in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a program, which, when executed by a processor, implements the method according to any one of claims 1 to 7.

Images