Method, device, equipment and medium for automatically generating multi-block structured grid of airfoil

Abstract

The present application discloses a method, device, equipment and medium for automatically generating multi-block structured grids of an airfoil, and relates to the technical field of computational fluid dynamics. The method determines the structured grid topology type of the airfoil and establishes a geometric parameterized model; calculates the coordinates of the grid topology control points on the airfoil and their unit normal vectors; calculates the coordinates of the outer boundary and far-field grid topology control points of the O-type grid; calculates the grid edge data on the airfoil using a grid point distribution function according to the coordinates of the grid topology control points, the number of grid points on the grid edge in the grid topology, the grid size at the starting position and the grid size at the ending position, and respectively calculates the grid edge data of the outer boundary of the O-type grid, the grid edge data of the normal of the O-type grid and other grid edge data in the grid topology to construct each grid surface, and automatically generates multi-block structured grids of the airfoil based on each grid surface, thereby improving the efficiency of generating multi-block structured grids of the airfoil, supporting airfoil performance analysis at different grid resolutions, and providing support for rapid selection and optimization of airfoils.

Description

Technical Field

[0001] The present invention relates to the technical field of computational fluid dynamics, and in particular to a method, device, equipment and medium for automatically generating multi-block structured grids of an airfoil. Background Art

[0002] At present, the automatic generation of airfoil flow field calculation grid is mainly achieved through two ways, one is to use unstructured filling, and the other is based on hyperbolic propulsion. The unstructured filling method has the advantage of high degree of automation, but the grid unit resolution and solution accuracy are low, which may introduce errors in airfoil performance analysis and increase design uncertainty. The hyperbolic propulsion method generates a structured grid, which has the advantages of good grid unit orthogonality and high resolution, but the propulsion boundary is uncertain and the parameters are highly dependent. It requires certain manual intervention, is difficult to achieve complete automation, and is difficult to apply to multivariate airfoils. Compared with unstructured filling and hyperbolic propulsion, multi-block structured airfoil grid has greater flexibility. It can obtain high-quality and high-resolution grids for different types of airfoils. It is a widely used grid in airfoil performance calculation and analysis. Multi-block structured airfoil grid is still achieved by manual block segmentation. Although the popularity of commercial software has greatly reduced the generation time of multi-block airfoil grid, it still requires experienced personnel to spend a certain amount of time to generate it, which is still a relatively large time consumption for airfoil selection involving thousands of states.

[0003] It can be seen from the above that how to realize the automatic generation of multi-block structured grids for airfoils, improve the efficiency of generating multi-block structured grids for airfoils, support airfoil performance analysis at different grid resolutions, and provide support for rapid selection and optimization of airfoils are problems to be solved in this field. Summary of the invention

[0004] In view of this, the purpose of the present invention is to provide a method, device, equipment and medium for automatically generating multi-block structured grids of airfoils, which can realize the automatic generation of multi-block structured grids of airfoils, improve the efficiency of generating multi-block structured grids of airfoils, support airfoil performance analysis at different grid resolutions, and provide support for rapid selection and optimization of airfoils. The specific scheme is as follows:

[0005] In a first aspect, the present application discloses a method for automatically generating a multi-block structured grid of an airfoil, comprising:

[0006] Determine the structured grid topology type of the airfoil, and establish a geometric parameterized model of the airfoil based on pre-acquired airfoil geometry data;

[0007] Calculating the coordinates of the grid topology control points on the airfoil based on the structured grid topology type and the geometric parameterized model, and calculating the unit normal vectors of the grid topology control points on the airfoil according to the coordinates of the grid topology control points on the airfoil;

[0008] Calculating the coordinates of the outer boundary grid topology control points of the O-shaped grid according to the unit normal vector, and determining the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology;

[0009] Determine the grid size of the starting position and the grid size of the ending position of the grid edge on the airfoil, according to the coordinates of the grid topology control point on the airfoil, the number of grid points on the grid edge in the grid topology, the grid size of the starting position and the grid size of the ending position of the grid edge on the airfoil, and use the grid point distribution function to determine the position distribution of the internal grid points of the grid edge on the airfoil, and calculate the grid edge data on the airfoil using the geometric parameterized model and the position distribution of the internal grid points of the grid edge on the airfoil; the grid point distribution function includes a hyperbolic distribution function;

[0010] Determine the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, and calculate the O-type grid outer boundary grid edge data, the O-type grid normal grid edge data, and the other grid edge data in the grid topology based on the grid edge data on the airfoil, the grid topology control point coordinates on the airfoil, the O-type grid outer boundary grid topology control point coordinates, the far-field grid topology control point coordinates, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology by using a grid point distribution function and adopting a linear interpolation method or a nonlinear interpolation method;

[0011] Each mesh surface is constructed using the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-type mesh, the normal mesh edge data of the O-type mesh, and other mesh edge data in the mesh topology, and a multi-block structured mesh of the airfoil is automatically generated based on each of the mesh surfaces.

[0012] Optionally, the determining of the structured grid topology type of the airfoil includes:

[0013] According to the airfoil type and shape, and combined with the requirements of airfoil flow numerical simulation, the structured grid topology type of the airfoil is selected;

[0014] Determine the number of control points, the number of control edges, the number of control surfaces, the connection relationship between control points, the sharing relationship between control edges, and the adjacent relationship between control surfaces in the mesh topology.

[0015] Optionally, establishing a geometric parameterized model of the airfoil according to the pre-acquired airfoil geometric data includes:

[0016] Calculating the Euclidean distances between adjacent geometric shape description points according to the coordinates of the geometric shape description points of the airfoil surface in the pre-acquired airfoil geometric data, and accumulating the Euclidean distances to obtain the curvilinear distance between each geometric shape description point on the airfoil surface and the trailing edge point on the upper surface of the airfoil;

[0017] Based on the geometric shape of the airfoil surface, the point coordinates and the curve distance are described, and an interpolation method is used to establish a geometric parameterized model of the airfoil.

[0018] Optionally, calculating the unit normal vector of the grid topology control point on the airfoil according to the coordinates of the grid topology control point on the airfoil includes:

[0019] According to the coordinates of the grid topology control point on the airfoil, position information of adjacent points adjacent to the grid topology control point on the airfoil is calculated, and the position information of the adjacent points is calculated using a geometric parameterized model to obtain the coordinates of the adjacent points;

[0020] The normal vector of the grid topology control point on the airfoil is calculated based on the coordinates of the neighboring points, and the normal vector is normalized to obtain a unit normal vector.

[0021] Optionally, calculating the coordinates of the outer boundary mesh topology control point of the O-shaped mesh according to the unit normal vector includes:

[0022] The coordinates of the topological control points of the outer boundary grid of the O-shaped grid are calculated according to the unit normal vector using a coordinate calculation formula; the coordinate calculation formula is:

[0023] ;

[0024] ;

[0025] in, is the coordinate of the topological control point of the outer boundary grid of the O-type grid, are the coordinates of the mesh topology control points on the airfoil, is the O-grid advancement distance, is the unit normal vector and c is the chord length of the airfoil.

[0026] Optionally, based on the mesh edge data on the airfoil, the mesh topology control point coordinates on the airfoil, the mesh topology control point coordinates of the outer boundary of the O-type mesh, the mesh topology control point coordinates of the far-field mesh, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size and the ending position mesh size of the outer boundary mesh edge of the O-type mesh, the starting position mesh size and the ending position mesh size of the normal mesh edge of the O-type mesh, and the starting position mesh size and the ending position mesh size of other mesh edges in the mesh topology, the mesh point distribution function is used and a linear interpolation method or a nonlinear interpolation method is used to respectively calculate the mesh edge data of the outer boundary of the O-type mesh, the mesh edge data of the normal mesh of the O-type mesh, and other mesh edge data in the mesh topology, including:

[0027] Based on the mesh edge data on the airfoil, the mesh topology control point coordinates on the airfoil, the mesh topology control point coordinates on the outer boundary of the O-type mesh, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size of the outer boundary mesh edge of the O-type mesh, and the ending position mesh size, the mesh point distribution function is used and the nonlinear interpolation method is used to calculate the mesh edge data of the outer boundary of the O-type mesh;

[0028] Based on the grid topology control point coordinates on the airfoil, the grid topology control point coordinates of the outer boundary of the O-shaped grid, the number of grid points on the grid edge in the grid topology, the starting position grid size of the O-shaped grid normal grid edge, and the ending position grid size, the grid point distribution function is used and the linear interpolation method is used to calculate the O-shaped grid normal grid edge data;

[0029] Based on the coordinates of the far-field grid topology control points, the coordinates of the grid topology control points on the outer boundary of the O-shaped grid, the number of grid points on the grid edge in the grid topology, the starting position grid size of other grid edges in the grid topology, and the ending position grid size, the grid point distribution function is used and linear interpolation or nonlinear interpolation is used to calculate other grid edge data in the grid topology.

[0030] Optionally, the step of constructing each mesh surface by using the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-shaped mesh, the normal mesh edge data of the O-shaped mesh, and other mesh edge data in the mesh topology, and automatically generating a multi-block structured mesh of the airfoil based on each mesh surface includes:

[0031] Using the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-shaped mesh, the mesh edge data on the normal direction of the O-shaped mesh, and other mesh edge data in the mesh topology, and using a preset algebraic interpolation method to construct each mesh surface; the preset algebraic interpolation method includes a transfinite interpolation method;

[0032] The boundary type of the logical grid edge of each grid surface is determined according to the adjacent relationship between the control surfaces, and the grid surfaces are associated and assembled to generate a multi-block structured grid of the airfoil.

[0033] In a second aspect, the present application discloses an automatic generation device for a multi-block structured grid of an airfoil, comprising:

[0034] A model building module, used for determining a structured grid topology type of the airfoil and building a geometric parameterized model of the airfoil according to pre-acquired airfoil geometric data;

[0035] A unit normal vector calculation module, used to calculate the coordinates of the grid topology control points on the airfoil based on the structured grid topology type and the geometric parameterized model, and calculate the unit normal vectors of the grid topology control points on the airfoil according to the coordinates of the grid topology control points on the airfoil;

[0036] A control point coordinate calculation module, used to calculate the coordinates of the outer boundary grid topology control points of the O-shaped grid according to the unit normal vector, and determine the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology;

[0037] The airfoil mesh edge data calculation module is used to determine the starting position mesh size and the ending position mesh size of the airfoil mesh edge, according to the mesh topology control point coordinates on the airfoil, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size and the ending position mesh size of the airfoil mesh edge, and the position distribution of the internal mesh points of the airfoil mesh edge is determined by using the grid point distribution function, and the airfoil mesh edge data is calculated by using the geometric parameterized model and the position distribution of the internal mesh points of the airfoil mesh edge; the grid point distribution function includes a hyperbolic distribution function;

[0038] an O-type and other grid edge data calculation module, for determining the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, and based on the grid edge data on the airfoil, the coordinates of the grid topology control points on the airfoil, the coordinates of the outer boundary grid topology control points of the O-type grid, the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, and respectively calculating the O-type grid outer boundary grid edge data, the O-type grid normal grid edge data, and the other grid edge data in the grid topology by using a grid point distribution function and adopting a linear interpolation method or a nonlinear interpolation method;

[0039] The automatic grid generation module is used to construct each grid surface by using the grid edge data on the airfoil, the grid edge data on the outer boundary of the O-shaped grid, the normal grid edge data of the O-shaped grid and other grid edge data in the grid topology, and automatically generate a multi-block structured grid of the airfoil based on each of the grid surfaces.

[0040] In a third aspect, the present application discloses an electronic device, comprising:

[0041] Memory, used to store computer programs;

[0042] The processor is used to execute the computer program to implement the aforementioned method for automatically generating a multi-block structured grid for an airfoil.

[0043] In a fourth aspect, the present application discloses a computer storage medium for storing a computer program; wherein, when the computer program is executed by a processor, the steps of the aforementioned method for automatically generating a multi-block structured grid for an airfoil are implemented.

[0044] It can be seen that the present application provides a method for automatically generating a multi-block structured grid of an airfoil, including determining a structured grid topology type of the airfoil, and establishing a geometric parameterized model of the airfoil according to pre-acquired airfoil geometric data; calculating the coordinates of the grid topology control points on the airfoil based on the structured grid topology type and the geometric parameterized model, and calculating the unit normal vector of the grid topology control points on the airfoil according to the coordinates of the grid topology control points on the airfoil; calculating the coordinates of the grid topology control points of the outer boundary of the O-type grid according to the unit normal vector, and determining the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology; determining the starting position grid size and the ending position grid size of the grid edge on the airfoil, according to the grid topology control point coordinates on the airfoil, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the grid edge on the airfoil, and using a grid point distribution function to determine the position distribution of the internal grid points of the grid edge on the airfoil, and using the geometric parameterized model and the position distribution of the internal grid points of the grid edge on the airfoil to calculate the grid edge data on the airfoil; the grid point distribution function includes a hyperbolic distribution function; determining the outer boundary grid of the O-type grid The mesh size of the starting position and the ending position of the edge, the mesh size of the starting position and the ending position of the O-shaped mesh normal mesh edge, the mesh size of the starting position and the ending position of other mesh edges in the mesh topology, based on the mesh edge data on the airfoil, the mesh topology control point coordinates on the airfoil, the mesh topology control point coordinates of the outer boundary of the O-shaped mesh, the far-field mesh topology control point coordinates, the number of mesh points on the mesh edge in the mesh topology, the mesh size of the starting position and the ending position of the mesh edge of the O-shaped mesh outer boundary, the starting position of the mesh edge of the O-shaped mesh normal mesh edge, and the mesh size of the starting position of the mesh edge of the O-shaped mesh normal mesh edge. The grid size and the end position grid size, the start position grid size and the end position grid size of other grid edges in the grid topology are set, and the grid point distribution function is used and a linear interpolation method or a nonlinear interpolation method is used to respectively calculate the O-type grid outer boundary grid edge data, the O-type grid normal grid edge data and other grid edge data in the grid topology; the grid edge data on the airfoil, the O-type grid outer boundary grid edge data, the O-type grid normal grid edge data and other grid edge data in the grid topology are used to construct each grid surface, and a multi-block structured grid of the airfoil is automatically generated based on each of the grid surfaces.The present application establishes a geometric parameterized model of the airfoil based on pre-acquired airfoil geometry data, calculates the coordinates of the grid topology control points on the airfoil using the structured grid topology type and the geometric parameterized model, calculates the unit normal vectors of the grid topology control points on the airfoil based on the coordinates of the grid topology control points on the airfoil, calculates the coordinates of the grid topology control points on the outer boundary of the O-type grid, determines the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, determines the starting position grid size and the ending position grid size of the grid edge on the airfoil, calculates the grid edge data on the airfoil, and then determines the starting position grid size and the ending position grid size of the grid edge on the outer boundary of the O-type grid, and the starting position of the normal grid edge of the O-type grid The grid size and the grid size at the end position, the grid size at the starting position and the grid size at the end position of other grid edges in the grid topology are used to calculate the grid edge data of the outer boundary of the O-type grid, the normal grid edge data of the O-type grid and other grid edge data in the grid topology, and finally each grid surface is constructed, and the multi-block structured grid of the airfoil is automatically generated based on each grid surface. In view of the problem that the generation of multi-block structured grids of airfoils requires manual intervention and is difficult to automate, the present application can realize the automatic generation of multi-block structured grid topology of airfoils, and compared with the original manual segmentation method, it can greatly improve the efficiency of the generation of multi-block structured grids of airfoils, provide support for rapid selection and optimization of airfoils, and support airfoil performance analysis at different grid resolutions. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0046] Figure 1 A flow chart of a method for automatically generating a multi-block structured grid for an airfoil disclosed in the present application;

[0047] Figure 2 An airfoil shape diagram disclosed in the present application;

[0048] Figure 3 A structured grid topology diagram of an airfoil disclosed in the present application;

[0049] Figure 4 A global view of the control point, control edge, and control surface numbering in a grid topology disclosed in the present application;

[0050] Figure 5 A leading edge view of numbering control points, control edges, and control surfaces in a grid topology disclosed in the present application;

[0051] Figure 6 A trailing edge view for numbering control points, control edges, and control surfaces in a grid topology disclosed in the present application;

[0052] Figure 7 A global view is automatically generated for a NACA0012 airfoil mesh disclosed in this application;

[0053] Figure 8 Automatically generate a leading edge view for a NACA0012 airfoil mesh disclosed in this application;

[0054] Fig. 9 Automatically generate a trailing edge view for a NACA0012 airfoil mesh disclosed in this application;

[0055] Fig.10 A specific flow chart for automatically generating a multi-block structured grid for an airfoil disclosed in this application;

[0056] Fig.11 This is a schematic diagram of the structure of an automatic generation device for multi-block structured grids of an airfoil disclosed in this application;

[0057] Fig.12 A structural diagram of an electronic device provided for this application. DETAILED DESCRIPTION

[0058] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0059] At present, the automatic generation of airfoil flow field calculation grid is mainly achieved through two ways, one is to use unstructured filling, and the other is based on hyperbolic propulsion. The unstructured filling method has the advantage of high degree of automation, but the grid unit resolution and solution accuracy are low, which may introduce errors in airfoil performance analysis and increase design uncertainty. The hyperbolic propulsion method generates a structured grid, which has the advantages of good grid unit orthogonality and high resolution, but the propulsion boundary is uncertain and the parameters are highly dependent. It requires certain manual intervention, is difficult to achieve complete automation, and is difficult to apply to multivariate airfoils. Compared with unstructured filling and hyperbolic propulsion, multi-block structured airfoil grid has greater flexibility. It can obtain high-quality and high-resolution grids for different types of airfoils. It is a widely used grid in airfoil performance calculation and analysis. Multi-block structured airfoil grid is still achieved by manual block segmentation. Although the popularity of commercial software has greatly reduced the generation time of multi-block airfoil grid, it still requires experienced personnel to spend a certain amount of time to generate it, which is still a relatively large time consumption for airfoil selection involving thousands of states. It can be seen from the above that how to realize the automatic generation of multi-block structured grids for airfoils, improve the efficiency of generating multi-block structured grids for airfoils, support airfoil performance analysis at different grid resolutions, and provide support for rapid selection and optimization of airfoils are problems to be solved in this field.

[0060] See also Figure 1 As shown, an embodiment of the present invention discloses a method for automatically generating a multi-block structured grid of an airfoil, which may specifically include:

[0061] Step S11: determining the structured grid topology type of the airfoil, and establishing a geometric parameterized model of the airfoil according to pre-acquired airfoil geometric data.

[0062] In this embodiment, according to the airfoil type and airfoil shape, and in combination with the airfoil flow numerical simulation requirements, the structured grid topology type of the airfoil is screened out; the number of control points, the number of control edges, the number of control surfaces, the connection relationship between control points, the sharing relationship between control edges, and the adjacent relationship between control surfaces in the grid topology are determined. For example, the grid topology type of the airfoil with a trailing edge band thickness is selected, and the airfoil shape with a trailing edge band thickness is as follows: Figure 2 As shown, considering the simulation requirements of transonic flow, the grid topology of O-type around the airfoil + overall H-type is adopted. The structured grid topology of the airfoil is as follows: Figure 3 As shown in Figure 2, the entire grid topology has 28 grid points, 40 grid edges, and 12 grid faces, that is, , , , Figure 4 Number the control points, control edges, and control surfaces in the mesh topology (global view), Figure 5 Numbering of control points, control edges, and control surfaces in the mesh topology (leading edge view), Figure 6 Numbering of control points, control edges, and control surfaces in the mesh topology (back edge view), Figure 4 , Figure 5 , Figure 6 It describes the connection relationship between mesh topology control points, the sharing relationship of mesh topology control edges, and the adjacent relationship of mesh topology control surfaces, where 1-28 are the numbers of mesh topology control points, (1)-(40) are the numbers of mesh topology control edges, and [1]-

[12] are the numbers of mesh topology control surfaces. For a unified description, the coordinates of the airfoil grid points are defined in the XY plane, with the airfoil chord direction being the X direction and the airfoil normal being the Y direction.

[0063] The Euclidean distances between adjacent geometric shape description points are calculated according to the coordinates of the geometric shape description points of the airfoil surface in the pre-acquired airfoil geometric data, and the Euclidean distances are accumulated to obtain the curvilinear distance between each geometric shape description point on the airfoil surface and the trailing edge point on the upper surface of the airfoil. Based on the coordinates of the geometric shape description points on the airfoil surface and the curvilinear distances, a geometric parameterized model of the airfoil is established using an interpolation method.

[0064] Specifically, according to the type and shape of the airfoil and the requirements of numerical simulation of airfoil flow, the appropriate structured grid topology type is selected to determine the control points, control edges, and control surfaces ( , , ) and determine the connection relationship between control points, the sharing relationship between control edges, and the adjacent relationship between control surfaces. The input of the geometric parameterization model is the curve distance from the airfoil surface point to the trailing edge point on the airfoil upper surface. The output is the X and Y coordinates of the point. The coordinates of any point on the airfoil can be obtained using this geometric parameterized model. The specific geometric parameterization model construction process is as follows: the coordinates of n geometric shape description points on the airfoil surface are known , calculate the Euclidean distance between adjacent geometric points:

[0065] ;

[0066] And add them up to get the curve distance from each airfoil surface description point to the trailing edge point of the airfoil upper surface:

[0067] ;

[0068] Describing the coordinates of points according to the airfoil geometry The curvilinear distance from the surface description point to the trailing edge point on the upper surface of the airfoil Based on the interpolation method, the coordinates of the geometric description points on the airfoil surface can be established With surface point position The functional relationship is the geometric parameterized model of the airfoil. Based on this parameterized model, given any position L, the corresponding point coordinates P = (x, y, z) can be obtained. Here, one-dimensional radial basis function interpolation is used as an illustration. In actual use, it is not limited to this interpolation method. Any interpolation method that meets the accuracy requirements can be used:

[0069] ;

[0070] Among them, f is the function to be interpolated, and here they represent the point coordinates (x, y, z), are the unknown coefficients of the interpolation function, is the basis function, and different basis function types can be selected. The coordinates of points described by the airfoil surface geometry and location The constructed linear algebraic equations determine that for different coordinate components, a set of interpolation coefficients will be obtained respectively .

[0071] Step S12: Calculating the coordinates of the grid topology control points on the airfoil based on the structured grid topology type and the geometric parameterized model, and calculating the unit normal vectors of the grid topology control points on the airfoil according to the coordinates of the grid topology control points on the airfoil.

[0072] In this embodiment, the coordinates of the grid topology control points on the airfoil are calculated based on the structured grid topology type and the geometric parameterized model, and the position information of neighboring points adjacent to the grid topology control points on the airfoil is calculated according to the coordinates of the grid topology control points on the airfoil. The geometric parameterized model is used to calculate the position information of the neighboring points to obtain the coordinates of the neighboring points, and the normal vector of the grid topology control points on the airfoil is calculated based on the coordinates of the neighboring points. The normal vector is vectorized to obtain a unit normal vector.

[0073] In this embodiment, the position of the airfoil grid topology control point on the airfoil is determined according to the grid topology structure and the accuracy requirement of the flow simulation. Then, based on the airfoil geometry parameterized model constructed in the above steps, the coordinates of the mesh topology control points on the airfoil are calculated by interpolation. , and then calculate the unit normal vector of the mesh topology control point on the airfoil.

[0074] For example, given the coordinates of 201 geometric points describing the airfoil surface, calculate the Euclidean distance between adjacent geometric points: , the accumulated curve distance of each airfoil surface description point from the trailing edge point of the airfoil upper surface is obtained:

[0075] ;

[0076] Figure 4 , Figure 5 , Figure 6 Numbers 1-8 are grid topology control points. The coordinates of the grid topology control points on the airfoil are , determine the position of airfoil mesh topology control points 1-8 on the airfoil , and then interpolate the coordinates of the grid topology control points based on the airfoil geometry parameterized model; where, , This example takes , , , , , .

[0077] The process of calculating the unit normal vector is as follows: first, when the distance is small enough, the line connecting the front and rear adjacent points will approach the tangent line of the control point, and the curve distance between the adjacent point and the control point is selected to be no more than 0.001 times the chord length of the airfoil; then, based on the airfoil geometric parameterized model, the coordinates of the adjacent points before and after the control point are calculated; finally, the line connecting the adjacent points is used as the direction of the tangent vector , calculate the normal vector of the control point , and obtain the unit normal vector of the control point position by vector normalization For control points without tangent vectors, the weighted normalization of the unit normal vectors on both sides of the control point can be expressed as ,in , is the weighting coefficient, , are the unit normal vectors on the left and right sides of the control point.

[0078] When the distance is small enough, the line connecting the front and rear neighboring points will approach the tangent line of the control point. In this example, the curve distance between the neighboring point and the control point is selected as 0.001c. Here, the positions of the front and rear neighboring points of the grid topology control points numbered 2-7 are , , the position of the previous neighboring point of the grid topology control point numbered 1 is , the position of the next neighboring point of the grid topology control point numbered 8 is .

[0079] Step S13: Calculate the coordinates of the outer boundary grid topology control points of the O-shaped grid according to the unit normal vector, and determine the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology.

[0080] In this embodiment, the coordinates of the outer boundary grid topology control points of the O-shaped grid are calculated according to the unit normal vector and the coordinate calculation formula is used, and the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology are determined; the coordinate calculation formula is:

[0081] ;

[0082] ;

[0083] in, is the coordinate of the topological control point of the outer boundary grid of the O-type grid, , are the coordinates of the mesh topology control points on the airfoil, is the O-grid advancement distance, is the unit normal vector, , c is the chord length of the airfoil.

[0084] Specifically, according to the calculated unit normal vector, the coordinates of the topological control points of the outer boundary of the O-type grid can be obtained through the advancement distance of the O-type grid. According to the experience of numerical simulation of airfoil flow, the O-type grid advancement distance is selected to be 0.03 times the chord length of the airfoil to obtain a better flow simulation accuracy. In this embodiment, 0.03 times the chord length of the airfoil is used by default. The coordinate calculation formula of the topological control points of the outer boundary of the O-type grid is shown above, so as to calculate the coordinates of the topological control points of the outer boundary of the O-type grid ,Right now Figure 4 , Figure 5 , Figure 6 The coordinates of the mesh topology control points numbered 9-16 in .

[0085] Determine the coordinates of the far-field mesh topology control points The process is as follows: for the far-field control points of the airfoil mesh topology, they are determined by the far-field distance and grid line consistency constraints. According to the experience of airfoil flow simulation, in most cases, the influence of the far-field boundary on the flow field simulation results can be ignored when the airfoil mesh far field is more than 20 times the chord length from the wall. Based on the far-field distance constraint, the X-coordinates of the far-field incoming flow and outlet boundary grid topology control points, and the Y-coordinates of the far-field upper and lower boundary grid topology control points can be determined respectively. Then, based on the grid line consistency constraint, the Y-coordinates of the far-field incoming flow and outlet boundary grid topology control points, and the X-coordinates of the far-field upper and lower boundary grid topology control points can be determined respectively. Specifically, Figure 4 , Figure 5 , Figure 6 Numbers 17-28 are far-field grid topology control points. The far-field control points of the airfoil grid topology are determined by the far-field distance and grid line consistency constraints. In this example, , , , , , , , , , where the curvature change of the airfoil head is considered. In order to improve the mesh quality, the X coordinates of points 18 and 26 are moved 0.5 times the chord length in the incoming flow direction, that is, the X coordinates are reduced by 0.5 times the chord length. The actual constructed airfoil mesh topology is different from Figure 3 There is a slight difference. The NACA0012 airfoil mesh is automatically generated (global view) as shown in Figure 7 shown.

[0086] The process of determining the number of grid points on the grid edge in the grid topology is as follows: according to the requirements of the airfoil shape and flow simulation accuracy, considering the constraints of multi-grid calculation acceleration, respectively determine the number of grid points on the grid edge of the airfoil leading edge, upper and lower wing surfaces, airfoil trailing edge, O-shaped grid propulsion direction, between the outer boundary of the O-shaped grid and the far field boundary, and then determine the number of grid points on other grid edges according to the constraint that the number of grid points on opposite sides in the structured grid is equal, thereby obtaining the number of grid points on the grid edge in the grid topology. In this embodiment, take , , , , , , , , , , .

[0087] Step S14: Determine the starting position grid size and the ending position grid size of the grid edge on the airfoil, according to the coordinates of the grid topology control point on the airfoil, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the grid edge on the airfoil, and use the grid point distribution function to determine the position distribution of the internal grid points of the grid edge on the airfoil, and use the geometric parameterized model and the position distribution of the internal grid points of the grid edge on the airfoil to calculate the grid edge data on the airfoil; the grid point distribution function includes a hyperbolic distribution function.

[0088] In this embodiment, the continuity constraint between the numerical simulation of the airfoil flow and the grid size is considered, the starting position grid size and the ending position grid size of the grid edge on the airfoil are determined, and according to the coordinates of the grid topology control point on the airfoil, the number of grid points on the grid edge in the grid topology, the starting position grid size of the grid edge on the airfoil, and the ending position grid size, the position distribution of the internal grid points of the grid edge on the airfoil is obtained using the grid point distribution function, the grid point distribution function includes a hyperbolic distribution function but is not limited to this function method, and the geometric parameterized model is used to calculate the grid edge data on the airfoil.

[0089] Specifically, the process of constructing the mesh edges (1)-(8) on the airfoil is as follows: first, considering the continuity constraint between the numerical simulation of the airfoil flow and the mesh size, the mesh sizes of the start and end positions of the mesh edges (1)-(8) on the airfoil are determined, and then, according to the coordinates of the mesh topology control points and the number of grid points on the grid edge, and the position distribution of the internal grid points of the grid edges (1)-(8) on the airfoil is calculated using the grid point distribution function. This embodiment adopts the most commonly used Hyperbolic distribution method in grid generation, but is not limited to this method to obtain the position distribution of the grid points. Finally, based on the airfoil geometry parameterization model, the coordinates of the grid points on the grid edge are calculated to obtain the grid edge data on the airfoil. In this example, the grid edge (4) and the grid edge (8) are the leading edge and trailing edge grid edges, and the grid points are evenly distributed. The starting point of the grid edge (1) is the grid topology control point 2, and the ending point is the control point 1. The grid size at the starting position (control point 2) is twice the average size, and the grid size at the ending position (control point 1) is the same as the grid size of the grid edge (8), satisfying the grid size continuity constraint. The starting point of mesh edge (3) is control point 4, and the ending point is control point 3. The grid size of the starting position (control point 4) is the same as that of mesh edge (4), satisfying the grid size continuity constraint. The grid size of the ending position (control point 3) is set to twice the average size. The starting point of mesh edge (2) is control point 3, and the ending point is control point 2. The grid size of the starting position (control point 3) is set to 1.1 times the grid size of the ending position of mesh edge (3), and the grid size of the ending position (control point 2) is set to 1.1 times the grid size of the starting position of mesh edge (1), considering the grid size continuity and growth constraints. The distribution of mesh edges (4), (5), and (6) adopts the same strategy as mesh edges (3), (2), and (1), respectively.

[0090] Step S15: Determine the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology; based on the grid edge data on the airfoil, the coordinates of the grid topology control points on the airfoil, the coordinates of the outer boundary grid topology control points of the O-grid, the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, use the grid point distribution function and adopt linear interpolation method or nonlinear interpolation method to respectively calculate the O-grid outer boundary grid edge data, the O-grid normal grid edge data, and other grid edge data in the grid topology.

[0091] In this embodiment, based on the grid edge data on the airfoil, the grid topology control point coordinates on the airfoil, the grid topology control point coordinates of the outer boundary of the O-type grid, the number of grid points on the grid edge in the grid topology, the starting position grid size of the outer boundary grid edge of the O-type grid, and the ending position grid size, the grid point distribution function is used and the nonlinear interpolation method is used to calculate the O-type grid outer boundary grid edge data; based on the grid topology control point coordinates on the airfoil, the grid topology control point coordinates of the outer boundary of the O-type grid, the number of grid points on the grid edge in the grid topology, the starting position grid size of the normal grid edge of the O-type grid, and the ending position grid size, the grid point distribution function is used and the linear interpolation method is used to calculate the O-type grid normal grid edge data; based on the far-field grid topology control point coordinates, the grid topology control point coordinates of the outer boundary of the O-type grid, the number of grid points on the grid edge in the grid topology, the starting position grid size of other grid edges in the grid topology, and the ending position grid size, the grid point distribution function is used and the linear interpolation method or the nonlinear interpolation method is used to calculate other grid edge data in the grid topology.

[0092] Specifically, the process of constructing the outer boundary grid edge (9)-(16) of the O-shaped grid is as follows: according to the numerical simulation requirements of the airfoil flow and the continuity constraint between the grid sizes, the grid size of the starting position and the grid size of the end position of the grid edge (9)-(16) are determined, and based on the grid edge data on the airfoil, the grid topology control point coordinates on the airfoil, and the grid topology control point coordinates of the outer boundary grid of the O-shaped grid, the grid point distribution function is used to copy the outer boundary grid edge of the O-shaped grid, thereby obtaining the outer boundary grid edge data of the O-shaped grid. In this example, the grid edge (12) and the grid edge (16) correspond to the leading edge and the trailing edge positions respectively, and the internal grid points are still uniformly distributed. The shape of the grid edge (12) is obtained by proportionally copying the shape of the grid edge (4), and the proportional coefficient is selected as 0.75. The grid edge (16) is connected by a straight line. The shape of mesh edge (9) is obtained by proportionally copying mesh edge (1), with a proportional coefficient of 1.0. The grid size at the starting position (control point 10) is the same as the grid size at the starting position of mesh edge (1), and the grid size at the ending position (control point 9) is the same as the grid size at mesh edge (16). The shape of mesh edge (10) is obtained by proportionally copying mesh edge (2), with a proportional coefficient of 1.0. The grid size at the starting position (control point 11) is the same as the grid size at the starting position of mesh edge (1), and the grid size at the ending position (control point 10) is the same as the grid size at the ending position of mesh edge (2). The shape of mesh edge (11) is obtained by proportionally copying mesh edge (3), with a proportional coefficient of 1.0. The grid size at the starting position (control point 12) is the same as the grid size at the starting position of mesh edge (3), and the grid size at the ending position (control point 11) is the same as the grid size at the ending position of mesh edge (3). The shapes and sizes of mesh edges (13), (14), and (15) are obtained in the same way as mesh edges (11), (10), and (9), respectively.

[0093] In this embodiment, according to the needs of airfoil flow simulation, the starting position grid size and the ending position grid size of the O-type grid normal grid edge are determined, and according to the coordinates of the grid topology control points on the airfoil, the coordinates of the grid topology control points on the outer boundary of the O-type grid and the number of grid points on the grid edge, the position distribution of the grid points on the O-type grid normal grid edge is obtained using a grid point distribution function, the grid point distribution function includes a hyperbolic distribution function but is not limited to this function method, and then the coordinates of the internal grid points are calculated by linear weighting of the endpoint coordinates to obtain the O-type grid normal edge data.

[0094] Specifically, the process of completing the construction of the O-type mesh normal mesh edge (17)-(20) is as follows: first, according to the needs of the airfoil flow simulation, determine the mesh size of the starting point of the normal mesh edge. If it is an inviscid Euler flow, the first layer of mesh height is set to 0.001 times the chord length. If it is a viscous flow, and according to the flow Reynolds number, the first layer of mesh height is determined according to the flat plate theory; then, according to the mesh size continuity constraint, determine the mesh size of the end point of the normal mesh edge; finally, based on the mesh size of the starting and ending positions, the number of mesh points on the mesh edge in the mesh topology, and the unit normal vector, use the mesh point distribution function to calculate the position distribution of the internal mesh points on the mesh edge. This embodiment adopts the most commonly used hyperbolic distribution method in mesh generation, but is not limited to this method to obtain the position distribution of the mesh points, and obtain the coordinates of the internal mesh points by linear weighting of the endpoint coordinates to obtain the O-type mesh normal mesh edge data. For example, the outermost mesh height of the mesh edge (17) is the same as the mesh size of the mesh edge (9) and the mesh edge (16) at the mesh topology control point 9. Finally, based on the grid sizes at the start and end positions and the number of grid points on the grid edge determined in step 7, the grid point distribution function is used to calculate the position distribution of the internal grid points on the grid edge (17)-(20). Here, the hyperbolic distribution method most commonly used in grid generation is used but not limited to this method to obtain the position distribution of the grid points, and the coordinates of the internal grid points are obtained by linearly weighting the endpoint coordinates.

[0095] Specifically, the process of constructing other mesh edges (21)-(40) is as follows: first, according to the mesh size continuity constraint and the far-field mesh size definition, determine the starting and ending mesh sizes of other mesh edges (21)-(40); then, based on the number of mesh points on the mesh edge in the mesh topology, the coordinates of the far-field mesh topology control points, and the coordinates of the mesh topology control points on the outer boundary of the O-shaped mesh, use the mesh point distribution function to calculate the position distribution of the internal mesh points on other mesh edges. This embodiment adopts the most commonly used hyperbolic distribution method in mesh generation, but is not limited to this method to obtain the position distribution of the internal mesh points; finally, the coordinates of the internal mesh points are obtained by linear or nonlinear interpolation of the coordinates of the mesh topology control points at the starting and ending positions of other mesh edges, thereby obtaining the data of other mesh edges in the mesh topology. In this example, for mesh edge (32), the mesh size at the starting position (mesh topology control point 12) is the same as the mesh size at the control point 12 position of mesh edge (11), mesh edge (12) and mesh edge (18), and the mesh size at the end position (control point 18) is selected to be 5 times the chord length. The definition process of mesh edges (24), (25), (26), (27), (33), (38), and (39) is the same as that of mesh edge (32). According to the mesh consistency constraint, the mesh sizes at both ends of mesh edges (21) and (28) are the same as those of mesh edge (24), mesh edges (23) and (30) are the same as those of mesh edge (25), mesh edge (31) is the same as mesh edge (32), mesh edge (34) is the same as mesh edge (33), mesh edge (37) is the same as mesh edge (38), mesh edge (40) is the same as mesh edge (39), mesh edge (35) is the same as mesh edge (12), mesh edge (36) is the same as mesh edge (16), the mesh size at the start position of mesh edge (22) is the same as the mesh size at the start position of mesh edge (11), and the mesh size at the end position is the same as the mesh size at the end position of mesh edge (9).

[0096] Step S16: construct each mesh surface using the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-type mesh, the normal mesh edge data of the O-type mesh, and other mesh edge data in the mesh topology, and automatically generate a multi-block structured mesh of the airfoil based on each mesh surface.

[0097] In this embodiment, mesh edge data on the airfoil, mesh edge data on the outer boundary of the O-type mesh, mesh normal edge data on the O-type mesh, and other mesh edge data in the mesh topology are utilized, and a preset algebraic interpolation method is adopted to construct each mesh surface; the preset algebraic interpolation method includes a transfinite interpolation method; the boundary type of the logical mesh edge of each mesh surface is determined according to the adjacent relationship between the control surfaces, and the mesh surfaces are associated and assembled to generate a multi-block structured grid of the airfoil.

[0098] In this embodiment, the coordinates of the grid points in the grid surface are calculated to complete the construction of the grid surface [1]-

[12] : the grid edge data on the airfoil, the grid edge data on the outer boundary of the O-type grid, the normal grid edge data of the O-type grid, and other grid edge data in the grid topology are used to assemble four logical grid edges in the grid surface, and then based on the data of the four logical grid edges, the coordinates of the internal grid points in the grid surface are calculated using a preset algebraic interpolation method, such as TFI (Transfinite Interpolation, transfinite interpolation method), and then the boundary type of the logical grid edge of each grid surface is determined according to the adjacent relationship between the grid surfaces, so as to realize the association and assembly between the data of different grid surfaces, and output the overall airfoil flow field calculation multi-block structured grid. For example, for the mesh surface [6], mesh edges (11), (10), and (9) form the logical edge of the mesh surface j0 position, mesh edge (22) forms the logical edge of the mesh surface j1 position, mesh edge (32) forms the logical edge of the mesh surface i0 position, and mesh edge (33) forms the logical edge of the mesh surface i1 position. The mesh of the mesh surface is generated based on TFI through the grid point coordinates of the four logical edges, and the data of the mesh surfaces [1]-

[12] are assembled to obtain the multi-block structured grid of the airfoil. According to the adjacent relationship between the mesh surfaces [1]-

[12] , the boundary type of the logical mesh edge of each mesh surface is determined, and then defined by numbering to achieve the association and assembly between the data of different mesh surfaces, and the overall multi-block structured grid of the airfoil flow field calculation is output. Figure 7 Automatic mesh generation for NACA0012 airfoil (global view), Figure 8 Automatic mesh generation for NACA0012 airfoil (leading edge view), Fig. 9 Automatic mesh generation for NACA0012 airfoil (trailing edge view). Figure 7 , Figure 8 , Fig. 9 The effect diagram of automatic generation of computational grid for NACA0012 airfoil is shown.

[0099] The specific process of realizing automatic generation of multi-block structured grid topology of airfoil in this application is as follows: Fig.10As shown, first determine the structured grid topology type of the airfoil, and establish a geometric parameterized model of the airfoil; then calculate the grid topology control points on the airfoil based on the structured grid topology type and the geometric parameterized model, and calculate the unit normal vector of the grid topology control points on the airfoil according to the coordinates of the grid topology control points on the airfoil; then calculate the coordinates of the outer boundary grid topology control points of the O-type grid according to the unit normal vector, and determine the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology; then determine the starting position grid size and the ending position grid size of the grid edge on the airfoil, determine the position distribution of the internal grid points of the grid edge on the airfoil according to the grid topology control point coordinates and the number of grid points and using the grid point distribution function, and calculate the grid edge data on the airfoil using the geometric parameterized model; then the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the other grid points in the grid topology. The starting position grid size and the ending position grid size of other grid edges are calculated based on the grid edge data on the airfoil, the grid topology control point coordinates on the airfoil, the grid topology control point coordinates of the outer boundary grid topology control points of the O-type grid, the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology. The grid point distribution function is used and a linear interpolation method or a nonlinear interpolation method is used to respectively calculate the outer boundary grid edge data of the O-type grid, the normal grid edge data of the O-type grid, and the other grid edge data in the grid topology. Finally, each grid surface is constructed using the grid edge data on the airfoil, the outer boundary grid edge data of the O-type grid, the normal grid edge data of the O-type grid, and the other grid edge data in the grid topology, and a multi-block structured grid of the airfoil is automatically generated based on each grid surface.

[0100] In response to the problem that the generation of multi-block structured grids for airfoils requires manual intervention and is difficult to automate, this application proposes: to achieve automatic generation of multi-block structured grid topology for airfoils through finite parameter driving, and then determine the distribution parameters of the grid edges based on constraints such as the continuity of the grid size, the incremental ratio, and the similarity of the distribution of opposite edges. Finally, the block construction method is used to complete the construction of the surface grid, and the automatic generation of multi-block structured grids for airfoils is achieved through block assembly. Compared with the original manual segmentation method, this application can not only greatly improve the efficiency of the generation of multi-block structured grids for airfoils, provide support for the rapid selection and optimization of airfoils, but also achieve sparse and encrypted grids through parameterization, and support airfoil performance analysis at different grid resolutions.

[0101] In this embodiment, the structured grid topology type of the airfoil is determined, and a geometric parameterized model of the airfoil is established according to the pre-acquired airfoil geometric data; the coordinates of the grid topology control points on the airfoil are calculated based on the structured grid topology type and the geometric parameterized model, and the unit normal vectors of the grid topology control points on the airfoil are calculated according to the coordinates of the grid topology control points on the airfoil; the coordinates of the grid topology control points on the outer boundary of the O-type grid are calculated according to the unit normal vector, and the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology are determined; the starting position grid size and the ending position grid size of the grid edge on the airfoil are determined, according to the coordinates of the grid topology control points on the airfoil, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the grid edge on the airfoil, and the position distribution of the internal grid points of the grid edge on the airfoil is determined using the grid point distribution function, and the grid edge data on the airfoil is calculated using the geometric parameterized model and the position distribution of the internal grid points of the grid edge on the airfoil; the grid point distribution function includes a hyperbolic distribution function; the starting position grid size of the outer boundary grid edge of the O-type grid is determined with and the grid size at the starting position and the ending position, the grid size at the starting position and the ending position of the normal grid edge of the O-type grid, and the grid size at the starting position and the ending position of other grid edges in the grid topology; based on the grid edge data on the airfoil, the coordinates of the grid topology control points on the airfoil, the coordinates of the outer boundary grid topology control points of the O-type grid, the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, the grid size at the starting position and the ending position of the outer boundary grid edge of the O-type grid, the grid size at the starting position and the ending position of the normal grid edge of the O-type grid, and the grid size at the starting position and the ending position of other grid edges in the grid topology, the grid point distribution function is used and a linear interpolation method or a nonlinear interpolation method is used to respectively calculate the outer boundary grid edge data of the O-type grid, the normal grid edge data of the O-type grid, and the other grid edge data in the grid topology; each grid surface is constructed using the grid edge data on the airfoil, the outer boundary grid edge data of the O-type grid, the normal grid edge data of the O-type grid, and the other grid edge data in the grid topology, and a multi-block structured grid of the airfoil is automatically generated based on each of the grid surfaces.The present application establishes a geometric parameterized model of the airfoil based on pre-acquired airfoil geometry data, calculates the coordinates of the grid topology control points on the airfoil using the structured grid topology type and the geometric parameterized model, calculates the unit normal vectors of the grid topology control points on the airfoil based on the coordinates of the grid topology control points on the airfoil, calculates the coordinates of the grid topology control points on the outer boundary of the O-type grid, determines the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, determines the starting position grid size and the ending position grid size of the grid edge on the airfoil, calculates the grid edge data on the airfoil, and then determines the starting position grid size and the ending position grid size of the grid edge on the outer boundary of the O-type grid, and the starting position of the normal grid edge of the O-type grid The grid size and the grid size at the end position, the grid size at the starting position and the grid size at the end position of other grid edges in the grid topology are used to calculate the grid edge data of the outer boundary of the O-type grid, the normal grid edge data of the O-type grid and other grid edge data in the grid topology, and finally each grid surface is constructed, and the multi-block structured grid of the airfoil is automatically generated based on each grid surface. In view of the problem that the generation of multi-block structured grids of airfoils requires manual intervention and is difficult to automate, the present application can realize the automatic generation of multi-block structured grid topology of airfoils, and compared with the original manual segmentation method, it can greatly improve the efficiency of the generation of multi-block structured grids of airfoils, provide support for rapid selection and optimization of airfoils, and support airfoil performance analysis at different grid resolutions.

[0102] See also Fig.11 As shown, the embodiment of the present invention discloses an automatic generation device for a multi-block structured grid of an airfoil, which may specifically include:

[0103] A model building module 11 is used to determine the structured grid topology type of the airfoil and to build a geometric parameterized model of the airfoil according to the pre-acquired airfoil geometric data;

[0104] A unit normal vector calculation module 12, used to calculate the coordinates of the grid topology control points on the airfoil based on the structured grid topology type and the geometric parameterized model, and calculate the unit normal vectors of the grid topology control points on the airfoil according to the coordinates of the grid topology control points on the airfoil;

[0105] A control point coordinate calculation module 13 is used to calculate the coordinates of the outer boundary grid topology control points of the O-shaped grid according to the unit normal vector, and determine the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology;

[0106] The airfoil mesh edge data calculation module 14 is used to determine the starting position mesh size and the ending position mesh size of the airfoil mesh edge, according to the mesh topology control point coordinates on the airfoil, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size and the ending position mesh size of the airfoil mesh edge, and the position distribution of the internal mesh points of the airfoil mesh edge is determined by using the grid point distribution function, and the airfoil mesh edge data is calculated by using the geometric parameterized model and the position distribution of the internal mesh points of the airfoil mesh edge; the grid point distribution function includes a hyperbolic distribution function;

[0107] An O-type and other grid edge data calculation module 15 is used to determine the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, and based on the grid edge data on the airfoil, the coordinates of the grid topology control points on the airfoil, the coordinates of the outer boundary grid topology control points of the O-type grid, the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, and respectively calculate the O-type grid outer boundary grid edge data, the O-type grid normal grid edge data, and the other grid edge data in the grid topology by using a grid point distribution function and adopting a linear interpolation method or a nonlinear interpolation method;

[0108] The automatic mesh generation module 16 is used to construct each mesh surface using the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-type mesh, the normal mesh edge data of the O-type mesh and other mesh edge data in the mesh topology, and automatically generate a multi-block structured mesh of the airfoil based on each of the mesh surfaces.

[0109] In this embodiment, the structured grid topology type of the airfoil is determined, and a geometric parameterized model of the airfoil is established according to the pre-acquired airfoil geometric data; the coordinates of the grid topology control points on the airfoil are calculated based on the structured grid topology type and the geometric parameterized model, and the unit normal vectors of the grid topology control points on the airfoil are calculated according to the coordinates of the grid topology control points on the airfoil; the coordinates of the grid topology control points on the outer boundary of the O-type grid are calculated according to the unit normal vector, and the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology are determined; the starting position grid size and the ending position grid size of the grid edge on the airfoil are determined, according to the coordinates of the grid topology control points on the airfoil, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the grid edge on the airfoil, and the position distribution of the internal grid points of the grid edge on the airfoil is determined using the grid point distribution function, and the grid edge data on the airfoil is calculated using the geometric parameterized model and the position distribution of the internal grid points of the grid edge on the airfoil; the grid point distribution function includes a hyperbolic distribution function; the starting position grid size of the outer boundary grid edge of the O-type grid is determined with and the grid size at the starting position and the ending position, the grid size at the starting position and the ending position of the normal grid edge of the O-type grid, and the grid size at the starting position and the ending position of other grid edges in the grid topology; based on the grid edge data on the airfoil, the coordinates of the grid topology control points on the airfoil, the coordinates of the outer boundary grid topology control points of the O-type grid, the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, the grid size at the starting position and the ending position of the outer boundary grid edge of the O-type grid, the grid size at the starting position and the ending position of the normal grid edge of the O-type grid, and the grid size at the starting position and the ending position of other grid edges in the grid topology, the grid point distribution function is used and a linear interpolation method or a nonlinear interpolation method is used to respectively calculate the outer boundary grid edge data of the O-type grid, the normal grid edge data of the O-type grid, and the other grid edge data in the grid topology; each grid surface is constructed using the grid edge data on the airfoil, the outer boundary grid edge data of the O-type grid, the normal grid edge data of the O-type grid, and the other grid edge data in the grid topology, and a multi-block structured grid of the airfoil is automatically generated based on each of the grid surfaces.The present application establishes a geometric parameterized model of the airfoil based on pre-acquired airfoil geometry data, calculates the coordinates of the grid topology control points on the airfoil using the structured grid topology type and the geometric parameterized model, calculates the unit normal vectors of the grid topology control points on the airfoil based on the coordinates of the grid topology control points on the airfoil, calculates the coordinates of the grid topology control points on the outer boundary of the O-type grid, determines the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, determines the starting position grid size and the ending position grid size of the grid edge on the airfoil, calculates the grid edge data on the airfoil, and then determines the starting position grid size and the ending position grid size of the grid edge on the outer boundary of the O-type grid, and the starting position of the normal grid edge of the O-type grid The grid size and the grid size at the end position, the grid size at the starting position and the grid size at the end position of other grid edges in the grid topology are used to calculate the grid edge data of the outer boundary of the O-type grid, the normal grid edge data of the O-type grid and other grid edge data in the grid topology, and finally each grid surface is constructed, and the multi-block structured grid of the airfoil is automatically generated based on each grid surface. In view of the problem that the generation of multi-block structured grids of airfoils requires manual intervention and is difficult to automate, the present application can realize the automatic generation of multi-block structured grid topology of airfoils, and compared with the original manual segmentation method, it can greatly improve the efficiency of the generation of multi-block structured grids of airfoils, provide support for rapid selection and optimization of airfoils, and support airfoil performance analysis at different grid resolutions.

[0110] In some specific embodiments, the model building module 11 may specifically include:

[0111] A mesh topology type screening module is used to screen out the structured mesh topology type of the airfoil according to the airfoil type and airfoil shape, and in combination with the airfoil flow numerical simulation requirements;

[0112] The quantity and relationship determination module is used to determine the number of control points, the number of control edges, the number of control surfaces, the connection relationship between control points, the sharing relationship between control edges, and the adjacent relationship between control surfaces in the grid topology.

[0113] In some specific embodiments, the model building module 11 may specifically include:

[0114] A Euclidean distance calculation module, used for calculating the Euclidean distance between adjacent geometric shape description points according to the coordinates of the geometric shape description points of the airfoil surface in the pre-acquired airfoil geometric data, and accumulating the Euclidean distances to obtain the curvilinear distance between each geometric shape description point on the airfoil surface and the trailing edge point on the upper surface of the airfoil;

[0115] The model building module is used to describe the point coordinates and the curve distance based on the geometric shape of the airfoil surface and to build a geometric parameterized model of the airfoil using an interpolation method.

[0116] In some specific embodiments, the unit normal vector calculation module 12 may specifically include:

[0117] A neighboring point coordinate calculation module is used to calculate the neighboring point position information adjacent to the grid topology control point on the airfoil according to the grid topology control point coordinates on the airfoil, and calculate the neighboring point position information using a geometric parameterized model to obtain the neighboring point coordinates;

[0118] The vector normalization module is used to calculate the normal vector of the grid topology control point on the airfoil based on the coordinates of the neighboring points, and to perform vector normalization on the normal vector to obtain a unit normal vector.

[0119] In some specific embodiments, the control point coordinate calculation module 13 may specifically include:

[0120] The control point coordinate calculation module is used to calculate the coordinates of the topological control points of the outer boundary grid of the O-shaped grid according to the unit normal vector and using the coordinate calculation formula; the coordinate calculation formula is:

[0121] ;

[0122] ;

[0123] in, is the coordinate of the topological control point of the outer boundary grid of the O-type grid, are the coordinates of the mesh topology control points on the airfoil, is the O-grid advancement distance, is the unit normal vector and c is the chord length of the airfoil.

[0124] In some specific embodiments, the O-type and other mesh edge data calculation module 15 may specifically include:

[0125] An outer boundary mesh edge data calculation module is used to calculate the outer boundary mesh edge data of the O-type mesh based on the mesh edge data on the airfoil, the coordinates of the mesh topology control points on the airfoil, the coordinates of the outer boundary mesh topology control points of the O-type mesh, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size of the outer boundary mesh edge of the O-type mesh, and the ending position mesh size, using a mesh point distribution function and a nonlinear interpolation method;

[0126] A normal mesh edge data calculation module is used to calculate the O-type mesh normal mesh edge data based on the mesh topology control point coordinates on the airfoil, the mesh topology control point coordinates of the outer boundary of the O-type mesh, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size of the O-type mesh normal mesh edge, and the ending position mesh size, using a mesh point distribution function and a linear interpolation method;

[0127] Other mesh edge data calculation module is used to calculate other mesh edge data in the mesh topology based on the coordinates of the far-field mesh topology control points, the coordinates of the mesh topology control points on the outer boundary of the O-type mesh, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size of other mesh edges in the mesh topology, and the ending position mesh size, using the mesh point distribution function and adopting linear interpolation or nonlinear interpolation method.

[0128] In some specific embodiments, the automatic grid generation module 16 may specifically include:

[0129] A mesh surface construction module, for constructing each mesh surface by using mesh edge data on the airfoil, mesh edge data on the outer boundary of the O-shaped mesh, mesh edge data on the normal direction of the O-shaped mesh, and other mesh edge data in the mesh topology, and adopting a preset algebraic interpolation method; the preset algebraic interpolation method includes a transfinite interpolation method;

[0130] The structured grid generation module is used to determine the boundary type of the logical grid edge of each grid surface according to the adjacent relationship between the control surfaces, and associate and assemble the grid surfaces to generate a multi-block structured grid of the airfoil.

[0131] Fig.12 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application. The electronic device 20 may specifically include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 is used to store a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the method for automatically generating a multi-block structured grid of an airfoil executed by an electronic device disclosed in any of the aforementioned embodiments.

[0132] In this embodiment, the power supply 23 is used to provide working voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and the external device, and the communication protocol it follows is any communication protocol that can be applied to the technical solution of the present application, and is not specifically limited here; the input and output interface 25 is used to obtain external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs and is not specifically limited here.

[0133] In addition, the memory 22, as a carrier for storing resources, can be a read-only memory, a random access memory, a disk or an optical disk, etc. The resources stored thereon include an operating system 221, a computer program 222 and data 223, etc. The storage method can be temporary storage or permanent storage.

[0134] Among them, the operating system 221 is used to manage and control the hardware devices and computer programs 222 on the electronic device 20 to realize the operation and processing of the data 223 in the memory 22 by the processor 21, which can be Windows, Unix, Linux, etc. In addition to including a computer program that can be used to complete the method for automatically generating a multi-block structured grid of an airfoil executed by the electronic device 20 disclosed in any of the aforementioned embodiments, the computer program 222 can further include a computer program that can be used to complete other specific tasks. In addition to including data transmitted from an external device received by the automatic generation device of a multi-block structured grid of an airfoil, the data 223 can also include data collected by its own input and output interface 25, etc.

[0135] The steps of the method or algorithm described in conjunction with the embodiments disclosed herein may be implemented directly using hardware, a software module executed by a processor, or a combination of the two. The software module may be placed in a random access memory (RAM), a memory, a read-only memory (ROM), an electrically programmable ROM, an electrically erasable programmable ROM, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.

[0136] Furthermore, an embodiment of the present application also discloses a computer-readable storage medium, in which a computer program is stored. When the computer program is loaded and executed by a processor, the steps of the method for automatically generating a multi-block structured grid for an airfoil disclosed in any of the aforementioned embodiments are implemented.

[0137] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0138] The above is a detailed introduction to the method, device, equipment and storage medium for automatically generating a multi-block structured grid of an airfoil provided by the present invention. Specific examples are used in this article to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation method and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.

Claims

1. A method for automatically generating multi-block structured grids for airfoils, characterized in that: include: Determine the structured grid topology type of the airfoil, and establish a geometric parameterized model of the airfoil based on pre-acquired airfoil geometry data; Calculating the coordinates of the grid topology control points on the airfoil based on the structured grid topology type and the geometric parameterized model, and calculating the unit normal vectors of the grid topology control points on the airfoil according to the coordinates of the grid topology control points on the airfoil; Calculating the coordinates of the outer boundary grid topology control points of the O-shaped grid according to the unit normal vector, and determining the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology; Determine the grid size of the starting position and the grid size of the ending position of the grid edge on the airfoil, according to the coordinates of the grid topology control point on the airfoil, the number of grid points on the grid edge in the grid topology, the grid size of the starting position and the grid size of the ending position of the grid edge on the airfoil, and use the grid point distribution function to determine the position distribution of the internal grid points of the grid edge on the airfoil, and calculate the grid edge data on the airfoil using the geometric parameterized model and the position distribution of the internal grid points of the grid edge on the airfoil; the grid point distribution function includes a hyperbolic distribution function; Determine the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, and calculate the O-type grid outer boundary grid edge data, the O-type grid normal grid edge data, and the other grid edge data in the grid topology based on the grid edge data on the airfoil, the grid topology control point coordinates on the airfoil, the O-type grid outer boundary grid topology control point coordinates, the far-field grid topology control point coordinates, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology by using a grid point distribution function and adopting a linear interpolation method or a nonlinear interpolation method; Utilizing the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-shaped mesh, the normal mesh edge data of the O-shaped mesh, and other mesh edge data in the mesh topology to construct each mesh surface, and automatically generating a multi-block structured mesh of the airfoil based on each mesh surface; Among them, the method of establishing a geometric parameterized model of the airfoil based on the pre-acquired airfoil geometric data includes: calculating the Euclidean distance between adjacent geometric shape description points based on the coordinates of the geometric shape description points of the airfoil surface in the pre-acquired airfoil geometric data, and accumulating the Euclidean distances to obtain the curvilinear distance between the geometric shape description point of each airfoil surface and the trailing edge point of the airfoil upper surface; based on the coordinates of the geometric shape description points of the airfoil surface and the curvilinear distances, the geometric parameterized model of the airfoil is established using an interpolation method.

2. The method for automatically generating multi-block structured grids for airfoils according to claim 1, characterized in that: The determining of the structured grid topology type of the airfoil includes: According to the airfoil type and shape, and combined with the requirements of airfoil flow numerical simulation, the structured grid topology type of the airfoil is selected; Determine the number of control points, the number of control edges, the number of control surfaces, the connection relationship between control points, the sharing relationship between control edges, and the adjacent relationship between control surfaces in the mesh topology.

3. The method for automatically generating multi-block structured grids for airfoils according to claim 1, characterized in that: The step of calculating the unit normal vector of the grid topology control point on the airfoil according to the coordinates of the grid topology control point on the airfoil comprises: According to the coordinates of the grid topology control point on the airfoil, position information of adjacent points adjacent to the grid topology control point on the airfoil is calculated, and the position information of the adjacent points is calculated using a geometric parameterized model to obtain the coordinates of the adjacent points; The normal vector of the grid topology control point on the airfoil is calculated based on the coordinates of the neighboring points, and the normal vector is normalized to obtain a unit normal vector.

4. The method for automatically generating multi-block structured grids for airfoils according to claim 1, characterized in that: The step of calculating the coordinates of the outer boundary grid topology control points of the O-shaped grid according to the unit normal vector comprises: The coordinates of the topological control points of the outer boundary grid of the O-shaped grid are calculated according to the unit normal vector using a coordinate calculation formula; the coordinate calculation formula is: ； ； in, is the coordinate of the topological control point of the outer boundary grid of the O-type grid, are the coordinates of the mesh topology control points on the airfoil, is the O-grid advancement distance, is the unit normal vector and c is the chord length of the airfoil.

5. The method for automatically generating multi-block structured grids for airfoils according to claim 1, characterized in that: Based on the mesh edge data on the airfoil, the mesh topology control point coordinates on the airfoil, the mesh topology control point coordinates of the outer boundary of the O-type mesh, the mesh topology control point coordinates of the far-field mesh, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size and the ending position mesh size of the outer boundary mesh edge of the O-type mesh, the starting position mesh size and the ending position mesh size of the normal mesh edge of the O-type mesh, and the starting position mesh size and the ending position mesh size of other mesh edges in the mesh topology, the mesh point distribution function is used and a linear interpolation method or a nonlinear interpolation method is used to respectively calculate the mesh edge data of the outer boundary of the O-type mesh, the mesh edge data of the normal mesh of the O-type mesh, and other mesh edge data in the mesh topology, including: Based on the mesh edge data on the airfoil, the mesh topology control point coordinates on the airfoil, the mesh topology control point coordinates on the outer boundary of the O-type mesh, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size of the outer boundary mesh edge of the O-type mesh, and the ending position mesh size, the mesh point distribution function is used and the nonlinear interpolation method is used to calculate the mesh edge data of the outer boundary of the O-type mesh; Based on the grid topology control point coordinates on the airfoil, the grid topology control point coordinates of the outer boundary of the O-shaped grid, the number of grid points on the grid edge in the grid topology, the starting position grid size of the O-shaped grid normal grid edge, and the ending position grid size, the grid point distribution function is used and the linear interpolation method is used to calculate the O-shaped grid normal grid edge data; Based on the coordinates of the far-field grid topology control points, the coordinates of the grid topology control points on the outer boundary of the O-shaped grid, the number of grid points on the grid edge in the grid topology, the starting position grid size of other grid edges in the grid topology, and the ending position grid size, the grid point distribution function is used and linear interpolation or nonlinear interpolation is used to calculate other grid edge data in the grid topology.

6. The method for automatically generating multi-block structured grids for airfoils according to any one of claims 1 to 5, characterized in that: The method of constructing each mesh surface by using the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-shaped mesh, the normal mesh edge data of the O-shaped mesh, and other mesh edge data in the mesh topology, and automatically generating a multi-block structured mesh of the airfoil based on each mesh surface, includes: Using the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-shaped mesh, the mesh edge data on the normal direction of the O-shaped mesh, and other mesh edge data in the mesh topology, and using a preset algebraic interpolation method to construct each mesh surface; the preset algebraic interpolation method includes a transfinite interpolation method; The boundary type of the logical grid edge of each grid surface is determined according to the adjacent relationship between the control surfaces, and the grid surfaces are associated and assembled to generate a multi-block structured grid of the airfoil.

7. An automatic generation device for multi-block structured grid of airfoil, characterized in that: include: A model building module, used for determining a structured grid topology type of the airfoil and building a geometric parameterized model of the airfoil according to pre-acquired airfoil geometric data; A unit normal vector calculation module, used to calculate the coordinates of the grid topology control points on the airfoil based on the structured grid topology type and the geometric parameterized model, and calculate the unit normal vectors of the grid topology control points on the airfoil according to the coordinates of the grid topology control points on the airfoil; A control point coordinate calculation module, used to calculate the coordinates of the outer boundary grid topology control points of the O-shaped grid according to the unit normal vector, and determine the coordinates of the far-field grid topology control points and the number of grid points on the grid edge in the grid topology; The airfoil mesh edge data calculation module is used to determine the starting position mesh size and the ending position mesh size of the airfoil mesh edge, according to the mesh topology control point coordinates on the airfoil, the number of mesh points on the mesh edge in the mesh topology, the starting position mesh size and the ending position mesh size of the airfoil mesh edge, and the position distribution of the internal mesh points of the airfoil mesh edge is determined by using the grid point distribution function, and the airfoil mesh edge data is calculated by using the geometric parameterized model and the position distribution of the internal mesh points of the airfoil mesh edge; the grid point distribution function includes a hyperbolic distribution function; an O-type and other grid edge data calculation module, for determining the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, and based on the grid edge data on the airfoil, the coordinates of the grid topology control points on the airfoil, the coordinates of the outer boundary grid topology control points of the O-type grid, the coordinates of the far-field grid topology control points, the number of grid points on the grid edge in the grid topology, the starting position grid size and the ending position grid size of the outer boundary grid edge of the O-type grid, the starting position grid size and the ending position grid size of the normal grid edge of the O-type grid, and the starting position grid size and the ending position grid size of other grid edges in the grid topology, and respectively calculating the O-type grid outer boundary grid edge data, the O-type grid normal grid edge data, and the other grid edge data in the grid topology by using a grid point distribution function and adopting a linear interpolation method or a nonlinear interpolation method; A mesh automatic generation module, used to construct each mesh surface by using the mesh edge data on the airfoil, the mesh edge data on the outer boundary of the O-shaped mesh, the normal mesh edge data of the O-shaped mesh, and other mesh edge data in the mesh topology, and automatically generate a multi-block structured mesh of the airfoil based on each of the mesh surfaces; Among them, the method of establishing a geometric parameterized model of the airfoil based on the pre-acquired airfoil geometric data includes: calculating the Euclidean distance between adjacent geometric shape description points based on the coordinates of the geometric shape description points of the airfoil surface in the pre-acquired airfoil geometric data, and accumulating the Euclidean distances to obtain the curvilinear distance between the geometric shape description point of each airfoil surface and the trailing edge point of the airfoil upper surface; based on the coordinates of the geometric shape description points of the airfoil surface and the curvilinear distances, the geometric parameterized model of the airfoil is established using an interpolation method.

8. An electronic device, characterized in that: include: Memory, used to store computer programs; A processor is used to execute the computer program to implement the method for automatically generating a multi-block structured grid for an airfoil as claimed in any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that: Used to store a computer program; wherein, when the computer program is executed by a processor, the method for automatically generating a multi-block structured grid for an airfoil as described in any one of claims 1 to 6 is implemented.

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