Design method, device, medium and product of an axisymmetric wind tunnel nozzle

Abstract

The application provides a design method, equipment, medium and product of an axisymmetric wind tunnel nozzle. A ray method in aerodynamic acoustics is introduced, and a nozzle optimization design method based on the ray method and computational fluid dynamics is provided. The basic idea is to establish the connection between the nozzle expansion area and the wave cancellation area by using the ray, so that the optimal nozzle profile is obtained by iterative optimization with small calculation cost and on the basis of considering the boundary layer. The evolution of the nozzle profile is gradually guided by the path of the ray tracing, and a high-performance point meeting the requirements is found, so that the dimension disaster problem of the conventional optimization method is avoided.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, and in particular to a design method, device, medium and product of an axisymmetric wind tunnel nozzle. BACKGROUND

[0002] In the field of aerospace, rail transportation, etc., wind tunnels are often used for various aircraft experiments and measurements to obtain information related to aircraft, such as lift, drag and moment, to verify the correctness of the design method and test the reliability of the numerical simulation results. In the wind tunnel, the nozzle is one of the most important components, which realizes flow acceleration through uniform changes in cross-sectional area to provide uniform airflow for the test section.

[0003] Current wind tunnel nozzle design mainly adopts two types of technologies: optimization method and characteristic line method. The optimization method iteratively optimizes specific geometric parameters through numerical calculation, which has the advantage of directional improvement of the objective function, but has a significant curse of dimensionality problem, that is, with the increase of design variables, the optimization process needs to consume a geometrically increasing amount of computing resources to obtain a convergent solution. In addition, the optimization method may have the following shortcomings: 1. The parameterized geometry may not perfectly cover the optimal solution; 2. The truncation error caused by the discontinuous flow such as shock wave in the numerical calculation process can easily lead to gradient evaluation distortion, making the optimization result deviate from the optimal solution; 3. Improper geometric deformation can mislead the optimization direction.

[0004] In contrast, the characteristic line method is based on the small perturbation theory of aerodynamics, which has the advantages of clear physical model and simple calculation process, and neither needs to construct a complex parameterized geometric model nor avoids the grid transformation process in numerical calculation. However, the characteristic line method is only suitable for supersonic flow and cannot consider the influence of the wall boundary layer. SUMMARY

[0005] The present application provides a design method, device, medium and product of an axisymmetric wind tunnel nozzle, which can solve one of the problems in the background art.

[0006] To achieve the above-mentioned purpose, the present application adopts the following technical solutions:

[0007] In a first aspect, a design method of a two-dimensional axisymmetric wind tunnel nozzle is provided, comprising:

[0008] Based on the known nozzle design parameters, an initial nozzle profile with smooth curvature and gradual expansion is prepared;

[0009] Determine the starting point of the expansion wave on the initial nozzle profile and the initial ray vector determined from the starting point to the nozzle symmetry axis direction;

[0010] Based on the relationship between local airflow velocity, sound speed, ray vector, and ray trajectory, the initial ray trajectory of the initial ray vector is determined step by step over time, and the subsequent ray vector and its subsequent ray trajectory are also determined. The ray trajectory includes an expansion zone trajectory and a wave-dissipating zone trajectory, and the ray is reflected at the position of the axis of symmetry.

[0011] Record the first intersection point formed when the ray intersects the initial nozzle profile before reflection, and the second intersection point formed when the ray intersects the initial nozzle profile after reflection;

[0012] The expansion angle is determined by the first intersection points of each pair of adjacent points, and the wave-damping angle is determined by the second intersection points of each pair of adjacent points;

[0013] When the expansion angle and the wave-damping angle corresponding to the two rays before and after the time sequence are different, adjust the line segment of the initial nozzle profile corresponding to the expansion angle or the wave-damping angle; and

[0014] Based on the adjusted results, the final nozzle profile is generated.

[0015] Based on the above technical solutions, the ray method from aeroacoustics is introduced, and a nozzle optimization design method based on the ray method and computational fluid dynamics is proposed. Its basic idea is to establish the connection between the nozzle expansion region and the wave-absorbing region using rays. Thus, with a relatively low computational cost and considering the boundary layer, a better nozzle profile is obtained through iterative optimization. Furthermore, the evolution of the nozzle profile is gradually guided by the ray tracing path to find the high-performance point that meets the requirements, thus avoiding the dimensionality curse problem of conventional optimization methods.

[0016] In one possible design approach of the first aspect, determining the starting point of the expansion wave and the initial ray vector from the starting point towards the nozzle symmetry axis along the initial nozzle profile specifically includes:

[0017] The internal flow field of the nozzle is obtained based on computational fluid dynamics methods.

[0018] Using the nozzle inlet as the pressure inlet and the nozzle outlet as the pressure outlet, a post-processing program is used to process the pressure distribution in the flow field inside the nozzle to obtain pressure contour lines.

[0019] The pressure contour lines were fitted using a linear fitting method to obtain the contour line equations;

[0020] The starting point and the initial ray vector are determined by the contour equation and the initial nozzle profile.

[0021] In one possible design approach of the first aspect, the relationship between local airflow velocity, sound speed, ray vector, and ray trajectory is as follows:

[0022]

[0023]

[0024]

[0025] wherein, is a ray trajectory, subscript p is a ray used to represent a diverging wave, subscripts i and j represent directions along x and y, s is a ray vector, V is a local velocity, n is an initial vector of a ray without flow deflection, and c is a sound speed.

[0026] In a possible design of the first aspect, the divergence angle is determined by two adjacent first intersection points, and the wave cancellation angle is determined by two adjacent second intersection points, specifically:

[0027] An angle between a straight line determined by two adjacent intersection points and a tangent line corresponding to a time-sequentially preceding intersection point on the initial nozzle profile is taken as the divergence angle or the wave cancellation angle.

[0028] In a possible design of the first aspect, a line segment of the initial nozzle profile corresponding to the divergence angle or the wave cancellation angle is adjusted, specifically:

[0029] The line segment is adjusted to rotate around a corresponding intersection point by a specified angle, and the specified angle is half of an angle difference between the divergence angle and the wave cancellation angle corresponding to two rays in time sequence.

[0030] In a possible design of the first aspect, based on an adjusted result, a final nozzle profile is generated, specifically:

[0031] The adjusted profile discrete points are fitted using a polynomial to obtain a smooth final nozzle profile.

[0032] In a second aspect, a design method of a three-dimensional axisymmetric wind tunnel nozzle is provided, including:

[0033] Based on known nozzle design parameters, an initial nozzle profile with smooth curvature and gradual expansion is prepared in a lofting manner;

[0034] A linear fitting is performed on the initial nozzle profile in a three-dimensional space to obtain a fitting model, a starting point of a diverging wave is determined on the fitting model, and an initial ray vector is determined from the starting point to a nozzle symmetry axis direction;

[0035] Based on the relationship between local airflow velocity, sound speed, ray vector, and ray trajectory, the initial ray trajectory of the initial ray vector is determined step by step over time, and the subsequent ray vector and its subsequent ray trajectory are also determined. The ray trajectory includes an expansion zone trajectory and a wave-dissipating zone trajectory, and the ray is reflected at the position of the axis of symmetry.

[0036] Record the first intersection point generated when the ray intersects the fitted model before reflection, and the second intersection point generated when the ray intersects the fitted model after reflection;

[0037] The expansion angle is determined by the first intersection points of each pair of adjacent points, and the wave-damping angle is determined by the second intersection points of each pair of adjacent points;

[0038] When the expansion angle and the wave-damping angle corresponding to the two rays before and after the time sequence are different, adjust the wall surface of the fitted model corresponding to the expansion angle or the wave-damping angle; and

[0039] Based on the adjusted results, the final nozzle profile is generated.

[0040] Thirdly, an electronic device is provided, comprising: a processor, and a memory coupled to the processor, the memory for storing a computer program; the processor for executing the computer program stored in the memory such that the electronic device performs a design method for a two-dimensional axisymmetric wind tunnel nozzle as in any possible implementation of the first aspect, or performs a design method for a three-dimensional axisymmetric wind tunnel nozzle as in the second aspect.

[0041] Fourthly, a computer-readable storage medium is provided, including a computer program or instructions that, when executed on a computer, cause the computer to perform the design method for a two-dimensional axisymmetric wind tunnel nozzle as described in any possible implementation of the first aspect, or to perform the design method for a three-dimensional axisymmetric wind tunnel nozzle as described in the second aspect.

[0042] Fifthly, a computer program product is provided, comprising: a computer program or instructions that, when executed on a computer, cause the computer to perform the design method for a two-dimensional axisymmetric wind tunnel nozzle as described in any possible implementation of the first aspect, or to perform the design method for a three-dimensional axisymmetric wind tunnel nozzle as described in the second aspect. Attached Figure Description

[0043] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the accompanying drawings needed to be used in the embodiments or the related description will be briefly introduced. Obviously, the accompanying drawings in the following description only show some embodiments of the present application, and other accompanying drawings can be obtained by those of ordinary skill in the art without any creative effort.

[0044] Figure 1 A flow chart of the nozzle design method in the embodiments of the present application;

[0045] Figure 2 A two-dimensional initial nozzle profile diagram in the embodiments of the present application;

[0046] Figure 3 A diagram of using ray matching expansion angle in the nozzle flow field in the embodiments of the present application, wherein, Figure 3 (a) represents the relationship among the initial vector n of the ray without deflection along the flow, the local velocity V and the ray vector s, Figure 3 (b) represents the trajectory of the ray gradually deflected along the flow inside the nozzle;

[0047] Figure 4 A trajectory step diagram of the ray in the nozzle flow field in the embodiments of the present application, wherein, Figure 4 (a) represents the trajectory of the ray in the nozzle flow field emitted at different positions, Figure 4 (b) represents the intersection of the ray without intersection with the nozzle wave absorbing zone wall surface and the extension line of the nozzle profile;

[0048] Figure 5 A diagram of iteratively changing the nozzle geometry based on the ray method and the computational fluid dynamics method in the embodiments of the present application, wherein, Figure 5 (a) represents obtaining the angle information of the ray based on the two-dimensional nozzle flow field by using the ray method, Figure 5 (b) represents deflecting the nozzle wave absorbing zone wall surface through the angle information, Figure 5 (c) represents translating the deflected wall surface, Figure 5 (d) represents fitting the translated wall surface using a smooth curve, Figure 5 (e) represents the nozzle wall surface after iterative convergence;

[0049] Figure 6 A three-dimensional initial nozzle profile diagram in the embodiments of the present application, wherein, Figure 6 (a) represents obtaining the angle information of the ray based on the three-dimensional nozzle flow field by using the ray method, Figure 6 (b) represents deflecting the point on the current section, Figure 6 (c) represents deflecting the point on the subsequent section;

[0050] Figure 7A schematic diagram of the nozzle geometry after iteration based on the ray method and the computational fluid dynamics method of the embodiments of the present application. DETAILED DESCRIPTION

[0051] In order to make the purposes, technical solutions and advantages of the present application clearer, the present application is further described in detail below in combination with the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and do not limit the present application.

[0052] It should be noted that although the functional modules are divided in the schematic diagram of the device, and the logical order is shown in the flowchart, in some cases, the steps shown or described can be performed in a manner different from the module division in the device or the order in the flowchart. The terms "first", "second", and the like in the specification and claims and the above drawings are used to distinguish similar objects, and do not necessarily describe a specific order or sequence.

[0053] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the present application belongs. The terms used herein are only for the purpose of describing the embodiments of the present application and are not intended to limit the present application.

[0054] As shown in the following, the introduction of the two-dimensional nozzle design process is made in combination with specific cases: Figure 1

[0055] This case selects the shortest nozzle with direct and rapid expansion at the nozzle inlet for display. The nozzle can uniformly convert the nozzle inlet airflow into horizontal airflow in a relatively short length. It is assumed that a user wants to use our method to design a nozzle to assist the design of a wind tunnel test section.

[0056] S1. The user can simply draw an initial nozzle profile according to the required nozzle length and height with a curve that is smooth and gradually expanding, as shown in Figure 2 The arrow on the left side represents the airflow at the nozzle inlet, which is discharged from the nozzle outlet after passing through the expanding nozzle. The flow lines inside the nozzle are obtained by the computational fluid dynamics method. The computational fluid dynamics method and its related grid generation, boundary setting and data post-processing can be automated by a batch program without manual clicking by the user.

[0057] S2. The initial expansion angle corresponding to the vector can be estimated by the basic expansion wave formula with the nozzle geometry, the nozzle inlet airflow speed and direction. After obtaining the pressure distribution inside the nozzle by the computational fluid dynamics method, the contour lines can be drawn, as shown in Figure 2 ​the dashed line in (a). The values of a and b are obtained by fitting the linear equation y = ax + b using the least square method. The intersection point (x0, y0) of the linear equation and the nozzle wall is also solved, which is the point on the nozzle satisfying y0 = ax0 + b. The intersection point (x0, y0) can be regarded as the starting point of the expansion wave, and the vector s corresponding to the expansion wave can be obtained by the slope a of the linear equation. Then, as shown in Figure 3 (a), the incident vector n of the ray is obtained by matching the expansion direction s according to the formula of the ray . In other words, the initial direction n of the ray, the local flow direction V and the expansion wave direction s form a velocity triangle.

[0058] S3. The trajectory of the ray in the nozzle is obtained using the ray method based on the incident vector n of the ray, the nozzle velocity and the sound speed distribution. Specifically, according to the incident vector n, the local flow velocity V and the sound speed c, the initial ray vector s can be obtained; substituting s into equation (1), the position Y p after a time step dt can be obtained. Then at the new ray position, according to equation (2), the new s value after a time step dt is obtained by the local flow velocity V and the s value of the previous step; then s is substituted into equation (1). In this way, the trajectory of the ray is gradually obtained, and the specific trajectory is shown in Figure 3 (b). In the expansion region, the ray gradually deflects with the flow until it reaches the position of the symmetry axis, as shown in Figure 4 (a); at this time, the ray is reflected into the wave cancellation region and then again deflects with the flow until it reaches the nozzle wall. Due to the limited length of the nozzle, some rays will exceed the range of the nozzle. At this time, the nozzle profile can be linearly extended to obtain the intersection points of the nozzle and these rays, as shown in Figure 4 (b).

[0059] (1)

[0060] (2)

[0061] wherein, is the trajectory of the ray, subscript p is used to represent the ray of the expansion wave, subscripts i and j represent the directions along x and y, s is the ray vector, V is the local velocity, n is the initial vector of the ray before deflection with the flow, and c is the sound speed.

[0062] S4. The intersection points of the rays and the wall are counted to obtain the angle between the straight line formed by the adjacent two intersection points and the extended line of the wall upstream of the first intersection point, i.e. the wave cancellation angle θ, as shown in Figure 5(a) shows. Similarly, the two intersection points correspond to the two points of the divergent section, and there is also a similar angle, the divergence angle μ. In theory, the divergence angle should be equal to the angle of the wave cancellation. If there is an angle deviation, the wall of the wave cancellation section will be deflected by half the angle difference (here the angle of the divergent section is kept unchanged, but in fact the divergence angle can also be changed). Because the flow field will change after the geometric change, the angle difference can only be changed gradually, and the deflection of half the angle difference here meets the design requirements. Of course, the angle difference can also be multiplied by a coefficient to slowly adjust the profile of the wall of the wave cancellation section and gradually approach the optimal solution. The angle deflection process can be understood as dividing the nozzle wall into many segments, and deflecting each segment around the intersection point by a certain angle, such as Figure 5 (b) shows, and then the deflected discrete wall surface is combined into a continuous wall surface by up and down translation, as shown in Figure 5 (c) shows. The specific formula is as follows:

[0063] θ'1=(μ+θ1) / 2

[0064] θ'2=(μ+θ2) / 2

[0065] θ'3=(μ+θ3) / 2

[0066] Then, as shown in Figure 5 (d), a polynomial is used to fit the deflected discrete points to obtain a smooth nozzle curve. Return to the first step and iterate repeatedly until convergence is achieved. Finally, remove the extra curve to obtain the nozzle profile shown in Figure 5 (e). Users can also change the divergence form according to their own preferences, or keep the angle of the wave cancellation section unchanged and change the angle of the divergent section to achieve reverse design.

[0067] The following introduces the three-dimensional nozzle design process combined with another specific case:

[0068] The three-dimensional design process is the same as the two-dimensional design process. The following will focus on the differences between three-dimensional and two-dimensional cases.

[0069] S1. Users can draw the three-dimensional initial nozzle profile by lofting according to the required nozzle inlet shape, outlet shape and length, as shown in Figure 6 (a). The computational fluid dynamics method used and its related mesh generation, boundary setting and data post-processing need to be adjusted to three dimensions, and can also be automated through a batch program.

[0070] S2. The pressure contours in the three-dimensional nozzle flow field present a three-dimensional form. At this time, a linear fitting needs to be made in the three-dimensional space using a parametric equation (x-x0) / a1= (y-y0) / a2 = (z-z0) / a3, wherein (a1, a2, a3) is a direction vector of the linear equation; (x0, y0, z0) is a point on the straight line; it needs to be noted that the direction of (x-x0, y-y0, z-z0) is parallel to the direction vector (a1, a2, a3). Thus, the corresponding expansion position and expansion angle can be obtained.

[0071] S3. The ray method itself is suitable for two-dimensional and three-dimensional, so the process of this step is basically the same.

[0072] S4. The intersection points of the rays and the wall surface are counted, and the slopes of two adjacent intersection points are obtained. In the three-dimensional case, there are two wave cancellation angles θ1 and θ2, as shown in Fig. (a). In addition, the slopes of the two points in the expansion region corresponding to the two intersection points also exist. In the three-dimensional case, there are two expansion angles μ1 and μ2. In principle, the expansion angle should be equal to the wave cancellation angle. If there is an angle deviation between the two, the wall surface of the wave cancellation region is deflected by a general angle difference. In order to facilitate the angle deflection of the three-dimensional wave cancellation wall surface, as shown in Fig. (b), the wall surface is divided into many sections along the flow direction. Then the points on the first section are deflected first, as shown in Fig. (c), and then the points on the subsequent sections are deflected. After the deflected three-dimensional point space is translated, a new profile is fitted. Return to the first step and iterate repeatedly until convergence, as shown in Fig. (d). Figure 6 Figure 6 Figure 6 Figure 7

[0073] The embodiment of the present application further provides an electronic device, including: a processor, and a memory coupled with the processor, the memory is used for storing a computer program; the processor is used for executing the computer program stored in the memory, so that the electronic device executes the method in any one of the above embodiments.

[0074] The electronic device can be a desktop computer, a notebook computer, a palm computer, a cloud server and the like. The electronic device can include, but is not limited to, a processor, a memory.

[0075] ​​​​The processor can be a central processing unit (CPU), and can also be other general-purpose processors, digital signal processors (DSP), application specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gates or transistor logic, discrete hardware components, etc. The general-purpose processor can be a microprocessor or the processor can also be any conventional processor. The processor is a control center of the electronic device, and connects all parts of the device through various interfaces and lines.

[0076] The memory can be used to store the computer program, and the processor realizes various functions of the electronic device by running or executing the computer program stored in the memory and calling data stored in the memory.

[0077] The memory can mainly include a program storage area and a data storage area. The program storage area can store an operating system, at least one application required by a function, etc. The data storage area can store data created according to the use of the mobile phone, etc. In addition, the memory can include a high-speed random access memory, and can also include a non-volatile memory, such as a hard disk, a memory, a plug-in hard disk, a smart media card (SMC), a secure digital (SD) card, a flash card, at least one disk storage device, a flash memory device, or other volatile solid-state memory devices.

[0078] The embodiment of the present application further provides a storage medium, which is a computer readable storage medium, and the computer program is stored in the computer readable storage medium. When the computer program is executed by a processor, the steps of each method embodiment described above can be realized. The computer program includes computer program code, which can be in the form of source code, object code, executable files or some intermediate forms, etc. The computer readable medium can include any entity or device capable of carrying the computer program code, recording medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal and software distribution medium, etc.

[0079] The embodiment of the present application further provides a computer program product, comprising a computer program or instructions, which, when running on a computer, enable the computer to perform the method of any possible implementation manner described above.

[0080] The above is the preferred embodiment of the present application, it should be pointed out that, for those skilled in the technology field, without departing from the principle of the present application, can make several improvements and refinements, these improvements and refinements also be considered as the protection scope of the present application.

Claims

1. A method of designing a two-dimensional axisymmetric wind tunnel nozzle, characterized by, The method comprises the steps of: based on known nozzle design parameters, an initial nozzle profile with smooth curvature and gradual expansion is prepared; determining the starting point of the expansion wave on the initial nozzle profile and the initial ray vector determined from the starting point to the direction of the nozzle symmetry axis; based on the relationship between the local airflow velocity, the sound speed, the ray vector and the ray trajectory, the initial ray trajectory of the initial ray vector is determined from the initial ray vector at each time step, and the subsequent ray vector and the subsequent ray trajectory of the subsequent ray vector, the ray trajectory comprises: an expansion zone trajectory and a wave cancellation zone trajectory, the ray is reflected at the symmetry axis position; recording the first intersection point generated by the intersection of the ray with the initial nozzle profile before reflection, and the second intersection point generated by the intersection of the ray with the initial nozzle profile after reflection; determining the expansion angle from adjacent two of the first intersection points, and determining the wave cancellation angle from adjacent two of the second intersection points; when the expansion angle and the wave cancellation angle corresponding to the two rays before and after the time sequence are different, adjusting the line segment of the initial nozzle profile corresponding to the expansion angle or the wave cancellation angle; and generating a final nozzle profile based on the adjusted result.

2. The method of designing a two-dimensional axisymmetric wind tunnel nozzle of claim 1, wherein determining the starting point of the expansion wave on the initial nozzle profile and the initial ray vector determined from the starting point to the direction of the nozzle symmetry axis, specifically comprising: obtaining the internal flow field of the nozzle based on the computational fluid dynamics method; using a post-processing program to process the pressure distribution in the internal flow field of the nozzle with the nozzle inlet as the pressure inlet and the nozzle outlet as the pressure outlet to obtain the pressure contour line; using a linear fitting method to fit the pressure contour line to obtain the contour line equation; determining the starting point and the initial ray vector from the contour line equation and the initial nozzle profile.

3. The method of designing a two-dimensional axisymmetric wind tunnel nozzle of claim 1, wherein The relationship between the local airflow velocity, the sound speed, the ray vector and the ray trajectory is specifically: where, is the ray trajectory, subscript p is used to characterize the dilatational wave, subscripts i and j represent the direction along x, y, s is the ray vector, V is the local velocity, n is the initial vector of the ray that does not experience streamwise deflection, and c is the sound speed.

4. The method of designing a two-dimensional axisymmetric wind tunnel nozzle of claim 1, wherein determining the expansion angle from adjacent two of the first intersection points, and determining the wave cancellation angle from adjacent two of the second intersection points, specifically: the angle between the straight line determined by the two intersection points and the tangent line on the initial nozzle profile corresponding to the intersection point before the time sequence is taken as the expansion angle or the wave cancellation angle.

5. The method of designing a two-dimensional axisymmetric wind tunnel nozzle of claim 1, wherein Adjusting the line segment of the initial nozzle profile corresponding to the expansion angle or the wave cancellation angle, specifically: adjusting the line segment to rotate around the corresponding intersection point by a specified angle, and the specified angle is half of the angle difference between the expansion angle and the wave cancellation angle corresponding to the two rays before and after the time sequence.

6. The method of designing a two-dimensional axisymmetric wind tunnel nozzle of claim 1, wherein Based on the adjusted result, a final nozzle profile is generated, specifically: using a polynomial to fit the discrete points of the adjusted profile to obtain a smooth final nozzle profile.

7. A method of designing a three-dimensional axisymmetric wind tunnel nozzle, characterized by, The method comprises the steps of: based on known nozzle design parameters, an initial nozzle profile with smooth curvature and gradual expansion is prepared; linear fitting is performed on the initial nozzle profile in three-dimensional space to obtain a fitting model, and the starting point of the expansion wave and the initial ray vector determined from the starting point to the direction of the nozzle symmetry axis are determined on the fitting model; determining, based on a relationship among a local airflow velocity, a sound speed, a ray vector and a ray trajectory, an initial ray trajectory of the initial ray vector from the initial ray vector at a time step, and a subsequent ray vector and a subsequent ray trajectory of the subsequent ray vector, the ray trajectory comprising: an expansion zone trajectory and a shock wave zone trajectory, the ray being reflected at the symmetry axis position; recording a first intersection point of the recording ray with the fitted model before reflection, and a second intersection point of the recording ray with the fitted model after reflection; determining an expansion angle from two adjacent first intersection points, and determining a shock wave angle from two adjacent second intersection points; when the expansion angle and the shock wave angle corresponding to two rays at a time sequence are different, adjusting a wall surface of the fitted model corresponding to the expansion angle or the shock wave angle; and generating a final nozzle profile based on an adjusted result.

8. An electronic device, comprising: The electronic device comprises: a processor, and a memory coupled with the processor, The memory is configured to store a computer program; and The processor is configured to execute the computer program stored in the memory, so that the electronic device executes the design method of the two-dimensional axisymmetric wind tunnel nozzle according to any one of claims 1-6, or so that the electronic device executes the design method of the three-dimensional axisymmetric wind tunnel nozzle according to claim 7.

9. A computer-readable storage medium, characterized in that, The computer readable storage medium comprises a computer program or instructions, when the computer program or instructions are run on a computer, so that the computer executes the design method of the two-dimensional axisymmetric wind tunnel nozzle according to any one of claims 1-6, or so that the computer executes the design method of the three-dimensional axisymmetric wind tunnel nozzle according to claim 7.

10. A computer program product, characterised in that, The computer program product comprises: a computer program or instructions, when the computer program or instructions are run on a computer, so that the computer executes the design method of the two-dimensional axisymmetric wind tunnel nozzle according to any one of claims 1-6, or so that the computer executes the design method of the three-dimensional axisymmetric wind tunnel nozzle according to claim 7.

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