Bionic wrinkled surface driven by flow field data and design method thereof

Abstract

The invention provides a bionic wrinkled surface driven by flow field data and a design method of the bionic wrinkled surface. The bionic wrinkle surface is of a wrinkle array structure which continuously fluctuates in the flow direction relative to the reference molded surface and is periodically arranged. The method comprises the following steps: S1, modeling an application object and establishing a simulation environment; s2, flow field characteristic data acquisition and analysis; s3, wrinkle geometric parameter calculation and initial phase determination; s4, establishing a feature function relationship; and S5, performing three-dimensional modeling and structure generation. According to the method, local wrinkle characteristic parameters can be correspondingly fitted according to parameters such as wall surface local flow velocity and shear stress, accurate intervention and adaptive capacity of boundary layer behaviors of corresponding areas are achieved, and therefore more efficient resistance reduction and flow control are achieved in different areas.

Description

Technical Field

[0001] This invention relates to the field of turbomachinery technology, and more particularly to a flow field data-driven biomimetic wrinkled surface and its design method. Background Technology

[0002] With global energy shortages and increasingly stringent carbon emission constraints, improving the operating efficiency and reducing energy loss of fluid machinery under higher power density and smaller structural dimensions has become a core research topic in aerospace, energy power, and marine propulsion. Fluid machinery, represented by compressors and turbines, suffers from complex internal flow conditions and high load levels, generally exhibiting significant aerodynamic losses and flow stability issues. Aerodynamic losses mainly originate from two aspects: first, frictional resistance caused by the viscous interaction between the fluid and the solid wall; and second, flow separation and secondary flow structures induced by high curvature, diffusion, and end-wall interference, resulting in significant pressure differential drag. Furthermore, under high Reynolds number and high turbulent kinetic energy conditions, intense local mixing, energy dissipation, and blockage caused by the accumulation of low-energy fluids further exacerbate system efficiency losses and instability risks.

[0003] To achieve drag reduction and efficiency improvement, scholars and engineering practitioners both domestically and internationally have proposed various flow control and surface optimization strategies, which can be mainly divided into two categories: active control and passive control. Active control methods, such as wall vibration, pulsed jet, boundary layer suction and injection, significantly regulate near-wall flow through external energy input. However, they often suffer from problems such as complex structures, high energy consumption, and insufficient reliability, limiting their application in complex environments with high temperature, high pressure, and high speed. In contrast, passive control technology has higher feasibility in engineering practice due to its simple structure, lack of external energy requirements, and strong adaptability. Among them, non-smooth wall structures based on biomimetic principles (such as microribs, grooves, and pits) are a typical passive drag reduction scheme. By inducing vortex structures in the near-wall layer through geometric perturbation, they suppress flow separation, weaken secondary flow, and delay boundary layer development, achieving certain drag reduction effects in various flow devices.

[0004] However, existing non-smooth surface designs generally have the following limitations: On the one hand, most solutions employ drag-reduction structures with a single scale or uniform parameters, failing to differentiate them according to the flow characteristics of different regions. On the other hand, these structures are typically based on fixed geometric parameters and lack the ability to adaptively respond to changes in complex multiphysics fields (such as local velocity, shear stress, and pressure). Therefore, their drag reduction and flow stability improvement effects under high loads and variable operating conditions are significantly limited.

[0005] To address the aforementioned issues, there is an urgent need to propose a novel drag-reducing surface and its design method that can adaptively adjust local flow field physical parameters. This would improve the aerodynamic performance of fluid machinery while also ensuring adaptability to multiple operating conditions, structural reliability, and manufacturing feasibility, thus providing a better flow control solution for the next generation of high-performance turbomachinery and related equipment. Summary of the Invention

[0006] To address the aforementioned technical problems, a flow field data-driven biomimetic wrinkled surface and its design method are provided.

[0007] The technical means employed in this invention are as follows: A flow field data-driven biomimetic folded surface, wherein the biomimetic folded surface is a folded array structure that is continuously undulating and periodically arranged along the flow direction relative to a reference profile. The local dimensions of the folded array structure include amplitude and period, and the amplitude and period of multiple folded array structures distributed along the flow direction are variable.

[0008] Furthermore, the folded array structure is a periodic folded surface formed on the wall, and its shape is characterized by a trigonometric function.

[0009] Furthermore, the biomimetic folded surface is arranged in the laminar flow region, transition region, or turbulent flow region.

[0010] This invention also provides a flow field data-driven design method for biomimetic wrinkled surfaces, comprising the following steps: S1. Application object modeling and simulation environment establishment; S11. Based on the application object of the biomimetic wrinkled surface, establish the three-dimensional geometric model and computational domain of the application object; S12. Set boundary conditions, select a suitable turbulence model or large eddy simulation, and perform numerical simulation. S2. Acquisition and analysis of flow field characteristic data; S21. Obtain key physical parameters of the flow field near the wall of the application object through numerical simulation, namely flow field data, which includes local velocity distribution and characteristic Reynolds number; S22. Extract and organize the flow field data to obtain the distribution characteristics of the flow direction coordinates, local velocity, and Reynolds number parameters, and determine the location and coverage of the transition zone during the flow process, thereby determining the arrangement position of the folded surface. S3. Calculation of folded geometric parameters and determination of initial phase: Using drag reduction curves and the relationship established based on drag reduction curves, calculate the geometric characteristic dimensions of folded array structures in specific flow field regions to achieve adaptive design of folded array structures in different regions. S4. Establishing the characteristic function relationship; S41. Extract the functional relationship between the flow field characteristic parameters and their corresponding spatial positions, wherein the flow field characteristic parameters include Reynolds number and local velocity; S42. Establish the correspondence between the flow field characteristic parameters and the fold geometric parameters, wherein the fold geometric parameters include amplitude A, period T, and initial phase. ; S43. Perform sinusoidal fitting along the flow direction on the local fold geometry to obtain the governing equation of the fold curve; S5, 3D modeling and structure generation; S51. Based on the obtained geometric feature dimensions of the fold array structure and the control equation of the fold curve, a biomimetic fold curve is generated, and then combined and fitted with the original profile of the application object to form a new profile with biomimetic folds. S52. Based on S51, CAD modeling or parametric 3D modeling is used to obtain a complete 3D model of the application object with a biomimetic wrinkled surface driven by flow field data.

[0011] Furthermore, in S11, the application objects include compressor planar blades or rotor blades and stator blades.

[0012] Furthermore, in S3, the geometric feature dimensions include amplitude, period, and initial phase.

[0013] Furthermore, the amplitude satisfies the following formula: ; In the formula, This represents a local dimensionless amplitude. The amplitude; For local velocity; Kinematic viscosity; The characteristic Reynolds number based on the string length, b This is the chord length of the blade; The period satisfies the following formula: ; In the formula, It is a local dimensionless period; It is a periodicity.

[0014] Furthermore, in S3, the initial phase It is mainly determined through the correlation of initial flow field characteristics, biomimetic structural design constraints, or fitting optimization. Its core function is to define the shape of the fold curve at the starting position to adapt to the needs of flow field control or biomimetic design.

[0015] Furthermore, in S43, the governing equation of the fold curve satisfies the following formula: ; In the formula, A is the amplitude and T is the period. This is the initial phase. 0、 1 represents the bias and weak linear term.

[0016] Compared with the prior art, the present invention has the following advantages: 1. The flow field data-driven biomimetic folded surface and its design method provided by this invention break through the limitations of traditional drag reduction structures that rely solely on fixed geometric parameters and a single flow field variable. It proposes an adaptive control mechanism based on flow field data, which can fit local folded characteristic parameters according to parameters such as local flow velocity and shear stress on the wall, thereby achieving precise intervention and adaptation of boundary layer behavior in the corresponding region, and thus achieving more efficient drag reduction and flow control in different regions.

[0017] 2. The biomimetic wrinkled surface and its design method driven by flow field data provided in this invention, as a passive flow control technology, can achieve comprehensive optimization of local aerodynamic performance without the need for external energy input or complex control devices. Compared with traditional non-smooth structures, this invention has the advantages of effectively controlling laminar transition, suppressing corner separation, and reducing friction and pressure drag under extreme conditions such as high Reynolds number and high pressure ratio, while maintaining the advantages of simple structure, feasible manufacturing, and high reliability. It is particularly suitable for high-load applications such as aero-engines, gas turbines, and high-performance turbomachinery.

[0018] 3. The biomimetic folded surface and its design method driven by flow field data provided by this invention can be flexibly arranged in laminar flow, transition, and turbulent separation regions according to application requirements. In the laminar flow region, the folded structure weakens the growth of the original unstable wave by introducing appropriate disturbances, delays boundary layer transition, and expands the laminar flow range. In the turbulent separation region, the folded structure can transform backflow into vortices, weaken the backflow intensity, and transform sliding friction into rolling friction, thereby reducing friction loss. When arranged simultaneously in laminar and turbulent regions, it can also achieve the dual effects of delaying transition and weakening turbulent separation, realizing efficient drag reduction and anti-separation control across the entire flow domain.

[0019] Based on the above reasons, this invention can be widely applied to surface flow control and drag reduction applications in high-performance power devices such as aero engines, gas turbines, marine propulsion systems, and industrial compressors. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram illustrating the distribution of velocity along the axial chord length within the blade cascade channel in this invention.

[0022] Figure 2 This is a schematic diagram of the friction coefficient of the blade's mid-diameter wall surface in this invention.

[0023] Figure 3 This is a schematic diagram of the turbulence intermittent factor and limiting streamline of the blade suction surface in this invention.

[0024] Figure 4 This is a schematic diagram of the flow direction folding curve in the laminar flow region at the leading edge in this invention.

[0025] Figure 5 This is a schematic diagram of the flow direction folding curve in the trailing edge turbulent region of the present invention.

[0026] Figure 6 This is a schematic diagram of the biomimetic folded leaf shape in this invention.

[0027] Figure 7 This is a schematic diagram of the biomimetic folded blade in this invention. Detailed Implementation

[0028] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of exemplary embodiments according to the invention. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0031] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0032] Example 1 With the increasing demands for high efficiency, lightweight design, and intelligence in high-performance power devices such as aero-engines, gas turbines, marine propulsion systems, and industrial compressors, boundary layer thickening, flow separation, localized high temperatures, and turbulent vortex structures in complex flow fields have become key factors limiting performance improvement. Especially in multi-stage axial compressors, low aspect ratio blade cascades, and the surfaces of high-speed rotating components, the drag reduction capability of traditionally uniformly arranged microstructures is limited, making it difficult to balance adaptability and stability under different operating conditions.

[0033] This invention proposes a flow field data-driven biomimetic pleated surface and its design method, which can be widely applied to surface flow control and drag reduction in high-performance power devices such as aero-engines, gas turbines, marine propulsion systems, and industrial compressors. Under complex flow conditions, the biomimetic pleated surface can be placed in the laminar boundary layer region before the transition zone. Through the additional disturbance waves induced by the pleats, it weakens or suppresses the growth process of the original unstable disturbances in the boundary layer, thereby effectively delaying the transition from laminar to turbulent flow, expanding the laminar flow development range, maintaining boundary layer stability, and reducing flow separation. Alternatively, it can be placed in the turbulent region after the transition. Here, the pleated structure can transform the separated backflow into vortex motion, weakening the backflow intensity. At the same time, it changes the friction mode between the near-wall airflow and the wall surface, transforming sliding friction into rolling friction, significantly reducing frictional drag, thereby weakening turbulent separation and improving overall flow characteristics. Furthermore, this biomimetic pleated surface can also be placed in both the laminar boundary layer region and the turbulent region to achieve a synergistic control effect of delaying transition and weakening separation, achieving comprehensive performance improvement with reduced losses and increased efficiency under different operating conditions.

[0034] The biomimetic folded surface proposed in this invention is a folded structure that is continuously undulating and periodically arranged along the flow direction relative to a reference profile. The local dimensions (amplitude, period) of the folds are directly related to the local flow field parameters (velocity and Reynolds number) at their location.

[0035] Folded array structure: A periodic folded surface is formed on the wall, and its shape is characterized by trigonometric functions.

[0036] Parametric characteristics: The amplitude A and period T of a single fold are used as key design parameters. Their values ​​are established with corresponding functional relationships with local flow field parameters. That is, the amplitude and period of multiple fold structures distributed along the flow direction are variable.

[0037] Distribution characteristics: The folded surface can be arranged in the laminar flow region, transition region or turbulent flow region to specifically delay the transition or weaken the turbulent separation.

[0038] This invention provides a new technical approach for surface drag reduction and flow control based on flow field data, which has good engineering applicability and promotion value.

[0039] The design method proposed in this invention includes the following main steps: Step 1: Application Object Modeling and Simulation Environment Establishment A three-dimensional geometric model and computational domain are established based on the specific application of the biomimetic folded surface (such as compressor planar blades, rotor blades, stator blades, etc.). Reasonable boundary conditions are set, and appropriate turbulence models or large eddy simulations are selected to ensure the accuracy of the flow field simulation.

[0040] Step 2: Acquisition and Analysis of Flow Field Characteristic Data Key physical parameters of the flow field near the wall are obtained through numerical simulation, including but not limited to local velocity distribution and characteristic Reynolds number. The flow field data is extracted and processed to obtain the distribution characteristics of flow direction coordinates and parameters such as local velocity and Reynolds number. Furthermore, the location and coverage of the transition zone during the flow process need to be determined, thereby determining the placement of the folded surfaces.

[0041] Step 3: Calculation of fold geometry parameters and determination of initial phase Using the established relational formula, the geometric characteristic dimensions of the folded array structure arranged in a specific flow field region are calculated, including amplitude, period and initial phase.

[0042] This step enables "adaptive design" of the pleated structure in different regions, making it more suitable for local flow field characteristics.

[0043] initial phase It is mainly determined through the correlation of initial flow field characteristics, biomimetic structural design constraints, or fitting optimization. Its core function is to define the shape of the fold curve at the starting position to adapt to the needs of flow field control or biomimetic design.

[0044] Step 4: Establishing the relationship of characteristic functions Based on the amplitude and period parameters obtained above, a correspondence between the biomimetic fold curve and the fold geometric parameters (amplitude A, period T) is further established.

[0045] Step 5: 3D Modeling and Structure Generation Based on the obtained amplitude, period, and arrangement parameters, a biomimetic fold curve is generated. Further CAD modeling or parametric 3D modeling is then employed to obtain a complete 3D model of the biomimetic fold surface driven by flow field data.

[0046] Example 2 This invention provides a flow field data-driven design method for biomimetic folded surfaces, which is applied to compressor planar blades to form a compressor planar blade with a data-driven biomimetic folded surface.

[0047] The above-mentioned design method for compressor planar blades with data-driven biomimetic folded surfaces includes the following steps: Step 1: First, determine the incoming flow conditions based on the selected compressor blade or cascade operating conditions, including the incoming Mach number and Reynolds number. Establish a three-dimensional geometric model and computational domain for the conventional compressor cascade. Set reasonable boundary conditions based on the blade's design operating conditions, and select turbulence models and numerical calculation methods validated by experimental data to ensure the accuracy of the flow field simulation.

[0048] Step 2: Obtain key physical parameters of the flow field near the near-wall surface of the blade's suction surface through numerical simulation, including but not limited to: local velocity distribution and characteristic Reynolds number. Extract and organize the flow field data to obtain the distribution characteristics of the flow direction coordinates and parameters such as local velocity and Reynolds number. The variation law of velocity within the blade passage with axial chord length is as follows: Figure 1 As shown.

[0049] The relationship between velocity and axial chord length position coordinates is fitted using polynomial least squares, yielding the following empirical function for x∈[0,1]: ; The coefficients are (rounded to three decimal places): a 5 = 693.795 a 4 = -1980.059 a 3 = 2201.090 a 2 = -1115.630 a 1 = 131.627 a 0 = 232.889, Goodness of fit: R 2 =0.9983.

[0050] Simultaneously, the blade surface friction coefficient and limiting streamline characteristics are extracted based on numerical calculations to accurately determine the location and coverage of the transition zone, thereby further accurately determining the arrangement of the folded surfaces. The local flow state or characteristics of the blade surface can be determined from the data extracted from the flow field data file, thus revealing the arrangement of the folded surfaces. The flow direction distribution curve of the blade surface friction coefficient is shown below. Figure 2 As shown, the friction coefficient of the blade surface indicates that the suction surface friction coefficient reaches a local minimum at approximately 30% of the axial chord length. Further analysis... Figure 3 The limiting streamline characteristics in the image indicate that the corresponding location is the starting point of the laminar separation bubble, i.e., the starting point of the suction surface transition zone. The turbulence interval factor and limiting streamline of the blade suction surface are shown below. Figure 3 As shown.

[0051] Based on the analysis results of the wall friction coefficient and the flow structure of the suction surface, the designed biomimetic pleated surface can be initially arranged in the corresponding region in front of the separation bubble to control the development of the laminar separation bubble and thus delay the transition. Alternatively, the pleated surface can be arranged at the end of the separation bubble and in the fully turbulent downstream region to control turbulent separation and weaken the corner separation intensity. Finally, pleated surfaces can be further arranged simultaneously in the turbulent regions upstream and downstream of the separation bubble to achieve synergistic control of the laminar separation bubble and corner separation, ultimately achieving drag reduction and efficiency improvement.

[0052] Step 3: Calculation of fold geometry parameters and determination of initial phase. Based on the drag reduction curve and the relationship established based on the drag reduction curve (the formula for calculating the drag reduction structure dimensions corresponding to the drag reduction curve), calculate the geometric characteristic dimensions of the fold array structure arranged in a specific flow field region, including: Amplitude is: ; In the formula, This represents a local dimensionless amplitude. The amplitude; For local velocity; Kinematic viscosity; The characteristic Reynolds number based on the string length, b This is the chord length of the blade; The period is: ; In the formula, It is a local dimensionless period; For periodicity; initial phase It is mainly determined through the correlation of initial flow field characteristics, biomimetic structural design constraints, or fitting optimization. Its core function is to define the shape of the fold curve at the starting position to adapt to the needs of flow field control or biomimetic design.

[0053] Step 4: Based on the above amplitude and period formulas, further establish the correspondence between the biomimetic fold curve and the fold geometric parameters (amplitude A, period T) (i.e., the governing equations below). Use the blade suction surface reference axis curve (or local tangential coordinates) as the flow direction coordinates. , with the direction of the law .

[0054] By performing a sinusoidal fit along the flow direction on the local fold geometry, allowing for slight linear drift (compensating for minor tilting / stretching of the curve), the governing equations of the fold curve are obtained as follows: ; In the formula, A is the amplitude and T is the period. This is the initial phase. 0、 1 represents the bias and weak linear term.

[0055] For the local parameters of the flow field in the leading edge region, the parameters of the governing equations are obtained by fitting as follows: amplitude A =0.0299, period T =3.78, initial phase =0.72, bias c 0= 4.18×10 -17 (Negligible), slope c 1 = 0.00105. The final control equations, substituted with the parameters, are as follows: ; Similarly, the governing equations for the trailing edge suction surface wrinkle curve can ultimately be written as: ; The schematic diagram of the arrangement and the biomimetic folded surface cross-sectional curves near the leading and trailing edges of the blade, obtained by fitting the flow field data, is shown below. Figure 4 and Figure 5 As shown.

[0056] Step 5: Based on the obtained governing equations of the folded curve, which include amplitude, period, and initial phase. n (s) Generate a biomimetic folded curve, and further merge and fit it with the original leaf shape line to form a new biomimetic folded leaf shape, such as Figure 6 As shown, the designed biomimetic folded profile consists of trigonometric function curves that undulate continuously along the flow direction relative to the airfoil reference profile. Further, a two-dimensional compressor airfoil with a data-driven biomimetic folded surface is established using CAD, and then a three-dimensional model is created using UG, ultimately yielding a complete three-dimensional compressor blade model with a flow field data-driven biomimetic folded surface, as shown. Figure 7 As shown.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A flow field data-driven biomimetic wrinkled surface, characterized in that, The biomimetic folded surface is a folded array structure that is continuously undulating and periodically arranged along the flow direction relative to the reference surface. The local dimensions of the folded array structure include amplitude and period, and the amplitude and period of multiple folded array structures distributed along the flow direction are variable.

2. The flow field data-driven biomimetic wrinkled surface according to claim 1, characterized in that, The folded array structure is a periodic folded surface formed on the wall, and its shape is characterized by trigonometric functions.

3. The flow field data-driven biomimetic wrinkled surface according to claim 1, characterized in that, The biomimetic folded surface is arranged in the laminar flow region, transition region, or turbulent flow region.

4. A method for designing a biomimetic wrinkled surface driven by flow field data as described in any one of claims 1-3, characterized in that, Includes the following steps: S1. Application object modeling and simulation environment establishment; S11. Based on the application object of the biomimetic wrinkled surface, establish the three-dimensional geometric model and computational domain of the application object; S12. Set boundary conditions, select a suitable turbulence model or large eddy simulation, and perform numerical simulation. S2. Acquisition and analysis of flow field characteristic data; S21. Obtain key physical parameters of the flow field near the wall of the application object through numerical simulation, namely flow field data, which includes local velocity distribution and characteristic Reynolds number; S22. Extract and organize the flow field data to obtain the distribution characteristics of the flow direction coordinates, local velocity, and Reynolds number parameters, and determine the location and coverage of the transition zone during the flow process, thereby determining the arrangement position of the folded surface. S3. Calculation of folded geometric parameters and determination of initial phase: Using drag reduction curves and the relationship established based on drag reduction curves, calculate the geometric characteristic dimensions of folded array structures in specific flow field regions to achieve adaptive design of folded array structures in different regions. S4. Establishing the characteristic function relationship; S41. Extract the functional relationship between the flow field characteristic parameters and their corresponding spatial positions, wherein the flow field characteristic parameters include Reynolds number and local velocity; S42. Establish the correspondence between flow field characteristic parameters and fold geometric parameters, wherein the fold geometric parameters include amplitude A and period T; S43. Perform sinusoidal fitting along the flow direction on the local fold geometry to obtain the governing equation of the fold curve; S5, 3D modeling and structure generation; S51. Based on the obtained geometric feature dimensions of the fold array structure and the control equation of the fold curve, a biomimetic fold curve is generated, and then combined and fitted with the original profile of the application object to form a new profile with biomimetic folds. S52. Based on S51, CAD modeling or parametric 3D modeling is used to obtain a complete 3D model of the application object with a biomimetic wrinkled surface driven by flow field data.

5. The method for designing a biomimetic wrinkled surface driven by flow field data according to claim 4, characterized in that, In S11, the application objects include compressor planar blades or rotor blades and stator blades.

6. The method for designing a biomimetic wrinkled surface driven by flow field data according to claim 4, characterized in that, In S3, the geometric feature dimensions include amplitude, period, and initial phase.

7. The method for designing a biomimetic wrinkled surface driven by flow field data according to claim 6, characterized in that, The amplitude satisfies the following formula: ； In the formula, This represents a local dimensionless amplitude. The amplitude; For local velocity; Kinematic viscosity; The characteristic Reynolds number based on the string length, b This is the chord length of the blade; The period satisfies the following formula: ； In the formula, It is a local dimensionless period; It is a periodicity.

8. The method for designing a biomimetic wrinkled surface driven by flow field data according to claim 4, characterized in that, In S3, the initial phase The shape of the folded curve at the starting position is determined by associating initial flow field characteristics, biomimetic structural design constraints, or fitting optimization, in order to adapt to the needs of flow field control or biomimetic design.

9. The method for designing a biomimetic wrinkled surface driven by flow field data according to claim 8, characterized in that, In S43, the governing equation of the fold curve satisfies the following formula: ； In the formula, A is the amplitude and T is the period. This is the initial phase. 0、 1 represents the bias and weak linear term.

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