Wing body assembly large attack angle asymmetric separation flow experiment method and system

Abstract

The invention relates to the technical field of aerospace vehicle aerodynamics ground tests, in particular to a wing body assembly large attack angle asymmetric separation flow experiment method and system. The method comprises the following steps: presetting train number parameters of a wind tunnel test model, a multi-color continuous oil supply module, a pressure image acquisition module, a flow display module, a pressure measurement module and a wind tunnel; image data and pressure data are synchronously acquired, the image data are pixel-level resolution time sequence oil flow image data formed on the basis of the surface of the wind tunnel test model, and the pressure data are acquired high-precision pressure distribution data on the surface of the wind tunnel test model; based on the acquired image data and the pressure data, acquiring an asymmetry degree, a bistable depth, a fitting coefficient and a compressibility suppression ratio; if the bistable depth is gt; 0.05 and the fitting coefficient is gt; when 0.9 is reached, judging that the state is an obvious bistable state; and otherwise, determining the state as weak bistable state / no bistable state.

Description

Technical Field

[0001] This disclosure relates to the field of ground-based aerodynamic testing technology for aerospace vehicles, specifically to a method and system for experimental analysis of asymmetric vortex separation at high angles of attack in wing-body combinations. This disclosure can be used in subsonic, transonic, and supersonic wind tunnel environments for simultaneous flow visualization, surface pressure measurement, quantitative assessment of lateral force bistable characteristics, and verification of active suppression of artificial micro-disturbances in the asymmetric vortex separation of slender wing-body combinations at high angles of attack, as well as for experimental data processing. Background Technology

[0002] Modern fighter jets, tactical missiles, and other slender forebody aircraft may develop asymmetric vortex systems on the leeward side during high angle-of-attack maneuvers, even under zero sideslip conditions. These asymmetric vortex systems may induce lateral forces and yaw moments that can reach or even exceed the limits of the aircraft's yaw control capabilities.

[0003] Current research on this technology primarily targets simple spin-type bodies, often presenting the following technical challenges: a lack of systematic experimental data on complex flows involving "wing-body coupling + high angle of attack + compressibility"; flow visualization and pressure testing are typically conducted in stages, making it difficult to maintain consistent Reynolds number / Mach number states; the location of artificial micro-perturbations is fixed, making it impossible to obtain complete double-period and bistable curves of lateral force evolution with the circumferential angle of the perturbation; and insufficient experimental evidence regarding the quantitative law of compressibility's suppression of asymmetric flow under supersonic conditions. Summary of the Invention

[0004] To address the problems existing in the prior art, this disclosure proposes an experimental method and system for asymmetric separation flow at high angles of attack in wing-body composite structures, thereby solving at least one of the technical problems listed in the background art. The technical solution adopted in this disclosure is as follows: In a first aspect, this disclosure provides an experimental method for asymmetric separation flow of a wing-body composite at high angles of attack, the method comprising: Step S100: Pre-set the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel cycle parameters; Step S200: Synchronously acquire image data and pressure data. The image data is time-series oil flow image data with pixel-level resolution formed on the surface of the wind tunnel test model, and the pressure data is high-precision pressure distribution data acquired on the surface of the wind tunnel test model. Step S300: Based on the acquired image data and pressure data, obtain the asymmetry A, bistable depth ΔCz, fitting coefficient R², and compressibility suppression rate η; Step S400: If the bistable depth ΔCz > 0.05 and the fitting coefficient R² > 0.9, it is determined to be "obvious bistable"; otherwise, it is determined to be "weakly bistable / no bistable".

[0005] Preferably, in step S100, the oil supply rate of the multi-color continuous oil supply module is linked to the total pressure of the wind tunnel in the pre-set wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel train parameters.

[0006] In practice, the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel can all be implemented using existing technologies.

[0007] Preferably, in step S100, the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel train parameters are set to ensure that the angle of attack α, Mach number Ma, and Reynolds number ReD of the wind tunnel are completely consistent within the same train.

[0008] Preferably, in step S400, if the bistable depth ΔCz > 0.05 and the fitting coefficient R² > 0.9, it is determined to be "obvious bistable"; otherwise, it is determined to be "weakly bistable / non-bistable". The method may further include: Step S500: Change the Mach number Ma and Reynolds number ReD of different wind tunnel runs, and repeat steps S200 to S400 several times to obtain the bistable depth ΔCz and compressibility suppression rate η corresponding to several groups. Step S600: If the variation amplitude of the bistable depth ΔCz and compressibility suppression rate η corresponding to each group is less than or equal to the preset floating threshold, then it is determined that supersonic asymmetry is suppressed; otherwise, it is determined that supersonic asymmetry is not suppressed.

[0009] A second aspect of this disclosure provides an experimental system for asymmetric separation flow of a wing-body combination at high angles of attack, the system comprising: The experiment initialization module is used to pre-set the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel cycle parameters. The data acquisition module is used to simultaneously acquire image data and pressure data. The image data is time-series oil flow image data with pixel-level resolution formed on the surface of the wind tunnel test model, and the pressure data is high-precision pressure distribution data acquired on the surface of the wind tunnel test model. The data analysis module is used to obtain the asymmetry A, bistable depth ΔCz, fitting coefficient R², and compressibility suppression rate η based on the collected image data and pressure data. The bistable determination module is used to determine "obvious bistable" if the bistable depth ΔCz>0.05 and the fitting coefficient R²>0.9; otherwise, it determines "weakly bistable / no bistable".

[0010] Preferably, the system may further include: Multiple sets of acquisition modules are used to change the Mach number Ma and Reynolds number ReD of different wind tunnel runs, and the data acquisition module to the bistable determination module is repeatedly executed several times to obtain the bistable depth ΔCz and compressibility suppression rate η corresponding to several sets. The supersonic asymmetry determination module is used to determine that supersonic asymmetry is suppressed if the variation amplitude of the bistable depth ΔCz and the compressibility suppression rate η corresponding to each group is less than or equal to a preset floating threshold; otherwise, it is determined that supersonic asymmetry is not suppressed.

[0011] In a third aspect, this disclosure provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the experimental method for asymmetric separation flow at high angle of attack of a wing-body combination as described above, or implements the experimental system for asymmetric separation flow at high angle of attack of a wing-body combination as described above.

[0012] In a fourth aspect, this disclosure provides an electronic device including a processor and a memory, the processor being configured to execute a computer program stored in the memory to implement the experimental method for asymmetric separation flow at high angle of attack of a wing-body combination as described above, or to implement the experimental system for asymmetric separation flow at high angle of attack of a wing-body combination as described above.

[0013] The beneficial effects of this disclosure are as follows: This disclosure proposes an experimental method and system for asymmetric separation flow of wing-body combinations at high angles of attack. Data acquisition, data processing, generation and updating of dual-period / bistable curves, and bistable determination can be achieved in the same wind tunnel test run, shortening the test cycle by more than 40% and improving data correlation by more than 30%. The entire process can achieve "visualization + pressure measurement + disturbance scanning." This disclosure is the first to provide a critical criterion for asymmetric suppression of wing-body combinations at Ma = 1.52, η > 0.85. This disclosure can be extended to complex configurations such as canards, strakes, and folding wings, with wide applicability, especially suitable for Mach numbers between 0.3 and 2.0, angles of attack α between –5° and 60°, and Reynolds numbers ReD of 0.2 × 10⁻⁶. 6 —2×10 6 The subsonic and transonic wind tunnels between.

[0014] This disclosure configures the various modules of the experimental system to configure the various steps of the experimental method. It can collect, process and output data in real time, such as asymmetry A, bistable depth ΔCz, fitting coefficient R² and compressibility inhibition rate η. It can also perform bistable determination and supersonic asymmetry determination based on the output parameters. It can also generate bi-period curves in real time. Based on the obtained ΔCz as the bistable depth, it can generate or update bistable curves in real time, thereby ensuring the sufficiency and reliability of experimental evidence on the quantitative law of compressibility inhibition of asymmetry under supersonic conditions. Attached Figure Description

[0015] The accompanying drawings, which form part of this application, are used to provide a further understanding of this disclosure. The illustrative embodiments of this disclosure and their descriptions are used to explain this disclosure and do not constitute an undue limitation of this disclosure.

[0016] Figure 1 This is a flowchart of the experimental method for asymmetric separation flow of a wing-body combination at high angle of attack as described in Embodiment 1 of this disclosure; wherein, the steps within the dashed boxes are optional steps.

[0017] Figure 2 This is a schematic diagram of the experimental system for asymmetric separation flow at high angle of attack of the wing-body combination as described in Embodiment 2 of this disclosure; wherein, the modules within the dashed boxes are optional modules. Detailed Implementation

[0018] The present disclosure will now be described in detail with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in the present application can be combined with each other.

[0019] The following detailed descriptions are exemplary and intended to provide further detailed explanation of this disclosure. Unless otherwise specified, all technical terms used in this disclosure have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains. The terminology used in this disclosure is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this disclosure.

[0020] Example 1: like Figure 1 As shown, this disclosure provides an experimental method for asymmetric separation flow at high angle of attack of a wing-body combination, the method including steps S100 to S600.

[0021] Step S100: Pre-set the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel cycle parameters.

[0022] Furthermore, in step S100, the oil supply rate of the multi-color continuous oil supply module is linked to the total pressure of the wind tunnel in the pre-set wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel train parameters.

[0023] Furthermore, in step S100, the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel train parameters are set to ensure that the angle of attack α, Mach number Ma, and Reynolds number ReD of the wind tunnel are completely consistent within the same train.

[0024] Step S200: Synchronously acquire image data and pressure data. The image data is time-series oil flow image data with pixel-level resolution formed on the surface of the wind tunnel test model, and the pressure data is high-precision pressure distribution data acquired on the surface of the wind tunnel test model.

[0025] Step S300: Based on the acquired image data and pressure data, obtain the asymmetry A, bistable depth ΔCz, fitting coefficient R², and compressibility suppression rate η.

[0026] Further, step S300, which involves obtaining the asymmetry A, bistable depth ΔCz, fitting coefficient R², and compressibility suppression rate η based on the acquired image data and pressure data, includes the following steps: Step S310: Calculate the asymmetry A of the separation line angle of the image data by performing template matching and edge extraction on the image data; Step S320: The cross-sectional lateral force coefficient Cz(ψ) is obtained by integrating the pressure data. A double-period curve is fitted based on the cross-sectional lateral force coefficient Cz(ψ). The bistable depth ΔCz and the fitting coefficient R² are obtained based on the double-period curve. Step S330: Obtain the compressibility suppression rate η based on the bistable depth ΔCz.

[0027] Furthermore, the formula for calculating the compressibility suppression ratio η based on the bistable depth ΔCz can be as follows: η = 1 – ΔCz; Ma = 1.52 / ΔCz; Where η is the compressibility suppression rate, Ma is the Mach number of the wind tunnel run, and ΔCz is the bistable depth.

[0028] Furthermore, step S310, calculating the asymmetry A of the separation line angle of the image data by performing template matching-edge extraction on the image data, specifically includes: Step S311: By performing template matching and edge extraction on the image data, the first separation line angle θL and the second separation line angle θR of the image data are obtained; Step S312: Calculate the absolute value of the difference between the first separation line angle θL and the second separation line angle θR, and use the calculated absolute value as the asymmetry A.

[0029] Furthermore, the formula for calculating the asymmetry A can be as follows: A = |θL – θR|; Where A is the degree of asymmetry, θL is the angle between the first separation lines, and θR is the angle between the second separation lines.

[0030] Furthermore, step S320, which involves integrating the pressure data to obtain the cross-sectional lateral force coefficient Cz(ψ), fitting a double-period curve based on the cross-sectional lateral force coefficient Cz(ψ), and obtaining the bistable depth ΔCz and the fitting coefficient R² based on the double-period curve, specifically includes the following steps: Step S321: The lateral force coefficient Cz(ψ) of the cross section is obtained by integrating the pressure data. The calculation formula is as follows: Cz = Σ(ΔCp,i · sinφi · ΔAi) / Sref; where Cz is the lateral force coefficient of the section, ΔCp,i = (pi – p∞) / q∞, and φi is the circumferential angle of the measuring point corresponding to the pressure data; Step S322: Fit a double-period curve based on the lateral force coefficient Cz(ψ) of the cross section. The formula for expressing the double-period curve can be as follows: Cz(ψ) = A1· sin[2(ψ – ψ0)] + B1; where A1, B1, and ψ0 are all constants, and ψ is the lateral force of the cross section; Step S323: Obtain the bistable depth ΔCz and the fitting coefficient R² based on the dual-period curve.

[0031] Furthermore, the formula for calculating the bistable depth ΔCz can be as follows: Bistable depth ΔCz = (Cz max – Cz min ) / 2.

[0032] It should be noted that the asymmetry of the separation line angle of the image data, the fitting of the double-period curve based on the cross-sectional lateral force coefficient Cz(ψ), the obtaining of the bistable depth and the fitting coefficient based on the double-period curve, and the calculation of the bistable depth are all common knowledge or existing technologies in the field, and therefore will not be elaborated here.

[0033] Step S400: If the bistable depth ΔCz > 0.05 and the fitting coefficient R² > 0.9, it is determined to be "obvious bistable"; otherwise, it is determined to be "weakly bistable / no bistable".

[0034] Preferably, in step S400, if the bistable depth ΔCz > 0.05 and the fitting coefficient R² > 0.9, it is determined to be "obvious bistable"; otherwise, it is determined to be "weakly bistable / non-bistable". The method may further include: Step S500: Change the Mach number Ma and Reynolds number ReD of different wind tunnel runs, and repeat steps S200 to S400 several times to obtain the bistable depth ΔCz and compressibility suppression rate η corresponding to several groups. Step S600: If the variation amplitude of the bistable depth ΔCz and compressibility suppression rate η corresponding to each group is less than or equal to the preset floating threshold, then it is determined that supersonic asymmetry is suppressed; otherwise, it is determined that supersonic asymmetry is not suppressed.

[0035] Furthermore, the preset floating threshold is determined according to actual needs, and is preferably 10%.

[0036] Furthermore, the method employs supersonic Reynolds number matched control to ensure that the Reynolds number ReD remains within the same critical range (0.34 × 10⁻⁶). 6 —0.38×10 6 ).

[0037] Specifically, the supersonic Reynolds number matching control may include: using ejector start-up for wind tunnel runs to achieve a ReD / Ma ratio of approximately 15.3 × 10⁻⁶ at Ma = 1.52. 6 When Ma = 0.6, ReD / Ma is approximately 13.7 × 10⁻⁶. 6 ; Where Ma is the Mach number, ReD is the Reynolds number, and Red / Ma is the ratio of ReD to Mach number Ma; As the Mach number Ma decreases from 1.52 to 0.6, the ReD / Ma changes by less than 10%, thus ensuring that the Reynolds number ReD remains within the same critical range (0.34 × 10⁻⁶). 6 —0.38×10 6 ).

[0038] For ease of understanding, this embodiment conducted three experiments, with each experiment corresponding to one wind tunnel run. The angle of attack α, Mach number Ma, Reynolds number ReD, bistable depth ΔCz, and compressibility suppression rate η for each run are shown in Table 1 below.

[0039] Table 1 - Parameters for each wind tunnel test run

[0040] As can be seen from Table 1, the variation range of the bistable depth ΔCz and compressibility suppression rate η between different train operations is consistently less than 10%. This demonstrates that the present invention can fully obtain the bistable depth and asymmetric suppression rate related to the lateral force coefficient of the cross section, providing reliable data for analyzing whether supersonic asymmetry is suppressed. The present invention can obtain a pseudo-bi-period curve by acquiring pressure data from multiple train operations through multiple experiments. Using the bistable depth ΔCz and other data obtained from these experiments, a bistable curve can be constructed, thus overcoming the limitation of existing technologies that cannot obtain a complete bi-period curve and bistable curve of the lateral force evolution with the circumferential angle of the disturbance.

[0041] Example 2: like Figure 2 As shown, this embodiment provides an experimental system for asymmetric separation flow at high angles of attack of a wing-body combination. The system includes: The experiment initialization module 100 is used to pre-set the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel cycle parameters. The data acquisition module 200 is used to simultaneously acquire image data and pressure data. The image data is time-series oil flow image data with pixel-level resolution formed on the surface of the wind tunnel test model, and the pressure data is high-precision pressure distribution data acquired on the surface of the wind tunnel test model. The data analysis module 300 is used to obtain the asymmetry A, bistable depth ΔCz, fitting coefficient R², and compressibility suppression rate η based on the acquired image data and pressure data. The bistable determination module 400 is used to determine "obvious bistable" if the bistable depth ΔCz>0.05 and the fitting coefficient R²>0.9; otherwise, it is determined as "weakly bistable / no bistable".

[0042] Preferably, the system may further include: Multiple sets of acquisition modules 500 are used to change the Mach number Ma and Reynolds number ReD of different wind tunnel runs, and repeatedly execute the data acquisition module 200 to the bistable determination module 400 several times to obtain the bistable depth ΔCz and compressibility suppression rate η corresponding to several sets. The supersonic asymmetry determination module 600 is used to determine that supersonic asymmetry is suppressed if the variation amplitude of the bistable depth ΔCz and the compressibility suppression rate η corresponding to each group is less than or equal to a preset floating threshold; otherwise, it is determined that supersonic asymmetry is not suppressed.

[0043] The experimental initialization module 100, data acquisition module 200, data analysis module 300, bistable determination module 400, multi-group acquisition module 500, and supersonic asymmetric determination module 600 correspond to steps S100, S200, S300, S400, S500, and S600, respectively.

[0044] Example 3: Embodiment 3 of this disclosure provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, it implements the experimental method for asymmetric separation flow of a wing-body combination at high angle of attack as described in Embodiment 1, or the experimental system for asymmetric separation flow of a wing-body combination at high angle of attack as described in Embodiment 2.

[0045] The computer-readable storage medium includes volatile or non-volatile, removable or non-removable media implemented in any method or technology for storing information (such as computer-readable instructions, data structures, computer program modules, or other data). Computer-readable storage media include, but are not limited to, RAM (Random Access Memory), ROM (Read-Only Memory), EEPROM (Electrically Erasable Programmable Read-Only Memory), flash memory or other memory technologies, CD-ROM (Compact Disc Read-Only Memory), DVD or other optical disc storage, cartridges, magnetic tapes, disk storage or other magnetic storage devices, or any other medium that can be used to store desired information and is accessible to a computer.

[0046] Example 4: Embodiment 4 of this disclosure provides an electronic device, which includes a processor and a memory. The processor is used to execute a computer program stored in the memory to implement the experimental method for asymmetric separation flow of wing-body combination at high angle of attack as described in Embodiment 1, or to implement the experimental system for asymmetric separation flow of wing-body combination at high angle of attack as described in Embodiment 2.

[0047] Based on this understanding, all or part of the processes in the methods of the above embodiments can also be implemented by a computer program instructing related hardware. The computer program can be stored in a computer-readable storage medium, and when executed by a processor, it can implement the steps of the various method embodiments described above. The computer program includes computer program code, which can be in the form of source code, object code, executable files, or certain intermediate forms. The computer-readable medium can include: any entity or device capable of carrying computer program code, recording media, USB flash drives, portable hard drives, magnetic disks, optical disks, computer memory, and read-only memory (ROM).

[0048] Those skilled in the art will understand that embodiments of this disclosure can be provided as methods, systems, or computer program products. Therefore, this disclosure can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this disclosure can take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0049] This disclosure is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this disclosure. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create a machine for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0050] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0051] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0052] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this disclosure. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0053] In summary, the experimental method and system for asymmetric separation flow of wing-body combinations at high angles of attack provided in this disclosure can achieve data acquisition, data processing, generation and updating of dual-period / bistable curves, and bistable determination in the same wind tunnel test run, shortening the test cycle by more than 40% and improving data correlation by more than 30%. The entire process can achieve "visualization + pressure measurement + disturbance scanning." This disclosure is the first to provide a critical criterion for asymmetric suppression of wing-body combinations at Ma = 1.52, η > 0.85. This disclosure can be extended to complex configurations such as canards, strakes, and folding wings, with wide applicability, especially suitable for Mach numbers between 0.3 and 2.0, angles of attack α between –5° and 60°, and Reynolds numbers ReD of 0.2 × 10⁻⁶. 6 —2×10 6 The subsonic and transonic wind tunnels between.

[0054] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this disclosure and not to limit them. Although this disclosure has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of this disclosure. Any modifications or equivalent substitutions that do not depart from the spirit and scope of this disclosure should be covered within the protection scope of the claims of this disclosure.

Claims

1. An experimental method for asymmetric separation flow at high angles of attack of a wing-body composite, characterized in that, The method includes: Step S100: Pre-set the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel cycle parameters; Step S200: Synchronously acquire image data and pressure data. The image data is time-series oil flow image data with pixel-level resolution formed on the surface of the wind tunnel test model, and the pressure data is high-precision pressure distribution data acquired on the surface of the wind tunnel test model. Step S300: Based on the acquired image data and pressure data, obtain the asymmetry A, bistable depth ΔCz, fitting coefficient R², and compressibility suppression rate η; Step S400: If the bistable depth ΔCz > 0.05 and the fitting coefficient R² > 0.9, it is determined to be "obvious bistable"; otherwise, it is determined to be "weakly bistable / no bistable".

2. The experimental method for asymmetric flow separation at high angles of attack of a wing-body combination as described in claim 1, characterized in that, In step S100, the oil supply rate of the multi-color continuous oil supply module is linked to the total pressure of the wind tunnel in the pre-set wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module and wind tunnel train parameters.

3. The experimental method for asymmetric flow separation at high angle of attack of a wing-body combination as described in claim 2, characterized in that, In step S100, the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel train parameters are set to ensure that the angle of attack α, Mach number Ma, and Reynolds number ReD of the wind tunnel are completely consistent within the same train.

4. The experimental method for asymmetric flow separation at high angles of attack of a wing-body combination as described in claim 1, characterized in that, Step S300, based on the acquired image data and pressure data, obtains the asymmetry A, bistable depth ΔCz, fitting coefficient R², and compressibility suppression rate η, including the following steps: Step S310: Calculate the asymmetry A of the separation line angle of the image data by performing template matching and edge extraction on the image data; Step S320: The cross-sectional lateral force coefficient Cz(ψ) is obtained by integrating the pressure data. A double-period curve is fitted based on the cross-sectional lateral force coefficient Cz(ψ). The bistable depth ΔCz and the fitting coefficient R² are obtained based on the double-period curve. Step S330: Obtain the compressibility suppression rate η based on the bistable depth ΔCz.

5. The experimental method for asymmetric flow separation at high angle of attack of a wing-body combination as described in claim 4, characterized in that, Step S310, which involves performing template matching and edge extraction on the image data to calculate the asymmetry A of the separation line angle of the image data, specifically includes: Step S311: By performing template matching and edge extraction on the image data, the first separation line angle θL and the second separation line angle θR of the image data are obtained; Step S312: Calculate the absolute value of the difference between the first separation line angle θL and the second separation line angle θR, and use the calculated absolute value as the asymmetry A.

6. The experimental method for asymmetric separation flow at high angle of attack of a wing-body combination as described in claim 4, characterized in that, Step S320, which involves integrating the pressure data to obtain the cross-sectional lateral force coefficient Cz(ψ), fitting a double-period curve based on the cross-sectional lateral force coefficient Cz(ψ), and obtaining the bistable depth ΔCz and the fitting coefficient R² based on the double-period curve, specifically includes the following steps: Step S321: Obtain the cross-sectional lateral force coefficient Cz(ψ) by integrating the pressure data; Step S322: Fit a double-period curve based on the lateral force coefficient Cz(ψ) of the cross section; Step S323: Obtain the bistable depth ΔCz and the fitting coefficient R² based on the dual-period curve.

7. The experimental method for asymmetric flow separation at high angle of attack of a wing-body combination as described in claim 1, characterized in that, In step S400, if the bistable depth ΔCz > 0.05 and the fitting coefficient R² > 0.9, it is determined to be "obvious bistable"; otherwise, it is determined to be "weakly bistable / non-bistable". After this step, the method further includes: Step S500: Change the Mach number Ma and Reynolds number ReD of different wind tunnel runs, and repeat steps S200 to S400 several times to obtain the bistable depth ΔCz and compressibility suppression rate η corresponding to several groups. Step S600: If the variation amplitude of the bistable depth ΔCz and compressibility suppression rate η corresponding to each group is less than or equal to the preset floating threshold, then it is determined that supersonic asymmetry is suppressed; otherwise, it is determined that supersonic asymmetry is not suppressed.

8. The experimental method for asymmetric flow separation at high angle of attack of a wing-body combination as described in claim 7, characterized in that, The preset floating threshold is 10%.

9. The experimental method for asymmetric flow separation at high angle of attack of a wing-body combination as described in claim 1, characterized in that, The method employs supersonic Reynolds number matched control.

10. An experimental system for asymmetric flow separation at high angles of attack of a wing-body combination, characterized in that, The experiment initialization module (100) is used to pre-set the wind tunnel test model, multi-color continuous oil supply module, pressure image acquisition module, flow display module, pressure measurement module, and wind tunnel cycle parameters; The data acquisition module (200) is used to simultaneously acquire image data and pressure data. The image data is time-series oil flow image data with pixel-level resolution formed on the surface of the wind tunnel test model, and the pressure data is high-precision pressure distribution data acquired on the surface of the wind tunnel test model. The data analysis module (300) is used to obtain the asymmetry A, bistable depth ΔCz, fitting coefficient R² and compressibility suppression rate η based on the acquired image data and pressure data. The bistable determination module (400) is used to determine "obvious bistable" if the bistable depth ΔCz > 0.05 and the fitting coefficient R² > 0.9; otherwise, it is determined as "weak bistable / no bistable".

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