Method and device for determining stall attack angle of wing with high aspect ratio

Abstract

The invention belongs to the technical field of flight control, and particularly relates to a method and a device for determining a stall attack angle of a high-aspect-ratio wing. The method comprises the following steps: S1, determining the maximum lift coefficient of a wing; and S2, determining a stall incidence angle. According to the method, the calculation efficiency of the high-aspect-ratio stall attack angle is high, and the calculation precision is controllable.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft design, and in particular to a method and device for determining the stall angle of attack of a high aspect ratio wing. Background Art

[0002] The maximum lift coefficient and stall angle of attack are important parameters for evaluating the lift characteristics of a transport aircraft. The design of the aircraft's flight envelope and pitch control rate requires accurate maximum lift coefficient and stall angle of attack data support. The leading edge sharpness, curvature, and maximum thickness position of the airfoil are very sensitive to the maximum lift coefficient and stall angle of attack of the high aspect ratio wing. The maximum lift coefficient and stall angle of attack of the wing are also closely related to the wing plane parameters and flight speed. The theoretical algorithms used in existing technologies are far from the actual data and have low calculation accuracy. Summary of the invention

[0003] In order to solve the above problems, the present application provides a method and device for determining the stall angle of attack of a high aspect ratio wing, providing technical support for the wing configuration parameter design, airfoil sensitive parameter design, and lift and stall characteristics evaluation of the aircraft high-speed configuration of the high aspect ratio aircraft.

[0004] In a first aspect, the present application provides a method for determining the stall angle of attack of a high aspect ratio wing, the method mainly comprising:

[0005] Step S1, determine the maximum lift coefficient C of the wing Lmax :

[0006] C Lmax =XC ymax +ΔC Lmax ;

[0007] Where X is the conversion factor of the maximum lift coefficient from two dimensions to three dimensions, C ymax is the maximum lift coefficient of the airfoil, ΔC Lmax is the maximum lift coefficient correction;

[0008] Step S2: Determine the stall angle of attack α max :

[0009]

[0010] Among them, C Lα is the slope of the wing lift line, α L0 is the angle of attack for zero lift, Δα max is the stall angle of attack correction.

[0011] Preferably, step S1 further comprises:

[0012] Step S11, determining a hundred-fold parameter ΔY of the airfoil leading edge sharpness Δy;

[0013] Step S12: Determine the conversion factor X as:

[0014] X = A-BΔY′;

[0015] When ΔY<1.4, ΔY'=0, when 1.4≤ΔY≤.25, ΔY'=ΔY-1.4, when ΔY>2.5, ΔY'=1.1;

[0016]

[0017] Among them, Λ LE is the wing leading edge sweep angle.

[0018] Preferably, step S1 further comprises:

[0019] Step S13: Determine the maximum lift coefficient C of the airfoil using the following formula: ymax :

[0020] C ymax =C ymaxb +ΔC ymax ;

[0021] Among them, parameter C ymaxb The interpolation calculation is obtained in the first interpolation table constructed by the maximum thickness position of the airfoil and the hundred-fold parameter ΔY; the parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by one hundred times the airfoil camber and one hundred times the parameter ΔY.

[0022] Preferably, step S1 further comprises:

[0023] Step S14: Determine the maximum lift coefficient correction value ΔC by the following formula: Lmax :

[0024]

[0025] Among them, parameter C is obtained by interpolation calculation in the third interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY, and parameter D is obtained by interpolation calculation in the fourth interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY.

[0026] Preferably, in step S2, the stall angle correction amount Δα max The wing leading edge sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter ΔY.

[0027] The second aspect of the present application provides a device for determining the stall angle of attack of a high aspect ratio wing, mainly comprising:

[0028] The wing maximum lift coefficient determination module is used to determine the wing maximum lift coefficient CLmax :

[0029] C Lmax =XC ymax +ΔC Lmax ;

[0030] Where X is the conversion factor of the maximum lift coefficient from two dimensions to three dimensions, C ymax is the maximum lift coefficient of the airfoil, ΔC Lmax is the maximum lift coefficient correction;

[0031] Stall angle of attack determination module, used to determine the stall angle of attack α max :

[0032]

[0033] Among them, C Lα is the slope of the wing lift line, α L0 is the angle of attack for zero lift, Δα max is the stall angle of attack correction.

[0034] Preferably, the wing maximum lift coefficient determination module includes:

[0035] A hundredfold parameter determination unit, used to determine a hundredfold parameter ΔY of the airfoil leading edge sharpness Δy;

[0036] The conversion factor determination unit is used to determine the conversion factor X as:

[0037] X = A-BΔY′;

[0038] When ΔY<1.4, ΔY'=0, when 1.4≤ΔY≤.25, ΔY'=ΔY-1.4, when ΔY>2.5, ΔY'=1.1;

[0039]

[0040] Among them, Λ LE is the wing leading edge sweep angle.

[0041] Preferably, the wing maximum lift coefficient determination module includes:

[0042] The maximum lift coefficient determination unit is used to determine the maximum lift coefficient C of the airfoil using the following formula ymax :

[0043] C ymax =C ymaxb +ΔC ymax ;

[0044] Among them, parameter C ymaxbThe interpolation calculation is obtained in the first interpolation table constructed by the maximum thickness position of the airfoil and the hundred-fold parameter ΔY; the parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by one hundred times the airfoil camber and one hundred times the parameter ΔY.

[0045] Preferably, the wing maximum lift coefficient determination module includes:

[0046] The maximum lift coefficient correction amount determination unit is used to determine the maximum lift coefficient correction amount ΔC by the following formula Lmax :

[0047]

[0048] Among them, parameter C is obtained by interpolation calculation in the third interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY, and parameter D is obtained by interpolation calculation in the fourth interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY.

[0049] Preferably, in the stall angle determination module, the stall angle correction value Δα max The wing leading edge sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter ΔY.

[0050] A third aspect of the present application provides a computer device, including a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for determining the stall angle of attack of a high aspect ratio wing as described above.

[0051] A fourth aspect of the present application provides a readable storage medium, which stores a computer program. When the computer program is executed by a processor, it is used to implement the method for determining the stall angle of attack of a high aspect ratio wing as described above.

[0052] Based on the test data, this application deeply analyzes the influence of airfoil sensitive parameters, wing plane parameters and flight speed on the maximum lift coefficient and stall angle of attack. The new model not only reflects the influence of wing configuration parameters and flight speed, but also accurately reflects the influence of airfoil leading edge sharpness, maximum thickness position and airfoil curvature.

[0053] The application has high calculation efficiency and controllable calculation accuracy for large aspect ratio stall angle of attack. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] Figure 1 It is a flow chart of a preferred embodiment of the method for determining the stall angle of attack of a high aspect ratio wing of the present application.

[0055] Figure 2It is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of the present application. DETAILED DESCRIPTION

[0056] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0057] The first aspect of the present application provides a method for determining the stall angle of attack of a high aspect ratio wing, such as Figure 1 As shown, the method mainly includes:

[0058] Step S1, determine the maximum lift coefficient C of the wing Lmax :

[0059] C Lmax =XC ymax +ΔC Lmax ;

[0060] Where X is the conversion factor of the maximum lift coefficient from two dimensions to three dimensions, C ymax is the maximum lift coefficient of the airfoil, ΔC Lmax is the maximum lift coefficient correction;

[0061] Step S2: Determine the stall angle of attack α max :

[0062]

[0063] Among them, C Lα is the slope of the wing lift line, α L0 is the angle of attack for zero lift, Δα max is the stall angle of attack correction.

[0064] In some optional implementations, step S1 further includes:

[0065] Step S11, determining a hundred-fold parameter ΔY of the airfoil leading edge sharpness Δy;

[0066] Step S12: Determine the conversion factor X as:

[0067] X = A-BΔY′;

[0068] When ΔY<1.4, ΔY'=0, when 1.4≤ΔY≤.25, ΔY'=ΔY-1.4, when ΔY>2.5, ΔY'=1.1;

[0069]

[0070] Among them, Λ LE is the wing leading edge sweep angle.

[0071] In some optional implementations, step S1 further includes:

[0072] Step S13: Determine the maximum lift coefficient C of the airfoil using the following formula: ymax :

[0073] C ymax =C ymaxb +ΔC ymax ;

[0074] Among them, parameter C ymaxb The interpolation calculation is obtained in the first interpolation table constructed by the maximum thickness position of the airfoil and the hundred-fold parameter ΔY; the parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by one hundred times the airfoil camber and one hundred times the parameter ΔY.

[0075] In this embodiment, the first interpolation table is shown in Table 1, and the second interpolation table is shown in Table 2.

[0076] Table 1 Parameter C ymaxb Data required for interpolation calculation

[0077]

[0078] Among them, the maximum thickness position of the airfoil Xtm refers to the distance from the maximum thickness position of the airfoil to the leading edge, which is usually expressed as the ratio of the maximum thickness position to the chord. The first column in Table 1 is the maximum thickness position of the airfoil, the second row is the hundred-fold parameter ΔY, and the other data are the parameters C ymaxb Interpolation calculates the required data.

[0079] Table 2 Parameters ΔC ymax Data required for interpolation calculation

[0080]

[0081] The first column in Table 2 is the parameter 100f, the second row is the hundred-fold parameter ΔY, and the other data are the parameters ΔC ymax Interpolation calculates the required data.

[0082] In some optional implementations, step S1 further includes:

[0083] Step S14: Determine the maximum lift coefficient correction value ΔC by the following formula: Lmax :

[0084]

[0085] Among them, parameter C is obtained by interpolation calculation in the third interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY, and parameter D is obtained by interpolation calculation in the fourth interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY.

[0086] In this embodiment, the third interpolation table is shown in Table 3, and the fourth interpolation table is shown in Table 4.

[0087] Table 3 Data required for parameter C interpolation calculation

[0088]

[0089] The first column in Table 3 is the Mach number, the second row is the hundred-fold parameter ΔY, and the other data are the data required for the interpolation calculation of parameter C.

[0090] Table 4 Data required for parameter D interpolation calculation

[0091]

[0092] The first column in Table 4 is the Mach number, the second row is the hundred-fold parameter ΔY, and the other data are the data required for the interpolation calculation of the parameter D.

[0093] In some optional implementations, in step S2, the stall angle correction value Δα max The wing leading edge sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter ΔY.

[0094] In this embodiment, the fifth interpolation table is shown in Table 5.

[0095] Table 5 Parameters Δα max Data required for interpolation calculation

[0096]

[0097]

[0098] The first column in Table 5 is the hundred-fold parameter ΔY, and the second column is the wing leading edge sweep angle Λ LE , other data are the stall angle correction Δα max Interpolation calculates the required data.

[0099] This application uses subsonic lift calculation theory and a large number of wind tunnel tests, and based on the test data, deeply analyzes the influence of airfoil sensitive parameters, wing plane parameters and flight speed on the maximum lift coefficient and stall angle of attack, thereby constructing the above-mentioned multiple interpolation tables, and interpolating relevant calculation parameters based on these interpolation tables to accurately reflect the influence of the sharpness of the leading edge of the airfoil, the maximum thickness position and the curvature of the airfoil on the maximum lift coefficient and the stall angle of attack, so that the stall angle of attack can be calculated more accurately, improving the calculation accuracy and efficiency.

[0100] The second aspect of the present application provides a device for determining the stall angle of attack of a high aspect ratio wing corresponding to the above method, mainly comprising:

[0101] The wing maximum lift coefficient determination module is used to determine the wing maximum lift coefficient C Lmax :

[0102] C Lmax =XC ymax +ΔC Lmax ;

[0103] Where X is the conversion factor of the maximum lift coefficient from two dimensions to three dimensions, C ymax is the maximum lift coefficient of the airfoil, ΔC Lmax is the maximum lift coefficient correction;

[0104] Stall angle of attack determination module, used to determine the stall angle of attack α max :

[0105]

[0106] Among them, C Lα is the slope of the wing lift line, α L0 is the angle of attack for zero lift, Δα max is the stall angle of attack correction.

[0107] In some optional embodiments, the wing maximum lift coefficient determination module includes:

[0108] A hundredfold parameter determination unit, used to determine a hundredfold parameter ΔY of the airfoil leading edge sharpness Δy;

[0109] The conversion factor determination unit is used to determine the conversion factor X as:

[0110] X = A-BΔY′;

[0111] When ΔY<1.4, ΔY'=0, when 1.4≤ΔY≤.25, ΔY'=ΔY-1.4, when ΔY>2.5, ΔY'=1.1;

[0112]

[0113] Among them, Λ LE is the wing leading edge sweep angle.

[0114] In some optional embodiments, the wing maximum lift coefficient determination module includes:

[0115] The maximum lift coefficient determination unit is used to determine the maximum lift coefficient C of the airfoil using the following formula ymax :

[0116] C ymax =C ymaxb +ΔC ymax ;

[0117] Among them, parameter C ymaxb The interpolation calculation is obtained in the first interpolation table constructed by the maximum thickness position of the airfoil and the hundred-fold parameter ΔY; the parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by one hundred times the airfoil camber and one hundred times the parameter ΔY.

[0118] In some optional embodiments, the wing maximum lift coefficient determination module includes:

[0119] The maximum lift coefficient correction amount determination unit is used to determine the maximum lift coefficient correction amount ΔC by the following formula Lmax :

[0120]

[0121] Among them, parameter C is obtained by interpolation calculation in the third interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY, and parameter D is obtained by interpolation calculation in the fourth interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY.

[0122] In some optional embodiments, in the stall angle determination module, the stall angle correction value Δα max The wing leading edge sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter ΔY.

[0123] In a third aspect of the present application, a computer device includes a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement a method for determining a stall angle of attack of a high aspect ratio wing.

[0124] In a fourth aspect of the present application, a readable storage medium stores a computer program, and when the computer program is executed by a processor, it is used to implement the method for determining the stall angle of attack of a high aspect ratio wing as described above. The computer readable storage medium may be included in the device described in the above embodiment; or it may exist independently without being assembled into the device. The computer readable storage medium carries one or more programs, and when the one or more programs are executed by the device, the data is processed according to the above method.

[0125] Reference below Figure 2 , which shows a schematic structural diagram of a computer device 400 suitable for implementing the embodiments of the present application. Figure 2 The computer device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0126] like Figure 2 As shown, the computer device 400 includes a central processing unit (CPU) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage part 408 into a random access memory (RAM) 403. In the RAM 403, various programs and data required for the operation of the device 400 are also stored. The CPU 401, the ROM 402, and the RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0127] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, etc.; an output section 407 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc., and a speaker, etc.; a storage section 408 including a hard disk, etc.; and a communication section 409 including a network interface card such as a LAN card, a modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to the I / O interface 405 as needed. A removable medium 411, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., is installed on the drive 410 as needed, so that a computer program read therefrom is installed into the storage section 408 as needed.

[0128] In particular, according to the embodiment of the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiment of the present application includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 409, and / or installed from the removable medium 411. When the computer program is executed by the central processing unit (CPU) 401, the above functions defined in the method of the present application are executed. It should be noted that the computer storage medium of the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, - but not limited to - a system, device or device of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to, an electrical connection with one or more conductors, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present application, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, an apparatus or a device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in combination with an instruction execution system, an apparatus or a device. The program code contained on the computer-readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, optical cable, RF, etc., or any suitable combination of the above.

[0129] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present application. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0130] The modules or units involved in the embodiments described in this application may be implemented by software or hardware. The modules or units described may also be set in a processor, and the names of these modules or units do not constitute limitations on the modules or units themselves in some cases.

[0131] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for determining the stall angle of attack of a high aspect ratio wing, characterized in that: include: Step S1, determine the maximum lift coefficient C of the wing Lmax : C Lmax =XC ymax +ΔC Lmax ; Where X is the conversion factor of the maximum lift coefficient from two dimensions to three dimensions, C ymax is the maximum lift coefficient of the airfoil, ΔC Lmax is the maximum lift coefficient correction; Step S2: Determine the stall angle of attack α max : Among them, C Lα is the slope of the wing lift line, α L0 is the angle of attack for zero lift, Δα max is the stall angle of attack correction.

2. The method for determining the stall angle of attack of a high aspect ratio wing according to claim 1, characterized in that: Step S1 further comprises: Step S11, determining a hundred-fold parameter ΔY of the airfoil leading edge sharpness Δy; Step S12: Determine the conversion factor X as: X = A-B ΔY'; When ΔY<1.4, ΔY'=0, when .14≤ΔY≤.25, ΔY'=ΔY-1.4, when ΔY>2.5, ΔY'=1.1; Among them, Λ LE is the wing leading edge sweep angle.

3. The method for determining the stall angle of attack of a high aspect ratio wing according to claim 2, characterized in that: Step S1 further comprises: Step S13: Determine the maximum lift coefficient C of the airfoil using the following formula: ymax : C ymax =C ymaxb +ΔC ymax ; Among them, parameter C ymaxb The interpolation calculation is obtained in the first interpolation table constructed by the maximum thickness position of the airfoil and the hundred-fold parameter ΔY; the parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by one hundred times the airfoil camber and one hundred times the parameter ΔY.

4. The method for determining the stall angle of attack of a high aspect ratio wing according to claim 2, characterized in that: Step S1 further comprises: Step S14: Determine the maximum lift coefficient correction value ΔC by the following formula: Lmax : Among them, parameter C is obtained by interpolation calculation in the third interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY, and parameter D is obtained by interpolation calculation in the fourth interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY.

5. The method for determining the stall angle of attack of a high aspect ratio wing according to claim 2, characterized in that: In step S2, the stall angle correction value Δα max The wing leading edge sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter ΔY.

6. A device for determining the stall angle of attack of a high aspect ratio wing, characterized in that: include: The wing maximum lift coefficient determination module is used to determine the wing maximum lift coefficient C Lmax : C Lmax =XC ymax +ΔC Lmax ; Where X is the conversion factor of the maximum lift coefficient from two dimensions to three dimensions, C ymax is the maximum lift coefficient of the airfoil, ΔC Lmax is the maximum lift coefficient correction; Stall angle of attack determination module, used to determine the stall angle of attack α max : Among them, C Lα is the slope of the wing lift line, α L0 is the angle of attack for zero lift, Δα max is the stall angle of attack correction.

7. The high aspect ratio wing stall angle determination device according to claim 6, characterized in that: The wing maximum lift coefficient determination module comprises: A hundredfold parameter determination unit, used to determine a hundredfold parameter ΔY of the airfoil leading edge sharpness Δy; The conversion factor determination unit is used to determine the conversion factor X as: X = A-B ΔY'; When ΔY<1.4, ΔY'=0, when .14≤ΔY≤.25, ΔY'=ΔY-1.4, when ΔY>2.5, ΔY'=1.1; Among them, Λ LE is the wing leading edge sweep angle.

8. The device for determining the stall angle of attack of a high aspect ratio wing according to claim 7, characterized in that: The wing maximum lift coefficient determination module comprises: The maximum lift coefficient determination unit is used to determine the maximum lift coefficient C of the airfoil using the following formula ymax : C ymax =C ymaxb +ΔC ymax ; Among them, parameter C ymaxb The interpolation calculation is obtained in the first interpolation table constructed by the maximum thickness position of the airfoil and the hundred-fold parameter ΔY; the parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by one hundred times the airfoil camber and one hundred times the parameter ΔY.

9. The high aspect ratio wing stall angle determination device according to claim 7, characterized in that: The wing maximum lift coefficient determination module comprises: The maximum lift coefficient correction amount determination unit is used to determine the maximum lift coefficient correction amount ΔC by the following formula Lmax : Among them, parameter C is obtained by interpolation calculation in the third interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY, and parameter D is obtained by interpolation calculation in the fourth interpolation table constructed by the flight Mach number M and the hundred-fold parameter ΔY.

10. The device for determining the stall angle of attack of a high aspect ratio wing according to claim 7, characterized in that: In the stall angle determination module, the stall angle correction value Δα max The wing leading edge sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter ΔY.

11. A computer device, characterized in that: The method comprises a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for determining the stall angle of attack of a high aspect ratio wing according to any one of claims 1 to 5.

12. A readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, it is used to implement the method for determining the stall angle of attack of a high aspect ratio wing as described in any one of claims 1 to 5.

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