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

Abstract

The invention belongs to the technical field of flight control, and particularly relates to a low-aspect-ratio wing stall attack angle determination method and device. The method comprises the following steps: S1, interpolating a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table according to a wing tip-root ratio; s2, determining a first interpolation parameter CAB1 according to the first correction coefficient, and determining a second interpolation parameter CAB2 according to the second correction coefficient; s3, determining a wing stall attack angle basic value in a third interpolation table according to the first interpolation parameter CAB1; s4, determining stall attack angle correction in a fourth interpolation table according to the second interpolation parameter CAB2; and S5, determining the stall angle of attack according to the wing stall angle of attack basic value and the stall angle of attack correction. According to the method, the calculation efficiency of the stall incidence angle with the small aspect ratio is high, and the calculation precision is controllable.

Description

Technical Field

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

[0002] The maximum lift coefficient and stall angle of attack are important parameters for evaluating the maneuverability of fighter jets. The design of the aircraft's flight envelope and pitch control rate requires accurate data support for the maximum lift coefficient and stall angle of attack. The wing sweep angle, aspect ratio and flight speed have a significant impact on the maximum lift coefficient and stall angle of attack of a wing with a small aspect ratio. The leading edge sharpness and maximum thickness position of the airfoil are sensitive to the maximum lift coefficient and stall angle of attack. In addition, the influence of the wing tip-to-root ratio cannot be ignored. The theoretical algorithm used in the existing technology does not take these parameters into account. The theoretical calculation value is far from the actual data, and the calculation accuracy is low. 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 wing with a small aspect ratio, providing technical support for the wing configuration parameter design, airfoil sensitive parameter design, and lift and stall characteristic evaluation of the aircraft high-speed configuration of a small aspect ratio aircraft.

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

[0005] Step S1, interpolating a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table respectively according to the wing tip-to-root ratio λ;

[0006] Step S2, determining a first interpolation parameter CAB1 according to the first correction coefficient, and determining a second interpolation parameter CAB2 according to the second correction coefficient;

[0007] Step S3: Determine the basic value of the wing stall angle of attack α in the third interpolation table according to the first interpolation parameter CAB1. maxb ;

[0008] Step S4: Determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2 max ;

[0009] Step S5: according to the basic value α of the wing stall angle of attack maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

[0010] Preferably, in step S2, the first interpolation parameter CAB1 is determined by the following formula:

[0011]

[0012] When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

[0013] Preferably, in step S2, the second interpolation parameter CAB2 is determined by the following formula:

[0014] CAB2=(C 2+1)ARtanΛ LE .

[0015] Preferably, in step S4, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, wherein the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is the Mach number M a , the second interpolation parameter CAB2 and the stall angle correction Δα max Constructed two-dimensional interpolation table;

[0016] When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ;

[0017] Where, ASH = AR cosΛ LE (1+4λ 2 ).

[0018] A second aspect of the present application provides a device for determining a stall angle of attack of a wing with a small aspect ratio, comprising:

[0019] A correction coefficient interpolation module, used for interpolating a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table respectively according to the wing tip-root ratio λ;

[0020] An interpolation parameter calculation module, used to determine a first interpolation parameter CAB1 according to a first correction coefficient, and to determine a second interpolation parameter CAB2 according to a second correction coefficient;

[0021] A wing stall angle of attack basic value determination module is used to determine the wing stall angle of attack basic value α in the third interpolation table according to the first interpolation parameter CAB1 maxb ;

[0022] A stall angle correction value determination module is used to determine the stall angle correction value Δα in a fourth interpolation table according to the second interpolation parameter CAB2 max ;

[0023] The stall angle determination module is used to determine the stall angle of attack of the wing according to the basic value α maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

[0024] Preferably, in the interpolation parameter calculation module, the first interpolation parameter CAB1 is determined by the following formula:

[0025]

[0026] When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

[0027] Preferably, in the interpolation parameter calculation module, the second interpolation parameter CAB2 is determined by the following formula:

[0028] CAB2=(C2+1)ARtanΛ LE .

[0029] Preferably, in the stall angle correction amount determination module, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, and the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction amount Δα max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is the Mach number M a , the second interpolation parameter CAB2 and the stall angle correction Δα max Constructed two-dimensional interpolation table;

[0030] When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ;

[0031] Where, ASH = AR cosΛ LE (1+4λ2 ).

[0032] 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 low aspect ratio wing as described above.

[0033] 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 small aspect ratio wing as described above.

[0034] Based on the test data, this application deeply analyzes the influence of airfoil sensitive parameters, wing plane parameters and flight speed on the stall angle of attack. It reflects the influence of wing configuration parameters and flight speed on the stall angle of attack.

[0035] The application has high calculation efficiency and controllable calculation accuracy for small aspect ratio stall angle of attack. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 It is a flow chart of a preferred embodiment of the method for determining the stall angle of attack of a wing with a small aspect ratio of the present application.

[0037] Figure 2 It is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of the present application. DETAILED DESCRIPTION

[0038] 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.

[0039] The first aspect of the present application provides a method for determining the stall angle of attack of a wing with a small aspect ratio, such as Figure 1 As shown, the method mainly includes:

[0040] Step S1, interpolating a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table respectively according to the wing tip-to-root ratio λ;

[0041] Step S2, determining a first interpolation parameter CAB1 according to the first correction coefficient, and determining a second interpolation parameter CAB2 according to the second correction coefficient;

[0042] Step S3: Determine the basic value of the wing stall angle of attack α in the third interpolation table according to the first interpolation parameter CAB1. maxb ;

[0043] Step S4: Determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2 max ;

[0044] Step S5: according to the basic value α of the wing stall angle of attack maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

[0045] The first correction coefficient C1 and the second correction coefficient C2 of step S1 of the present application are both obtained by interpolating the single parameter of the wing tip-to-root ratio λ. Table 1 below gives a first interpolation table for representing the relationship between the wing tip-to-root ratio λ and the first correction coefficient C1, and Table 2 gives a second interpolation table for representing the relationship between the wing tip-to-root ratio λ and the second correction coefficient C2.

[0046] Table 1 The first interpolation table

[0047] λ C1 0 0 0.1 0.24 0.2 0.494 0.3 0.5 0.4 0.48 0.6 0.21 0.8 0.09 1 0

[0048] Table 2 Second interpolation table

[0049]

[0050]

[0051] In some optional implementations, in step S2, the first interpolation parameter CAB1 is determined by the following formula:

[0052]

[0053] When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

[0054] In some optional implementations, in step S2, the second interpolation parameter CAB2 is determined by the following formula:

[0055] CAB2=(C2+1)ARtanΛ LE .

[0056] Then in step S3, the third interpolation table is shown in Table 3 below. According to the first interpolation parameter CAB1, the basic value of the wing stall angle of attack α can be directly interpolated. maxb .

[0057] Table 3 Data required for interpolation calculation of basic stall angle of attack

[0058] CAB1 0 0.4 0.8 1 1.2 1.6 2 2.5 3 <![CDATA[α maxb ]]> 35 35 35 34 32 28 25 23 22

[0059] In some optional embodiments, in step S4, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, wherein the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα. max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is the Mach number M a , the second interpolation parameter CAB2 and the stall angle correction Δα max Constructed two-dimensional interpolation table;

[0060] When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ;

[0061] Where, ASH = AR cosΛ LE (1+4λ 2) .

[0062] Table 4 gives the fourth ASH interpolation table, and Table 5 gives the fourth Mach number interpolation table. In Table 4, the first column of data is the ASH parameter, the second row of data is the second interpolation parameter CAB2, and the other data is the stall angle correction Δα max In Table 5, the first column of data is the Mach number, the second row of data is the second interpolation parameter CAB2, and the other data is the stall angle correction Δα max .

[0063] Table 4 Fourth ASH interpolation table

[0064]

[0065] Table 5 Interpolation table of the fourth Mach number

[0066]

[0067] This application uses supersonic lift calculation theory and a large number of wind tunnel tests to deeply analyze the effects of airfoil sensitive parameters, wing plane parameters and flight speed on the stall angle of attack based on test data, thereby constructing the above-mentioned multiple interpolation tables, and interpolating relevant calculation parameters based on these interpolation tables to accurately reflect the influence of wing configuration on the stall angle of attack, so that the stall angle of attack can be calculated more accurately, improving the calculation accuracy and efficiency.

[0068] The second aspect of the present application provides a device for determining the stall angle of attack of a wing with a small aspect ratio corresponding to the above method, mainly comprising:

[0069] A correction coefficient interpolation module, used for interpolating a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table respectively according to the wing tip-root ratio λ;

[0070] An interpolation parameter calculation module, used to determine a first interpolation parameter CAB1 according to a first correction coefficient, and to determine a second interpolation parameter CAB2 according to a second correction coefficient;

[0071] A wing stall angle of attack basic value determination module is used to determine the wing stall angle of attack basic value α in the third interpolation table according to the first interpolation parameter CAB1 maxb ;

[0072] A stall angle correction value determination module is used to determine the stall angle correction value Δα in a fourth interpolation table according to the second interpolation parameter CAB2 max ;

[0073] The stall angle determination module is used to determine the stall angle of attack of the wing according to the basic value α maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

[0074] In some optional implementations, in the interpolation parameter calculation module, the first interpolation parameter CAB1 is determined by the following formula:

[0075]

[0076] When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

[0077] In some optional implementations, in the interpolation parameter calculation module, the second interpolation parameter CAB2 is determined by the following formula:

[0078] CAB2=(C2+1)ARtanΛ LE .

[0079] In some optional embodiments, in the stall angle correction value determination module, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, and the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is the Mach number M a , the second interpolation parameter CAB2 and the stall angle correction Δα max Constructed two-dimensional interpolation table;

[0080] When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ;

[0081] Where, ASH = AR cosΛ LE (1+4λ 2 ).

[0082] 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 wing with a small aspect ratio.

[0083] 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 low 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.

[0084] 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.

[0085] like Figure 2As 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.

[0086] 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.

[0087] 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.

[0088] 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.

[0089] 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.

[0090] 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 wing with a small aspect ratio, characterized in that: include: Step S1, interpolating a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table respectively according to the wing tip-to-root ratio λ; Step S2, determining a first interpolation parameter CAB1 according to the first correction coefficient, and determining a second interpolation parameter CAB2 according to the second correction coefficient; Step S3: Determine the basic value of the wing stall angle of attack α in the third interpolation table according to the first interpolation parameter CAB1. maxb ; Step S4: Determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2 max ; Step S5: according to the basic value α of the wing stall angle of attack maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

2. The method for determining the stall angle of attack of a low aspect ratio wing according to claim 1, characterized in that: In step S2, the first interpolation parameter CAB1 is determined by the following formula: When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

3. The method for determining the stall angle of attack of a low aspect ratio wing according to claim 1, characterized in that: In step S2, the second interpolation parameter CAB2 is determined by the following formula: CAB2=(C 2+1)ARtanΛ LE 。 4. The method for determining the stall angle of attack of a low aspect ratio wing according to claim 1, characterized in that: In step S4, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, wherein the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is the Mach number M a , the second interpolation parameter CAB2 and the stall angle correction Δα max Constructed two-dimensional interpolation table; When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ; Where, ASH = AR cosΛ LE (1+4λ 2 ).

5. A device for determining the stall angle of attack of a wing with a small aspect ratio, characterized in that: include: A correction coefficient interpolation module, used for interpolating a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table respectively according to the wing tip-root ratio λ; An interpolation parameter calculation module, used to determine a first interpolation parameter CAB1 according to a first correction coefficient, and to determine a second interpolation parameter CAB2 according to a second correction coefficient; A wing stall angle of attack basic value determination module is used to determine the wing stall angle of attack basic value α in the third interpolation table according to the first interpolation parameter CAB1 maxb ; A stall angle correction value determination module is used to determine the stall angle correction value Δα in a fourth interpolation table according to the second interpolation parameter CAB2 max ; The stall angle determination module is used to determine the stall angle of attack of the wing according to the basic value α maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

6. The device for determining the stall angle of attack of a wing with a low aspect ratio as claimed in claim 5, characterized in that: In the interpolation parameter calculation module, the first interpolation parameter CAB1 is determined by the following formula: When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

7. The device for determining the stall angle of attack of a wing with a low aspect ratio as claimed in claim 5, characterized in that: In the interpolation parameter calculation module, the second interpolation parameter CAB2 is determined by the following formula: CAB2=(C2+1)ARtanΛ LE 。 8. The device for determining the stall angle of attack of a wing with a low aspect ratio as claimed in claim 5, characterized in that: In the stall angle correction determination module, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, wherein the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction Δα. max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is the Mach number M a , the second interpolation parameter CAB2 and the stall angle correction Δα max Constructed two-dimensional interpolation table; When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ; Where, ASH = AR cosΛ LE (1+4λ 2 ).

9. 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 small aspect ratio wing according to any one of claims 1 to 4.

10. 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 low aspect ratio wing as described in any one of claims 1 to 4.

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