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

Abstract

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

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 an aircraft's flight envelope and pitch control rate requires accurate data on the maximum lift coefficient and stall angle of attack. The airfoil's leading edge sharpness, camber, and maximum thickness position are highly sensitive to the maximum lift coefficient and stall angle of attack of high-aspect-ratio wings. These factors are also closely related to the wing's planform parameters and flight speed. The theoretical algorithms used in existing technologies are significantly different from actual data, resulting in 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 high-speed aircraft configurations.

[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 from two-dimensional to three-dimensional maximum lift coefficient, 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 hundredfold parameter ΔY of the airfoil leading edge sharpness Δy;

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

[0014] X = A - B Δ Y ′;

[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 Obtained by interpolation calculation in the first interpolation table constructed by the position of the maximum thickness of the airfoil and the hundred-fold parameter ΔY; parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by the hundred-fold airfoil camber and the hundred-fold parameter ΔY.

[0022] Preferably, step S1 further comprises:

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

[0024]

[0025] Among them, parameter C is obtained by interpolation calculation in a 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 a 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 sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter ΔY.

[0027] A 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] Wing maximum lift coefficient determination module, used to determine the wing maximum lift coefficient CLmax :

[0029] C Lmax =XC ymax +ΔC Lmax ;

[0030] Where X is the conversion factor from two-dimensional to three-dimensional maximum lift coefficient, 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 - B Δ Y ′;

[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 ymaxbObtained by interpolation calculation in the first interpolation table constructed by the position of the maximum thickness of the airfoil and the hundred-fold parameter ΔY; parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by the hundred-fold airfoil camber and the hundred-fold parameter ΔY.

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

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

[0047]

[0048] Among them, parameter C is obtained by interpolation calculation in a 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 a 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 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, comprising 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] In a fourth aspect, the present application provides a readable storage medium storing 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 experimental data, this application thoroughly analyzes the effects of airfoil-sensitive parameters, wing planform 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 effects of airfoil leading edge sharpness, maximum thickness location, and airfoil camber.

[0053] The present 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 This 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 structural diagram of a computer device suitable for implementing the embodiments of the present application. DETAILED DESCRIPTION

[0056] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers 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 should not 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 conjunction 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 from two-dimensional to three-dimensional maximum lift coefficient, 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 embodiments, step S1 further includes:

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

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

[0067] X = A - B Δ Y ′;

[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 embodiments, 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 Obtained by interpolation calculation in the first interpolation table constructed by the position of the maximum thickness of the airfoil and the hundred-fold parameter ΔY; parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by the hundred-fold airfoil camber and the hundred-fold 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 hundredfold parameter ΔY, and the other data are parameters C ymaxb Interpolation calculation 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 parameters ΔC ymax Interpolation calculation required data.

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

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

[0084]

[0085] Among them, parameter C is obtained by interpolation calculation in a 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 a 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 the 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 embodiments, in step S2, the stall angle correction value Δα max The 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 hundredfold parameter ΔY, and the second column is the wing leading edge sweep angle Λ LE , other data are stall angle correction value Δα max Interpolation calculation required data.

[0099] This application uses subsonic 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 maximum lift coefficient and stall angle of attack based on test data, thereby constructing the above-mentioned multiple interpolation tables. Based on these interpolation tables, relevant calculation parameters are interpolated to accurately reflect the effects of the airfoil leading edge sharpness, maximum thickness position, and airfoil camber on the maximum lift coefficient and stall angle of attack, thereby enabling more accurate calculation of the stall angle of attack and improving calculation accuracy and efficiency.

[0100] A 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] Wing maximum lift coefficient determination module, used to determine the wing maximum lift coefficient C Lmax :

[0102] C Lmax =XC ymax +ΔC Lmax ;

[0103] Where X is the conversion factor from two-dimensional to three-dimensional maximum lift coefficient, 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 - B Δ Y ′;

[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 Obtained by interpolation calculation in the first interpolation table constructed by the position of the maximum thickness of the airfoil and the hundred-fold parameter ΔY; parameter ΔC ymax It is obtained by interpolation calculation in the second interpolation table constructed by the hundred-fold airfoil camber and the hundred-fold parameter ΔY.

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

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

[0120]

[0121] Among them, parameter C is obtained by interpolation calculation in a 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 a 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 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, the present application provides a readable storage medium storing a computer program that, when executed by a processor, implements 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 apparatus described in the above embodiments, or it may exist independently and not incorporated into the apparatus. The computer-readable storage medium carries one or more programs, and when executed by the apparatus, the one or more programs process data according to the method described above.

[0125] Reference below Figure 2 , which shows a 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 limit the functions and scope of use of the embodiments of the present application.

[0126] like Figure 2 As shown, 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 portion 408 into a random access memory (RAM) 403. Various programs and data required for the operation of device 400 are also stored in RAM 403. CPU 401, ROM 402, and RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to bus 404.

[0127] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, and the like; an output section 407 including devices such as a cathode ray tube (CRT), a liquid crystal display (LCD), and a speaker; a storage section 408 including a hard disk; and a communication section 409 including a network interface card such as a LAN card or a modem. 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. Removable media 411, such as a magnetic disk, an optical disk, a magneto-optical disk, or a semiconductor memory, is installed in the drive 410 as needed, so that computer programs read therefrom can be 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 component 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 having one or more conductors, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this application, a computer-readable storage medium may be any tangible medium that contains or stores a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, which carries computer-readable program code. Such a propagated data signal may take a variety of forms, including, but not limited to, electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium that can transmit, propagate, or transfer a program for use by or in conjunction with an instruction execution system, apparatus, or device. The program code embodied on a computer-readable medium may be transmitted using any suitable medium, including, but not limited to, wireless, wire, optical cable, RF, etc., or any suitable combination thereof.

[0129] The flow charts and block diagrams in the accompanying drawings illustrate the possible architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present application. In this regard, each box in the flow chart or block diagram can represent a module, program segment or a part of code, and the module, program segment or a part of code includes one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a sequence different from that marked in the accompanying drawings. For example, two 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 box in the block diagram and / or flow chart, and the combination of the boxes in the block diagram and / or flow chart can be implemented by a dedicated hardware-based system that performs the specified function or operation, or can be implemented by a combination of dedicated hardware and computer instructions.

[0130] The modules or units described in the embodiments of this application may be implemented in software or hardware. The modules or units described may also be provided in a processor, and the names of these modules or units do not, in certain circumstances, limit the modules or units themselves.

[0131] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection 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 +△C Lmax ; Where X is the conversion factor from two-dimensional to three-dimensional maximum lift coefficient, C ymax is the maximum lift coefficient of the airfoil, △C 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, △α max is the stall angle of attack correction; Wherein, step S1 further includes: Step S11, determining a hundred-fold parameter ΔY of the airfoil leading edge sharpness Δy; Step S12: Determine the conversion factor X: X=AB△Y'; When △Y<1.4, △Y'=0, when 1.4≤△Y≤2.5, △Y'=△Y-1.4, when △Y>2.5, △Y'=1.1; Among them, Λ LE is the wing leading edge sweep angle.

2. The method for determining the stall angle of attack of a high aspect ratio wing according to claim 1, wherein: Step S1 further comprises: Step S13: Determine the maximum lift coefficient C of the airfoil using the following formula: ymax : C ymax =C ymaxb +△C ymax ; Among them, parameter C ymaxb Obtained by interpolation calculation in the first interpolation table constructed by the position of the maximum thickness of the airfoil and the hundred-fold parameter △Y; parameter △C ymax It is obtained by interpolation calculation in the second interpolation table constructed by hundred-fold airfoil camber and hundred-fold parameter △Y.

3. The method for determining the stall angle of attack of a high aspect ratio wing according to claim 1, wherein: Step S1 further comprises: Step S14: Determine the maximum lift coefficient correction value ΔC using 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 △Y, 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 △Y.

4. The method for determining the stall angle of attack of a high aspect ratio wing according to claim 1, wherein: In step S2, the stall angle correction value Δα max The sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter △Y.

5. A device for determining the stall angle of attack of a high aspect ratio wing, characterized in that: include: Wing maximum lift coefficient determination module, used to determine the wing maximum lift coefficient C Lmax : C Lmax =XC ymax +△C Lmax ; Where X is the conversion factor from two-dimensional to three-dimensional maximum lift coefficient, C ymax is the maximum lift coefficient of the airfoil, △C 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, △α max is the stall angle of attack correction; Wherein, the wing maximum lift coefficient determination module includes: A hundredfold parameter determination unit, used to determine the hundredfold parameter △Y of the airfoil leading edge sharpness △y; The conversion factor determination unit is used to determine the conversion factor X as: X=AB△Y'; When △Y<1.4, △Y'=0, when 1.4≤△Y≤2.5, △Y'=△Y-1.4, when △Y>2.5, △Y'=1.1; Among them, Λ LE is the wing leading edge sweep angle.

6. The high aspect ratio wing stall angle determination device according to claim 5, characterized in that: The wing maximum lift coefficient determination module includes: 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 +△C ymax ; Among them, parameter C ymaxb Obtained by interpolation calculation in the first interpolation table constructed by the position of the maximum thickness of the airfoil and the hundred-fold parameter △Y; parameter △C ymax It is obtained by interpolation calculation in the second interpolation table constructed by hundred-fold airfoil camber and hundred-fold parameter △Y.

7. The high aspect ratio wing stall angle determination device according to claim 5, characterized in that: The wing maximum lift coefficient determination module includes: The maximum lift coefficient correction value determination unit is used to determine the maximum lift coefficient correction value △C 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 △Y, 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 △Y.

8. The high aspect ratio wing stall angle determination device according to claim 5, characterized in that: In the stall angle determination module, the stall angle correction value Δα max The sweep angle Λ LE , and is obtained by interpolation calculation in the fifth interpolation table constructed with the hundredfold parameter △Y.

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

Images