Method and device for calculating transverse static stability derivative of cruise configuration wing

Abstract

The invention belongs to the technical field of aircraft design, and relates to a cruise configuration wing transverse static stability derivative calculation method and device. The method comprises the following steps: S1, determining a transverse static stability derivative generated by wing plane parameters, when the wing is a triangular wing, calculating a transverse static stability derivative of the triangular wing according to a lift coefficient and a wing aspect ratio, and when the wing is a trapezoidal wing, calculating a transverse static stability derivative of the triangular wing; calculating the transverse static stability derivative of the trapezoidal wing according to the compressibility correction factor and the transverse static stability derivative generated by the wing in the incompressible flow; and S2, determining a transverse static stability derivative generated by the dihedral angle of the wing. The calculation model reflects the influence of the speed, the lift coefficient, the airfoil lift characteristic, the wing dihedral angle, the wing aspect ratio, the tip root ratio and the sweepback angle on the transverse static stability, and the transverse static stability derivative of the cruise configuration wing can be accurately calculated.

Description

Technical Field

[0001] This application belongs to the field of aircraft design technology, and specifically relates to a method and apparatus for calculating the lateral static stability derivative of a cruise configuration wing. Background Technology

[0002] The wing is a key component determining the lateral static stability of an aircraft. The sensitive parameters for lateral static stability differ significantly between supersonic, low-aspect-ratio delta wings and subsonic trapezoidal wings. Furthermore, the lateral static stability of wings for high-speed cruise requires aerocompressibility correction. The lateral static stability of a wing is related not only to wing planar parameters such as aspect ratio, tip-root ratio, and sweep angle, but also to the dihedral angle, the lift line slope of the airfoil, the flight Mach number, the lift coefficient, and the location of the wing's center of pressure. Due to the numerous factors influencing wing lateral static stability, its calculation model is complex. Therefore, accurately constructing a lateral static stability derivative calculation model for wings to guide wing structural optimization is a pressing technical problem that needs to be solved. Summary of the Invention

[0003] To address the aforementioned issues, this application provides a method and apparatus for calculating the lateral static stability derivative of a cruise-configuration wing, which can provide technical support for the calculation and evaluation of the lateral static stability of aircraft.

[0004] The first aspect of this application provides a method for calculating the lateral static stability derivative of a cruise-configuration airfoil, mainly including:

[0005] Step S1: Determine the lateral static stability derivative generated by the wing plane parameters. When the wing is a triangular wing, calculate the lateral static stability derivative of the triangular wing based on the lift coefficient and the wing aspect ratio. When the wing is a trapezoidal wing, calculate the lateral static stability derivative of the trapezoidal wing based on the compressibility correction factor and the lateral static stability derivative generated by the wing in the incompressible flow.

[0006] Step S2: Determine the lateral static stability derivative generated by the dihedral angle on the wing.

[0007] Preferably, in step S1, the lateral static stability derivative of the delta wing is calculated using the following formula:

[0008] ;

[0009] in, For the wing aspect ratio, This is the lift coefficient.

[0010] Preferably, in step S1, the lateral static stability derivative of the trapezoidal wing is calculated using the following formula. :

[0011] ;

[0012] in, It is a compressibility correction factor. This is the lateral static stability derivative generated by the wing in an incompressible flow.

[0013] Preferably, the lateral static stability derivative generated by the wing in the incompressible flow is calculated using the following formula. :

[0014] ;

[0015] in, The lift coefficient, For the lateral static stability derivative of the incompressible flow in a straight airfoil, This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

[0016] Preferably, the parameters are calculated using the following formula. :

[0017] ;

[0018] in, ;

[0019] ;

[0020] The wing root ratio.

[0021] Preferably, the parameters are calculated using the following formula. :

[0022] ;

[0023] in, ;

[0024] ;

[0025] ;

[0026] in, This indicates the location of the wing's aerodynamic pressure center.

[0027] Preferably, in a given two-dimensional interpolation table, a compressibility correction factor is interpolated based on a given Mach number correction parameter and the wing aspect ratio, wherein the Mach number correction parameter... Calculated using the following formula:

[0028] .

[0029] Preferably, in step S2, the lateral static stability derivative generated by the dihedral angle of the wing is calculated using the following formula. :

[0030] ;

[0031] in, The dihedral angle of the wing. For wing parameters;

[0032] ;

[0033] ;

[0034] in, The lift line slope of the Mach number M airfoil;

[0035] In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula:

[0036] ;

[0037] Second correction parameter Calculated using the following formula:

[0038] ;

[0039] in, It is the sweep angle of the wing's quarter chord.

[0040] The second aspect of this application provides a device for calculating the lateral static stability derivative of a cruise-configuration airfoil, mainly comprising:

[0041] The module for determining the lateral static stability derivative generated by the wing plane parameters is used to determine the lateral static stability derivative generated by the wing plane parameters. When the wing is a triangular wing, the lateral static stability derivative of the triangular wing is calculated based on the lift coefficient and the wing aspect ratio. When the wing is a trapezoidal wing, the lateral static stability derivative of the trapezoidal wing is calculated based on the compressibility correction factor and the lateral static stability derivative generated by the wing in the incompressible flow.

[0042] The module for the lateral static stability derivative generated by the dihedral angle of the wing is used to determine the lateral static stability derivative generated by the dihedral angle of the wing.

[0043] Preferably, in the module for determining the lateral static stability derivative generated by the wing planar parameters, the lateral static stability derivative of the delta wing is calculated using the following formula:

[0044] ;

[0045] in, For the wing aspect ratio, This is the lift coefficient.

[0046] Preferably, in the module for determining the lateral static stability derivative generated by the wing planar parameters, the lateral static stability derivative of the trapezoidal wing is calculated using the following formula. :

[0047] ;

[0048] in, It is a compressibility correction factor. This is the lateral static stability derivative generated by the wing in an incompressible flow.

[0049] Preferably, the lateral static stability derivative generated by the wing in the incompressible flow is calculated using the following formula. :

[0050] ;

[0051] in, The lift coefficient, For the lateral static stability derivative of the incompressible flow in a straight airfoil, This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

[0052] Preferably, the parameters are calculated using the following formula. :

[0053] ;

[0054] in, ;

[0055] ;

[0056] The wing root ratio.

[0057] Preferably, the parameters are calculated using the following formula. :

[0058] ;

[0059] in, ;

[0060] ;

[0061] ;

[0062] in, This indicates the location of the wing's aerodynamic pressure center.

[0063] Preferably, in a given two-dimensional interpolation table, a compressibility correction factor is interpolated based on a given Mach number correction parameter and the wing aspect ratio, wherein the Mach number correction parameter... Calculated using the following formula:

[0064] .

[0065] Preferably, in the module for calculating the lateral static stability derivative generated by the dihedral angle of the wing, the lateral static stability derivative generated by the dihedral angle of the wing is calculated using the following formula. :

[0066] ;

[0067] in, The dihedral angle of the wing. For wing parameters;

[0068] ;

[0069] ;

[0070] in, The lift line slope of the Mach number M airfoil;

[0071] In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula:

[0072] ;

[0073] Second correction parameter Calculated using the following formula:

[0074] ;

[0075] in, It is the sweep angle of the wing's quarter chord.

[0076] A third aspect of this 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 calculating the lateral static stability derivative of a cruise configuration wing as described above.

[0077] A fourth aspect of this application provides a readable storage medium storing a computer program that, when executed by a processor, is used to implement the method for calculating the lateral static stability derivative of a cruise configuration wing as described above.

[0078] The calculation model in this application reflects the influence of speed, lift coefficient, airfoil lift characteristics, wing dihedral angle, wing aspect ratio, tip root ratio and sweep angle on lateral static stability, and can accurately calculate the lateral static stability derivative of cruise configuration wings. Attached Figure Description

[0079] Figure 1 This is a flowchart of a preferred embodiment of the method for calculating the lateral static stability derivative of a cruise configuration wing according to this application.

[0080] Figure 2 This is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of this application. Detailed Implementation

[0081] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0082] The first aspect of this application provides a method for calculating the lateral static stability derivative of a cruise-configuration airfoil, such as... Figure 1 As shown, it mainly includes:

[0083] Step S1: Determine the lateral static stability derivative generated by the wing plane parameters. When the wing is a triangular wing, calculate the lateral static stability derivative of the triangular wing based on the lift coefficient and the wing aspect ratio. When the wing is a trapezoidal wing, calculate the lateral static stability derivative of the trapezoidal wing based on the compressibility correction factor and the lateral static stability derivative generated by the wing in the incompressible flow.

[0084] Step S2: Determine the lateral static stability derivative generated by the dihedral angle on the wing.

[0085] Step S1 provides a calculation model for the lateral static stability derivative generated by the wing plane parameters.

[0086] In some alternative implementations, in step S1, the lateral static stability derivative of the delta wing is calculated using the following formula:

[0087] ;

[0088] in, For the wing aspect ratio, This is the lift coefficient.

[0089] In some alternative implementations, in step S1, the lateral static stability derivative of the trapezoidal wing is calculated using the following formula. :

[0090] ;

[0091] in, It is a compressibility correction factor. This is the lateral static stability derivative generated by the wing in an incompressible flow.

[0092] In some alternative implementations, the lateral static stability derivative generated by the wing in the incompressible flow is calculated using the following formula. :

[0093] ;

[0094] in, The lift coefficient, For the lateral static stability derivative of the incompressible flow in a straight airfoil, This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

[0095] In some alternative implementations, the parameters are calculated using the following formula. :

[0096] ;

[0097] in, ;

[0098] ;

[0099] The wing root ratio.

[0100] In some alternative implementations, the parameters are calculated using the following formula. :

[0101] ;

[0102] in, ;

[0103] ;

[0104] ;

[0105] in, This indicates the location of the wing's aerodynamic pressure center.

[0106] In some alternative implementations, a compressibility correction factor is interpolated from a given two-dimensional interpolation table, as shown in Table 1, based on a given Mach number correction parameter and the wing aspect ratio. Calculated using the following formula:

[0107] .

[0108] Table 1. Data required for compressibility correction factor interpolation calculation

[0109]

[0110] Step S2 is used to generate the lateral static stability derivative of the dihedral angle on the computer wing.

[0111] In some alternative implementations, in step S2, the lateral static stability derivative generated by the dihedral angle of the wing is calculated using the following formula. :

[0112] ;

[0113] in, The dihedral angle of the wing. For wing parameters;

[0114] ;

[0115] ;

[0116] in, The lift line slope of the Mach number M airfoil;

[0117] In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula:

[0118] ;

[0119] Second correction parameter Calculated using the following formula:

[0120] ;

[0121] in, It is the sweep angle of the wing's quarter chord.

[0122] In this embodiment, the three-dimensional interpolation table provides different wing tip root ratios. There is a corresponding two-dimensional interpolation table. Here, only the two-dimensional data table for λ=0.25 is given as an example, as shown in Table 2.

[0123] Table 2 Zv interpolation data (λ=0.5)

[0124]

[0125] The example aircraft has an aspect ratio of 7.6, a tip-to-root ratio of 0.246, a quarter-chord sweep angle of 30°, a half-chord sweep angle of 26.46°, and an anhedral angle of 3°.

[0126] Calculation conditions: Flight Mach number is 0.78, and the lift line slope of the airfoil at Mach 0.78 is 8.44 / rsd. The procedure for calculating the lateral static stability derivative of an airfoil with a lift coefficient of 0.5 is as follows:

[0127] (1) The lateral static stability derivative generated by the computer wing plane parameters is -0.0704 / rad.

[0128] (2) The lateral static stability derivative generated by the dihedral angle of the computer wing is -0.042 / rad.

[0129] The second aspect of this application provides a device for calculating the lateral static stability derivative of a cruise configuration wing corresponding to the above method, mainly comprising:

[0130] The module for determining the lateral static stability derivative generated by the wing plane parameters is used to determine the lateral static stability derivative generated by the wing plane parameters. When the wing is a triangular wing, the lateral static stability derivative of the triangular wing is calculated based on the lift coefficient and the wing aspect ratio. When the wing is a trapezoidal wing, the lateral static stability derivative of the trapezoidal wing is calculated based on the compressibility correction factor and the lateral static stability derivative generated by the wing in the incompressible flow.

[0131] The module for the lateral static stability derivative generated by the dihedral angle of the wing is used to determine the lateral static stability derivative generated by the dihedral angle of the wing.

[0132] In some alternative implementations, in the module for determining the lateral static stability derivative generated by the wing planar parameters, the lateral static stability derivative of the delta wing is calculated using the following formula:

[0133] ;

[0134] in, For the wing aspect ratio, This is the lift coefficient.

[0135] In some alternative implementations, in the module for determining the lateral static stability derivative generated by the wing plane parameters, the lateral static stability derivative of the trapezoidal wing is calculated using the following formula. :

[0136] ;

[0137] in, It is a compressibility correction factor. This is the lateral static stability derivative generated by the wing in an incompressible flow.

[0138] In some alternative implementations, the lateral static stability derivative generated by the wing in the incompressible flow is calculated using the following formula. :

[0139] ;

[0140] in, The lift coefficient, For the lateral static stability derivative of the incompressible flow in a straight airfoil, This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

[0141] In some alternative implementations, the parameters are calculated using the following formula. :

[0142] ;

[0143] in, ;

[0144] ;

[0145] The wing root ratio.

[0146] In some alternative implementations, the parameters are calculated using the following formula. :

[0147] ;

[0148] in, ;

[0149] ;

[0150] ;

[0151] in, This indicates the location of the wing's aerodynamic pressure center.

[0152] In some alternative implementations, a compressibility correction factor is interpolated from a given two-dimensional interpolation table based on a given Mach number correction parameter and the wing aspect ratio, wherein the Mach number correction parameter... Calculated using the following formula:

[0153] .

[0154] In some alternative implementations, in the module for calculating the lateral static stability derivative of the wing dihedral, the lateral static stability derivative of the wing dihedral is calculated using the following formula. :

[0155] ;

[0156] in, The dihedral angle of the wing. For wing parameters;

[0157] ;

[0158] ;

[0159] in, The lift line slope of the Mach number M airfoil;

[0160] In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula:

[0161] ;

[0162] Second correction parameter Calculated using the following formula:

[0163] ;

[0164] in, It is the sweep angle of the wing's quarter chord.

[0165] In a third aspect of this application, a computer device is provided, 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 calculating the lateral static stability derivative of a cruise configuration wing as described above.

[0166] In a fourth aspect, this application provides a readable storage medium storing a computer program that, when executed by a processor, implements the method for calculating the lateral static stability derivative of a cruise-configuration wing as described above. This 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 aforementioned computer-readable storage medium carries one or more programs that, when executed by the apparatus, process data according to the method described above.

[0167] The following is for reference. Figure 2 It shows a schematic diagram of the structure of a computer device 400 suitable for implementing the embodiments of this application. Figure 2 The computer device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments described in this application.

[0168] 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 section 408 into a random access memory (RAM) 403. The RAM 403 also stores various programs and data required for the operation of the device 400. The CPU 401, ROM 402, and RAM 403 are interconnected via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0169] The following components are connected to I / O interface 405: an input section 406 including a keyboard, mouse, etc.; an output section 407 including a cathode ray tube (CRT), liquid crystal display (LCD), etc., and speakers, 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, modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to I / O interface 405 as needed. A removable medium 411, such as a disk, optical disk, magneto-optical disk, semiconductor memory, etc., is installed on drive 410 as needed so that computer programs read from it can be installed into storage section 408 as needed.

[0170] Specifically, according to embodiments of this application, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of this application include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication section 409, and / or installed from removable medium 411. When the computer program is executed by central processing unit (CPU) 401, it performs the functions defined in the methods of this application. It should be noted that the computer storage medium of this application can be a computer-readable signal medium or a computer-readable storage medium, or any combination thereof. A computer-readable storage medium can be, for example,—but not limited to—an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of computer-readable storage media may include, but are not limited to: electrical connections having one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof. In this application, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in connection 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, carrying computer-readable program code. Such propagated data signals can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can also be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on a computer-readable medium can be transmitted using any suitable medium, including but not limited to: wireless, wire, optical fiber, RF, etc., or any suitable combination thereof.

[0171] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this application. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0172] The modules or units described in the embodiments of this application can be implemented in software or hardware. The described modules or units can also be located in a processor, and the names of these modules or units do not necessarily constitute a limitation on the module or unit itself.

[0173] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for calculating the lateral static stability derivative of a cruise-configuration wing, characterized in that, include: Step S1: Determine the lateral static stability derivative generated by the wing plane parameters. When the wing is a triangular wing, calculate the lateral static stability derivative of the triangular wing based on the lift coefficient and the wing aspect ratio. When the wing is a trapezoidal wing, calculate the lateral static stability derivative of the trapezoidal wing based on the compressibility correction factor and the lateral static stability derivative generated by the wing in the incompressible flow. Step S2: Determine the lateral static stability derivative generated by the dihedral angle on the wing.

2. The method for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 1, characterized in that, In step S1, the lateral static stability derivative of the delta wing is calculated using the following formula: ； in, For the wing aspect ratio, This is the lift coefficient.

3. The method for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 1, characterized in that, In step S1, the lateral static stability derivative of the trapezoidal wing is calculated using the following formula. : ； in, It is a compressibility correction factor. This is the lateral static stability derivative generated by the wing in an incompressible flow.

4. The method for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 3, characterized in that, The lateral static stability derivative of an airfoil in an incompressible flow is calculated using the following formula. : ； in, The lift coefficient, For the lateral static stability derivative of the incompressible flow in a straight airfoil, This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

5. The method for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 4, characterized in that, Parameters are calculated using the following formula. : ； in, ; ； The wing root ratio.

6. The method for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 5, characterized in that, Parameters are calculated using the following formula. : ； in, ; ； ； in, This indicates the location of the wing's aerodynamic pressure center.

7. The method for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 3, characterized in that, In a given two-dimensional interpolation table, a compressibility correction factor is interpolated based on a given Mach number correction parameter and the wing aspect ratio. The Mach number correction parameter... Calculated using the following formula: 。 8. The method for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 1, characterized in that, In step S2, the lateral static stability derivative generated by the dihedral angle of the computer wing is calculated using the following formula. : ； in, The dihedral angle of the wing. For wing parameters; ； ； in, The lift line slope of the Mach number M airfoil; In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula: ； Second correction parameter Calculated using the following formula: ； in, It is the sweep angle of the wing's quarter chord.

9. A device for calculating the lateral static stability derivative of a cruise-configuration wing, characterized in that, include: The module for determining the lateral static stability derivative generated by the wing plane parameters is used to determine the lateral static stability derivative generated by the wing plane parameters. When the wing is a triangular wing, the lateral static stability derivative of the triangular wing is calculated based on the lift coefficient and the wing aspect ratio. When the wing is a trapezoidal wing, the lateral static stability derivative of the trapezoidal wing is calculated based on the compressibility correction factor and the lateral static stability derivative generated by the wing in the incompressible flow. The module for the lateral static stability derivative generated by the dihedral angle of the wing is used to determine the lateral static stability derivative generated by the dihedral angle of the wing.

10. The device for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 9, characterized in that, In the module for determining the lateral static stability derivative generated by the wing planar parameters, the lateral static stability derivative of the delta wing is calculated using the following formula: ； in, For the wing aspect ratio, This is the lift coefficient.

11. The device for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 9, characterized in that, In the module for determining the lateral static stability derivative generated by the wing planar parameters, the lateral static stability derivative of the trapezoidal wing is calculated using the following formula. : ； in, It is a compressibility correction factor. This is the lateral static stability derivative generated by the wing in an incompressible flow.

12. The device for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 11, characterized in that, The lateral static stability derivative of an airfoil in an incompressible flow is calculated using the following formula. : ； in, The lift coefficient, For the lateral static stability derivative of the incompressible flow in a straight airfoil, This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

13. The device for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 12, characterized in that, Parameters are calculated using the following formula. : ； in, ; ； The wing root ratio.

14. The device for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 13, characterized in that, Parameters are calculated using the following formula. : ； in, ; ； ； in, This indicates the location of the wing's aerodynamic pressure center.

15. The device for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 11, characterized in that, In a given two-dimensional interpolation table, a compressibility correction factor is interpolated based on a given Mach number correction parameter and the wing aspect ratio. The Mach number correction parameter... Calculated using the following formula: 。 16. The device for calculating the lateral static stability derivative of a cruise configuration wing as described in claim 9, characterized in that, In the module for calculating the lateral static stability derivative of the wing dihedral angle, the lateral static stability derivative generated by the wing dihedral angle is calculated using the following formula. : ； in, The dihedral angle of the wing. For wing parameters; ； ； in, The lift line slope of the Mach number M airfoil; In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula: ； Second correction parameter Calculated using the following formula: ； in, It is the sweep angle of the wing's quarter chord.

17. A computer device, characterized in that, It 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 the method for calculating the lateral static stability derivative of a cruise configuration wing as described in any one of claims 1-8.

18. A readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it is used to implement the method for calculating the lateral static stability derivative of a cruise configuration wing as described in any one of claims 1-8.

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