Method, device and equipment for predicting two-dimensional rhombic double-wing aerodynamic force and medium

Abstract

The embodiment of the invention relates to the technical field of aerodynamic layout of supersonic aircrafts, and discloses a two-dimensional rhombic double-wing aerodynamic force prediction method, device and equipment and a medium. According to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave and a predetermined first slip line, predicting aerodynamic force between the two rhombic wings; when the two expansion waves intersect, the aerodynamic force between the rhombic double wings is predicted according to the flow field properties of the two expansion waves before intersection and a predetermined second slip line; wherein the expansion wave is generated by the midpoint of the lower wing in the two-dimensional rhombic double wings; the intersected expansion wave is a fan-shaped area, and the Prandtt-Mayer expansion fan of the intersected expansion wave is emitted from the vertex of the fan-shaped area. According to the method, the complex flow field characteristics under double-wing flow can be accurately described, and the precision and efficiency of aerodynamic force prediction are improved.

Description

Technical Field

[0001] The embodiments of the present invention relate to the field of aerodynamic layout design of supersonic aircraft, and in particular to a method, device, equipment, medium and product program for predicting aerodynamic force of a two-dimensional diamond-shaped double wing. Background Art

[0002] The existing methods for predicting the aerodynamic force of supersonic airfoils are mainly based on classical inviscid fluid theory and numerical simulation technology. Among them, the prediction method based on classical inviscid fluid theory is highly efficient, but the accuracy cannot be guaranteed, and the prediction method based on numerical simulation technology is relatively accurate, but the efficiency is low. Summary of the invention

[0003] The purpose of the present invention is to at least provide a method and device for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing, so as to at least solve the problem that the expansion wave interferes with other flow field structures, making it difficult to predict the aerodynamic force of the two-dimensional diamond-shaped double wing.

[0004] In order to solve the above technical problems, at least one embodiment of the present application provides a method for predicting aerodynamic force of a two-dimensional diamond-shaped double wing, comprising:

[0005] When the expansion wave intersects the oblique shock wave, predicting the aerodynamic force between the diamond-shaped double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line;

[0006] When two expansion waves intersect, predicting the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and a predetermined second slip line;

[0007] The expansion wave is generated by the midpoint of the lower wing of the two-dimensional rhombus double wings; the intersecting expansion waves are a fan-shaped area, and the Prandtl-Meyer expansion fan of the intersecting expansion waves is emitted from the vertex of the fan-shaped area.

[0008] In some embodiments, predicting the aerodynamic force between the diamond-shaped double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line includes:

[0009] Determining a first region where the expansion wave and the oblique shock wave intersect according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line;

[0010] The aerodynamic force at any point in the first region is predicted according to the Prandtl-Meyer angle at the point.

[0011] In some embodiments, determining a first region where the expansion wave intersects the oblique shock wave according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line comprises:

[0012] Determine the Mach number of the fluid above the first slip line according to the emission position of the expansion wave and the aerodynamic parameters of the expansion wave, so as to determine a first boundary in the first region above the first slip line;

[0013] Determine the Mach number of the fluid below the first slip line according to the emission position of the oblique shock wave and the aerodynamic parameters of the oblique shock wave, so as to determine a second boundary below the first slip line in the first region;

[0014] The first area is determined according to the first boundary and the second boundary.

[0015] In some embodiments, determining a first boundary in the first region that is above the first slip line includes:

[0016] Calculating a corresponding Mach cone angle according to the Mach number of the fluid above the first slip line to determine the first boundary;

[0017] Determining a second boundary in the first region below the first slip line includes:

[0018] The corresponding Mach cone angle is calculated according to the Mach number of the fluid below the first slip line to determine the second boundary.

[0019] In some embodiments, predicting the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and the predetermined second slip line includes:

[0020] Determining a second region where the two expansion waves intersect according to flow field properties of the two expansion waves before the intersection and a predetermined second slip line;

[0021] The aerodynamic force at any point in the second region is determined according to the Prandtl-Meyer angle of the point.

[0022] In some embodiments, determining the second region where the two expansion waves intersect according to the flow field properties of the two expansion waves before the intersection and a predetermined second slip line includes:

[0023] Determining a third region of the two expansion waves before the intersection according to flow field properties of the two expansion waves before the intersection;

[0024] A second region where two expansion waves intersect is determined based on the third region and the second slip line.

[0025] In some embodiments, after the expansion wave intersects the oblique shock wave, the expansion wave is reflected and expanded secondary on the upper wing of the two-dimensional diamond-shaped double wings;

[0026] The aerodynamic parameters of the oblique shock wave include: the wavefront aerodynamic parameters and the waveback aerodynamic parameters of the oblique shock wave; the aerodynamic parameters of the expansion wave include: the wavefront aerodynamic parameters and the waveback aerodynamic parameters of the expansion wave.

[0027] At least one embodiment of the present application further provides a device for predicting aerodynamic forces of a two-dimensional diamond-shaped double wing, comprising:

[0028] an aerodynamic force determination first module, for predicting the aerodynamic force between the diamond-shaped double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line when the expansion wave intersects the oblique shock wave;

[0029] The second aerodynamic force determination module is used to predict the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and the predetermined second slip line when the two expansion waves intersect;

[0030] The expansion wave is generated by the midpoint of the lower wing of the two-dimensional rhombus double wings; the intersecting expansion waves are a fan-shaped area, and the Prandtl-Meyer expansion fan of the intersecting expansion waves is emitted from the vertex of the fan-shaped area.

[0031] At least one embodiment of the present application also provides an electronic device, comprising: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, and the instructions are executed by the at least one processor so that the at least one processor can execute the above-mentioned method for predicting the aerodynamic force of a two-dimensional diamond biplane.

[0032] At least one embodiment of the present application further provides a computer-readable storage medium storing a computer program, wherein the computer program, when executed by a processor, implements the above-mentioned method for predicting the aerodynamic force of a two-dimensional diamond-shaped biplane.

[0033] An embodiment of the present application provides a method for predicting the aerodynamic force of a two-dimensional diamond double wing, comprising: when an expansion wave intersects with an oblique shock wave, predicting the aerodynamic force between the diamond double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line; when two expansion waves intersect, predicting the aerodynamic force between the diamond double wings according to the flow field properties of the two expansion waves before the intersection and a predetermined second slip line; wherein the expansion wave is generated by the midpoint of the lower wing of the two-dimensional diamond double wing; the expansion waves that intersect are a fan-shaped area, and the Prandtl-Meyer expansion fan of the expansion waves that intersect is emitted from the vertex of the fan-shaped area.

[0034] In summary, the present invention is based on the shock wave-expansion wave theory, and proposes the hypothesis that the expansion wave after being disturbed has a fan-shaped area point. The method provided by the present invention can accurately describe the complex flow field characteristics under the double-wing flow, and improve the accuracy and efficiency of aerodynamic prediction. This method is not only applicable to the existing diamond double-wing aerodynamic prediction, but can also be promoted and applied to the design of other supersonic aircraft in the future, and has broad application prospects and economic benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] One or more embodiments are exemplarily described by the pictures in the corresponding drawings, and these exemplary descriptions do not constitute limitations on the embodiments.

[0036] Figure 1 It is a flow chart of a method for predicting aerodynamic force of a two-dimensional diamond-shaped double wing provided by an embodiment of the present application;

[0037] Figure 2 is a schematic diagram of a diamond-shaped double-wing design provided by an embodiment of the present application;

[0038] Figure 3 is a flowchart of step 100 provided by an embodiment of the present application;

[0039] Figure 4 It is a schematic diagram of a flow chart of solving aerodynamic characteristics of an alternating current field between an expansion wave and an oblique shock wave provided by an embodiment of the present application;

[0040] Figure 5 is a flowchart of step 101 provided by an embodiment of the present application;

[0041] Figure 6 This is a schematic diagram of a theoretical analysis method for the alternating current between an expansion wave and an oblique shock wave provided in an embodiment of the present application.

[0042] Figure 7 is a flowchart of step 1011 provided by an embodiment of the present application;

[0043] Figure 8 is a flowchart of step 1012 provided by an embodiment of the present application;

[0044] Fig. 9 is a flowchart of step 200 provided by an embodiment of the present application;

[0045] Fig.10 It is a schematic diagram of a flow chart of solving aerodynamic characteristics of an alternating current field between expansion waves and expansion waves provided by an embodiment of the present application;

[0046] Fig.11 is a flowchart of step 201 provided by an embodiment of the present application;

[0047] Fig.12 This is a schematic diagram of a theoretical analysis method for the alternating current field between expansion waves and expansion waves provided in an embodiment of the present application.

[0048] Fig.13 It is a schematic diagram of the flow field characteristics of a typical rhombus double wing layout provided in a specific embodiment of the present application;

[0049] Fig.14 It is a detailed exploded view of the internal flow field structure of the diamond-shaped double wing provided in the specific embodiment of the present application;

[0050] Fig.15 is an example diagram of a method for solving aerodynamic parameters of a typical double-wing layout provided by a specific embodiment of the present application;

[0051] Fig.16 It is a schematic diagram comparing the pressure prediction capabilities of the method proposed by the present invention and the existing methods provided in the specific implementation mode of the present application;

[0052] Fig.17 is a schematic diagram of a two-dimensional diamond-shaped double-wing aerodynamic prediction device provided by an embodiment of the present application;

[0053] Fig.18 It is a schematic diagram of the structure of an electronic device provided by another embodiment of the present application. DETAILED DESCRIPTION

[0054] To make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the embodiments of the present application will be described in detail below in conjunction with the accompanying drawings. However, it will be appreciated by those skilled in the art that in the present application, many technical details are proposed in order to enable the reader to better understand the present application. However, even without these technical details and various changes and modifications based on the following embodiments, the technical scheme claimed in the present application can also be implemented. The division of the following embodiments is for the convenience of description, and the specific implementation of the present application should not be construed as any limitation, and the various embodiments can be combined and referenced with each other under the premise of no contradiction.

[0055] In order to facilitate understanding of the embodiments of the present application, relevant content regarding the technical difficulties in rapid prediction of aerodynamic forces of a two-dimensional diamond-shaped double wing is first introduced here.

[0056] In the prior art, the inviscid fluid theory analysis methods for solving the aerodynamic characteristics of supersonic airfoils include linearization theory, second-order approximation theory, shock-expansion wave theory, etc. Among them, linearization theory and second-order approximation theory are both derived using the thin wing assumption, and are essentially unable to describe the shock wave / boundary layer and shock wave / shock wave interactions generated between the upper and lower wings, resulting in poor prediction accuracy of the aerodynamic forces of the wings.

[0057] In contrast, the shock wave-expansion wave theory is more suitable for the prediction of biplane aerodynamics. Expansion waves are sparse waves without discontinuities, and appear as fan-shaped areas of expansion waves in space. When an expansion wave interacts with another shock wave / expansion wave (the interaction problem between multiple oblique shock waves has been well solved by existing technologies), the fan-shaped area of ​​the expansion wave will lead to poor flow field prediction accuracy. At present, the shock wave-expansion wave theory cannot be directly used to solve the aerodynamic characteristics of complex flow fields with expansion wave interference, and the mutual interference between expansion waves and other flow field structures is a common flow field structure in biplane aerodynamic layout.

[0058] Specifically, Liu Shuhan et al. (Liu Shuhan, Zhu Zhanxia. Research on three-dimensional hypersonic wing based on Busemann double wing [J]. Acta Aeronautica Sinica, 2018, 39(6): 121405.) established a method based on shock-expansion wave theory to predict the aerodynamic characteristics of double wings. This method analyzes the aerodynamic characteristics of the shock / expansion waves generated by the surface changes. This method does not consider the aerodynamic effects caused by the shock / expansion wave interference between the upper and lower wings. Since the shock / expansion waves at the upper and lower wing heads will inevitably intersect, the parameters of the shock / expansion waves after the intersection are different from those before the intersection. Therefore, the error of the double wing aerodynamic results estimated by only considering the surface changes is very large.

[0059] In addition, Xue Yifei et al. (Xue Yifei, Zeng Honggang, Cheng Siye. Research on Supersonic Beneficial Interference for Diamond Biplane Layout [J]. Aeronautical Science and Technology, 2023, 34(07): 13-21.) proposed a method for solving the post-wave flow field based on the slip line for the flow field with the intersection of shock wave / expansion wave, which can solve the mutual interference between the two wings and improve the accuracy of solving the flow field interference problem between the two wings. When analyzing the shock wave-expansion wave interference, this method assumes that the expansion wave is a line, that is, the expansion process is completed quickly, but the expansion wave is a sparse wave with a large influence domain in space. Therefore, in the flow problem involving the interaction between the expansion wave and the oblique shock wave / expansion wave, the error of this method is large.

[0060] In summary, establishing a theoretical prediction method for aerodynamic characteristics with expansion waves and flow field structure interference problems, and realizing fast and accurate prediction of the aerodynamic characteristics of double wings, is an important problem to be solved by those skilled in the art. Based on this, the present invention proposes a two-dimensional diamond double wing aerodynamic prediction method. The implementation details of a two-dimensional diamond double wing aerodynamic prediction method of this embodiment are specifically described below. The following content is only for the convenience of understanding the implementation details provided, and is not necessary for the implementation of this solution.

[0061] Embodiment 1:

[0062] The method for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing of this embodiment can be applied to electronic devices with communication, computing and data storage capabilities. The specific process can be as follows: Figure 1 As shown, including:

[0063] Step 100: When the expansion wave intersects the oblique shock wave, predicting the aerodynamic force between the diamond-shaped double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line;

[0064] Step 200: When two expansion waves intersect, predicting the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and a predetermined second slip line;

[0065] The expansion wave is generated by the midpoint of the lower wing of the two-dimensional diamond-shaped double wing (the position of the midpoint is as shown in Figure 2 As shown by the dots in the figure, the high pressure area of ​​the lower wing acts on the upper wing and generates additional lift); the intersecting expansion waves are a fan-shaped area (expansion fan), and the Prandtl-Meyer expansion fan of the intersecting expansion waves is emitted from the apex of the fan-shaped area.

[0066] In summary, the present invention proposes an expansion wave fan-shaped area center hypothesis, and establishes a method for estimating the aerodynamic characteristics of the expansion wave fan-shaped area after being disturbed by shock waves / expansion waves. In this method, it is assumed that each disturbed expansion wave has a dot in the fan-shaped area, and the Prandtl-Meyer expansion fan of the expansion wave is emitted from the dot. This hypothesis can estimate the spatial position of the disturbed expansion wave fan-shaped area, and can be used to estimate the aerodynamic characteristics at different positions. Although this hypothesis has a certain deviation, it can still greatly improve the accuracy of aerodynamic prediction in practical applications.

[0067] First, see Figure 2 , Figure 2 The design principle of the dynamic layout shown is that the lower surface of the upper wing utilizes the local high pressure generated at the midpoint of the lower wing to generate additional lift, thereby improving the lift / lift-to-drag ratio.

[0068] Specifically, when the high-pressure area 1 generated by the lower wing of the diamond-shaped double wing acts on the lower surface of the upper wing, the pressure on the lower surface of the upper wing increases and the lift increases. Therefore, the upper wing needs to capture as much high pressure as possible brought by the lower wing. The lower surface of the upper wing will also produce high pressure, namely, the high-pressure area 2. The lower wing should try to avoid the high-pressure area 2 to ensure that the lift will not decrease.

[0069] Based on the analysis of the above design principles, not only flow field structures such as shock waves and expansion waves will appear in the flow field, but also complex flow field structures such as interference between shock waves and interference between shock waves and between shock waves and expansion waves (after the expansion wave is disturbed, the spatial position of the expansion wave changes).

[0070] In some examples, step 100 and step 200 are two situations of the technical problems to be solved by the present application: the flow situation where the expansion wave intersects with the oblique shock wave; and the flow situation where multiple expansion waves intersect, and the technical definition after step 200 is the assumption of the method proposed in the present application. Although this assumption has a certain deviation, it can still greatly improve the accuracy of aerodynamic prediction in practical applications.

[0071] With respect to step 100, it is understood that an oblique shock wave (shock wave) refers to a shock wave generated when a high-speed fluid flows over an inclined solid surface (such as a wedge-shaped or conical object). The oblique shock wave will reduce the velocity of the fluid, increase the pressure and temperature, and change the flow direction. The angle and intensity of the oblique shock wave depend on factors such as the velocity of the incident fluid, the shape and angle of the object, etc.

[0072] Dilation waves are the opposite of shock waves. They are waves that occur when a fluid passes through a gradually expanding area. Dilation waves increase the velocity of the fluid and decrease its pressure and temperature. Dilation waves usually occur when a fluid passes around a convex corner or flows from a narrow channel into a wide channel.

[0073] For step 200, when two expansion waves intersect, the direction of the expansion waves will change. When the two expansion waves do not overlap, there is also a unique slip line in the flow field behind the expansion waves after the intersection, and the aerodynamic characteristics on both sides of the slip line are the same as the aerodynamic characteristics after the two expansion waves.

[0074] Embodiment 2:

[0075] See also Figure 3 as well as Figure 4 The method for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing of this embodiment can be applied to electronic devices with communication, computing and data storage capabilities. Step 100 includes:

[0076] Step 101: determining a first region where the expansion wave and the oblique shock wave intersect according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line;

[0077] It should be noted that in step 101, it is assumed that there is a unique slip line (first slip line) in the flow field after the oblique shock wave intersects the expansion wave, the aerodynamic data above the first slip line and below the first slip line are different, and there is a unique slip line solution that satisfies the following conditions:

[0078] Pressure above the slip line = pressure below the slip line;

[0079] The velocity direction of the fluid above the slip line = the velocity direction of the fluid below the slip line.

[0080] Step 102: predicting the aerodynamic force of any point in the first region according to the Prandtl-Meyer angle of the point.

[0081] Specifically, the aerodynamic characteristics of any point in the first region are obtained according to the Prandtl-Meyer angle of the expansion fan. The Prandtl-Meyer angle describes the rotation angle of the fluid when it passes through the expansion fan (composed of a series of expansion waves). The Prandtl-Meyer expansion fan refers to a series of continuous expansion waves formed when the fluid passes around a convex angle (such as the throat or expansion angle of the nozzle).

[0082] See also Figure 5 The method for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing of this embodiment can be applied to electronic devices with communication, computing and data storage capabilities. Step 101 includes:

[0083] Step 1011: determining the Mach number of the fluid above the first slip line according to the emission position of the expansion wave and the aerodynamic parameters of the expansion wave, so as to determine a first boundary in the first region above the first slip line;

[0084] Step 1012: determining the Mach number of the fluid below the first slip line according to the emission position of the oblique shock wave and the aerodynamic parameters of the oblique shock wave, so as to determine a second boundary below the first slip line in the first region;

[0085] Step 1013: Determine the first area according to the first boundary and the second boundary.

[0086] In steps 1011 to 1013, see Figure 6The left and right boundaries of the intersecting expansion wave can be obtained by theoretical analysis. Assuming that there is a dot in the fan-shaped area of ​​the intersecting expansion wave and it is located at the intersection of the extended lines of the left and right boundaries of the expansion wave, the aerodynamic characteristics at each spatial position X can be obtained according to the angle characteristics of the disturbed expansion fan.

[0087] Specifically, Figure 6 It contains an expansion wave starting from point O and an oblique shock wave starting from point M. The oblique shock wave intersects with the expansion wave, and both the oblique shock wave and the expansion wave are deflected. The spatial position of the oblique shock wave starting from point M and the aerodynamic parameters of the oblique shock wave front and after the wave are known: OA wave front and MA wave after. The aerodynamic parameters of the expansion wave front and after the wave starting from point O are known: OA wave front and OB wave after. The left boundary of the expansion wave starting from point O can be obtained from the aerodynamic parameters of the OA wave front. The intersection point A of the left boundary of the expansion wave starting from point O and the oblique shock wave starting from point M is. In order to obtain the intersection point B of the right boundary of the expansion wave starting from point O and the oblique shock wave after interference, it is necessary to first obtain the spatial position and aerodynamic characteristics of the oblique shock wave after interference by the expansion wave. The slip line hypothesis method is adopted here:

[0088] After obtaining the position of the slip line and the aerodynamic characteristics of the two areas above and below the slip line, the spatial position of the oblique shock wave after being disturbed by the expansion wave can be obtained according to the aerodynamic characteristics behind the OB wave and below the slip line, and the intersection B between the oblique shock wave and the right boundary of the expansion wave can be estimated. Here, the spatial position of the oblique shock wave after being disturbed by the expansion wave is recorded as BN.

[0089] The Mach cone angle of the region is calculated from the Mach number above the slip line, and then the right boundary of the expansion wave after being disturbed by the oblique shock wave can be obtained, which is recorded as BD. At the same time, the Mach cone angle is calculated using the Mach number after the MA wave, and then the left boundary of the expansion wave after being disturbed by the oblique shock wave is obtained, which is recorded as AC. Applying the assumption proposed by the present invention, that is, assuming that the expansion wave still has a unique dot in the expansion fan structure after being disturbed, find the intersection of the extended lines of AC and BD, which is recorded as O'. This point is the dot of the expansion wave after being disturbed by the oblique shock wave.

[0090] See also Figure 7 The method for predicting aerodynamic force of a two-dimensional diamond-shaped double wing of this embodiment can be applied to electronic devices with communication, computing and data storage capabilities. The step 1011 of "determining a first boundary in the first region above the first slip line" includes:

[0091] Step 10111: Calculate the corresponding Mach cone angle according to the Mach number of the fluid above the first slip line to determine the first boundary;

[0092] See also Figure 8 The step 1012 of “determining a first boundary in the first region located above the first slip line” includes:

[0093] Step 10121: Calculate the corresponding Mach cone angle according to the Mach number of the fluid below the first slip line to determine the second boundary.

[0094] See also Fig. 9 as well as Fig.10 The method for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing of this embodiment can be applied to electronic devices with communication, computing and data storage capabilities. Step 200 includes:

[0095] Step 201: determining a second region where the two expansion waves intersect according to flow field properties of the two expansion waves before the intersection and a predetermined second slip line;

[0096] When two expansion waves intersect, the direction of the expansion waves will change. When the two expansion waves do not overlap, there is also a unique slip line (the second slip line) in the flow field behind the expansion waves after the intersection. The aerodynamic characteristics on both sides of the second slip line are the same as the aerodynamic characteristics behind the two expansion waves.

[0097] Step 202: Determine the aerodynamic force of any point in the second region according to the Prandtl-Meyer angle of the point.

[0098] The implementation of this step is similar to that of step 102 and will not be described again here.

[0099] See also Fig.11 The method for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing of this embodiment can be applied to electronic devices with communication, computing and data storage capabilities. Step 201 includes:

[0100] Step 2011: determining a third region of the two expansion waves before the intersection according to the flow field properties of the two expansion waves before the intersection;

[0101] Step 2012: Determine a second region where two expansion waves intersect based on the third region and the second slip line.

[0102] When two expansion waves intersect, the flow field characteristics are as follows: Fig.12 The figure shows a method for obtaining the aerodynamic characteristics of the position of any expansion wave interference zone based on the expansion wave dot hypothesis proposed in this application:

[0103] In the flow field where expansion waves intersect, if the flow field characteristics before the two expansion waves intersect are known, the aerodynamic characteristics of any point in the expansion wave fan-shaped area after the two expansion waves intersect can be derived. From the expansion wave front Mach number and the points O1 and O2 of the expansion wave, the left boundary of the expansion wave starting from point O1 and the right boundary of the expansion wave starting from point O2 can be obtained. From the post-wave Mach number of expansion wave 1 and the point O1, the right boundary of the expansion wave starting from point O1 can be obtained; from the post-wave Mach number of expansion wave 2 and the point O2, the left boundary of the expansion wave starting from point O2 can be obtained. The right boundary of expansion wave 1 intersects with the right boundary of expansion wave 2 at point A (estimated), and the left boundary of expansion wave 1 intersects with the left boundary of expansion wave 2 at point B (estimated).

[0104] The right boundary AE of the expansion wave 2 after the interference can be determined by point A and the Mach number of the area after the expansion wave 1. Similarly, the left boundary BF of the expansion wave 1 after the interference can be determined by point B and the Mach number of the area after the expansion wave 2. Before solving the boundaries of the other two disturbed expansion waves, it is necessary to first determine the aerodynamic characteristics after the expansion wave. Here, the slip line hypothesis is also used. The slip line is shown as the long dashed line in the figure, and the aerodynamic characteristics above and below the slip line can be solved. The right boundary AD of the expansion wave 1 after the interference can be estimated by the Mach number above the slip line and point A, and the left boundary BC of the expansion wave 2 after the interference can be estimated by the Mach number below the slip line and point B.

[0105] Applying the dot hypothesis proposed by the present invention, the extended lines of AD and BF intersect at O1', i.e., the dot of the fan-shaped area of ​​expansion wave 1 disturbed by expansion wave 2, and the extended lines of AE and BC intersect at O2', i.e., the dot of the fan-shaped area of ​​expansion wave 2 disturbed by expansion wave 1. When solving the aerodynamic characteristics of point X1 in the expansion wave interference area shown in the figure, the aerodynamic characteristics at the position of X1 can be determined according to the Prandtl-Meyer angle of O1'X1. Similarly, when X2 is located in the disturbed expansion wave 2, the aerodynamic characteristics at the position of X2 can be determined according to the Prandtl-Meyer angle of O2'X2.

[0106] As can be seen from the above description, an embodiment of the present application provides a method for predicting the aerodynamic force of a two-dimensional diamond double wing, comprising: when an expansion wave intersects with an oblique shock wave, predicting the aerodynamic force between the diamond double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line; when two expansion waves intersect, predicting the aerodynamic force between the diamond double wings according to the flow field properties of the two expansion waves before the intersection and a predetermined second slip line; wherein the expansion wave is generated by the lower wing of the two-dimensional diamond double wing; the expansion waves that intersect are a fan-shaped area, and the Prandtl-Meyer expansion fan of the expansion waves that intersect is emitted from the vertex of the fan-shaped area.

[0107] In summary, the present invention aims at the aerodynamic layout optimization problem of a two-dimensional diamond-shaped double-wing, which has a complex double-wing combination, many adjustable variables, and a large optimization space, and provides a method for rapid aerodynamic prediction that can take into account both accuracy and efficiency.

[0108] Embodiment three:

[0109] In order to further illustrate the solution, the present invention also takes a typical double-wing layout as an example ( Fig.13 ), provides a specific implementation method of a two-dimensional diamond-shaped double-wing aerodynamic prediction method, which specifically includes the following contents.

[0110] The purpose of the present invention is to provide a method for rapid prediction of supersonic biplane aerodynamics based on shock wave-expansion wave theory, so as to solve the problem that the expansion wave and other flow field structures interfere with each other and are difficult to predict, thereby improving the accuracy of the prediction method of the aerodynamics of a two-dimensional diamond biplane.

[0111] It should be noted that the present invention is universal to the two-dimensional diamond-shaped double-wing problem and can be used to quickly predict the aerodynamic characteristics of different attack angles, different diamond sizes, and different relative spatial positions of the double wings.

[0112] See also Fig.13 , the upper wing angle of attack of this diamond-shaped double-wing layout is 5°, the lower wing angle of attack is 1°, the chord length of the upper and lower wings is 1m, the wingtip angle is 2×arctan(0.1), the position of the upper wing relative to the lower wing is (Δx,Δy)=(0.5012,0.1820)m, and the incoming flow Mach number is 3. This set of Mach numbers and relative position parameters can make the oblique shock wave interact with the leading edge of the upper wing, so that the upper wing can capture the high pressure generated by the lower wing to the greatest extent, and at the same time make the disturbed upper wing oblique shock wave just act on the trailing edge of the lower wing, so that the lower wing avoids the high pressure area generated by the upper wing. The aerodynamic characteristics of this typical layout can be solved by the traditional shock wave-expansion wave theory. Fig.13 The aerodynamic forces of the middle surface (1) to the surface (7) can achieve a fast and accurate solution of the aerodynamic characteristics for the complex flow near the upper wing corner based on theoretical analysis of the internal flow field characteristics and the use of the expansion wave point hypothesis proposed by the present invention.

[0113] See also Fig.14 Before using theoretical methods to derive aerodynamic characteristics, it is necessary to first analyze the flow field characteristics inside the double wings. The shape of the internal flow field is shown in the figure below. The oblique shock wave starting from point M on the leading edge of the upper wing will interfere with the expansion wave starting from point O on the lower wing. After the interference, the shock wave angle direction of the oblique shock wave changes. Then the oblique shock wave after the interference intersects with the lower wing at point N on the trailing edge. At the same time, the fan-shaped area of ​​the expansion wave after the interference changes. The fan-shaped area of ​​the expansion wave after the interference interacts with the lower surface of the upper wing, and the expansion wave is reflected. In particular, the expansion wave not only reflects behind the upper wing, but also expands again after passing through the corner of point E.

[0114] Continue to see Fig.14 The diamond-shaped double-wing flow shown in the figure uses the shock wave-expansion wave theory and geometric relationship to analyze the aerodynamic characteristics of the double-wing. The specific analysis process is as follows Fig.15 shown.

[0115] First, the aerodynamic characteristics of surfaces (1) to (7) are solved by shock wave expansion wave theory. Surfaces (1), (3), and (5) are the wave rear regions where the oblique shock wave is generated by the interaction between the incoming flow and the wall. The aerodynamic characteristics on these surfaces are obtained by the same set of oblique shock wave formulas. In the formula, δ represents the airflow deflection angle. The wavefront Mach number Ma is known. m＝ Ma ∞ , use the oblique shock wave relationship to find the shock wave angle β.

[0116]

[0117] After obtaining the shock wave angle, the post-wave Mach number Ma is further obtained. n and post-wave pressure P n .

[0118]

[0119]

[0120] Where P m Indicates the wavefront pressure.

[0121] Surface (7) is located behind surface (3). Therefore, when the above method is used to solve the aerodynamic characteristics of the oblique shock wave, the wavefront Mach number and pressure need to use the data of surface (3).

[0122] When solving surfaces (2), (4), and (6), it is necessary to consider the aerodynamic characteristics of the flow after the action of the expansion wave. Accordingly, the expansion wave wavefront parameters use the aerodynamic data of surfaces (1), (3), and (5), respectively, and the following expansion wave relationship is used to calculate the post-wave aerodynamic characteristics.

[0123] Calculate the Mach number Ma of the expansion wave after the wave according to the airflow deflection angle δ n :

[0124]

[0125] In the formula, Ma m is the wavefront Mach number of the expansion wave. Then, according to the wavefront pressure P m The Mach number Ma on both sides of the expansion wave m ,Ma n Solve for the pressure of the flow field after the expansion wave:

[0126]

[0127] Then the aerodynamic characteristics of surface (ma) and surface (mb) are solved. Here, the slip line theory is adopted. It is assumed that surface (ma) and surface (mb) are separated by a slip line. The pressure on both sides of the slip line is the same, the speed / Mach number is different, and the speed direction is the same. The aerodynamic parameters above the slip line are obtained by surface (7) and an expansion wave, and the aerodynamic parameters below the slip line are obtained by surface (4) and an oblique shock wave. According to the principle that the pressure on both sides of the slip line is the same, the unique solution of the slip line can be obtained, and the spatial position of the oblique shock wave in front of the surface (ma) and the aerodynamic characteristics of the surface (ma) and the surface (mb) can be obtained.

[0128] It should be pointed out that solving the pressure distribution on the bottom surface of the upper wing requires the use of the expansion wave point hypothesis proposed in the present invention. Fig.15 The detailed decomposition diagram of the complex internal structure of the double wing shows the analysis process of the aerodynamic characteristics of the expansion wave area under the interference of complex flow fields. From the Mach number of surface (3), the Mach cone angle of the surface (3) area can be obtained:

[0129] μ3=arcsin(1 / Ma3),

[0130] That is, the left boundary position of the expansion wave starting from point O. From the Mach number of surface (4), the Mach cone angle of the surface (4) area can be obtained:

[0131] μ4=arcsin(1 / Ma4),

[0132] That is, the right boundary position of the expansion wave starting from point O. The left boundary intersects with the oblique shock wave passing through point M, and the position of point A can be obtained. The right boundary intersects with the oblique shock wave passing through point N (that is, the oblique shock wave in front of the surface (ma)), and the position of point B can be obtained.

[0133] From the Mach number of surface (7), we can obtain the Mach cone angle μ7 of the surface (7) area, that is, the slope k7 of the left boundary of the expansion wave:

[0134] μ7=arcsin(1 / Ma7),

[0135] k7=tan[μ7-(α b +θ)],

[0136] Using this slope and the two conditions of passing through point A, the left boundary of the new expansion wave after the shock wave-expansion wave interference can be obtained. Similarly, the Mach cone angle is calculated from the Mach number of the surface (mb), and then the slope k of the right boundary is obtained. mb :

[0137] μ mb =arcsin(1 / Ma mb ),

[0138] kmb =tan(μ mb -α m ),

[0139] Where α m is the flow direction at both ends of the slip line, obtained by solving the slip line hypothesis. Combined with the condition of passing through point B, the right boundary position of the new expansion wave can be obtained. The intersection of the straight lines where the left and right boundaries are located is the point O' of the imaginary new expansion wave fan area.

[0140] Given the coordinates of point A and point E, we can find the size of ∠AO'E. Taking the Mach number at point E as a variable, we can establish an equation using the geometric relationship of the Mach cone and the expansion wave relationship:

[0141] arcsin(1 / Ma E )-arcsin(1 / Ma7)+∠AO'E-(ν E -ν7)=0,

[0142] where ν represents the Prandtl-Meyer angle, ν E The expression with ν7 is:

[0143]

[0144] Solving the above equation gives the Mach number Ma at point E in the expansion wave: E , but for the lower surface of the upper wing, the expansion wave is reflected at point E. Under the combined effect of the expansion wave and the reflected expansion wave, the aerodynamic parameters on the left side of point E are equivalent to experiencing two identical expansions, namely:

[0145]

[0146] The Mach number Ma to the left of point E can be calculated EL , and then the pressure P on the left side of point E can be calculated EL :

[0147]

[0148] The right side of point E additionally experiences the reflection of the expansion wave and the expansion effect of the corner. By adding these two interferences, the aerodynamic characteristics Ma on the right side of point E can be inferred. ER and P ER :

[0149]

[0150] Where 2θ refers to the wing tip angle of the leading and trailing edges of the diamond-shaped double wing. The slope of the right boundary of the expansion wave passing through point B is:

[0151] μmb=arcsin(1 / Mamb),

[0152] k mb =tan(μ mb -α m ).

[0153] The slope of the right boundary of the expansion wave passing through point E is:

[0154] μER=arcsin(1 / MaER),

[0155] k ERD =tan(μ ER -(θ-α b )).

[0156] The intersection point of the right boundary of the expansion wave passing through point B and the right boundary of the expansion wave passing through point E is D (estimated). The expansion wave starting from point E interferes with the expansion wave starting from point O'. The aerodynamic characteristics of the surface (ma2) and surface (mb2) in the rear region of the expansion wave are still obtained by the slip line assumption. The slope of the expansion wave passing through point D is:

[0157] μmb2=arcsin(1 / Mamb2),

[0158] k mb2 =tan(μ mb2 -α m2 ),

[0159] Where α m is the flow direction at both ends of the slip line, which is obtained by the slip line assumption, so that the right boundary DF of the expansion wave passing through point D can be obtained.

[0160] The left boundary of the expansion wave passing through point E (estimated) can be obtained from the Mach number at point E:

[0161] μER=arcsin(1 / MaER),

[0162] k ERU =tan(μ ER +(θ-α b )).

[0163] The left boundary line through point E and the extended line of the right boundary line through point D intersect at point O”.

[0164] From the spatial position of point G, the angle of ∠EO”G is calculated. Taking the Mach number at point G as a variable, the Mach number at point G is solved through the following relationship between the Mach cone angle and the expansion wave angle.

[0165] arcsin(1 / Ma G )-arcsin(1 / Ma ER )+∠EO”G-(ν G -ν ER )=0,

[0166] Where, ν G With ν ER The expression is:

[0167]

[0168] Point G is located on the trailing edge of the upper wing. Therefore, when solving the pressure of point G on the wall, the effect of the expansion wave wall reflection needs to be included. Here, the aerodynamic characteristics of point G considering the effect of wall reflection are recorded as Ma GW and P GW .

[0169]

[0170] Pressure GW It can be obtained from the expansion wave characteristics:

[0171]

[0172] for Fig.14 For the double-wing flow shown in the figure, the above method can not only obtain the pressure of surfaces (1) to (7), but also obtain the aerodynamic characteristics of several key points: point C, the left side of point E, the right side of point E, and point G. By connecting the aerodynamic results of these key points into a broken line, the aerodynamic characteristics of the entire double wing can be obtained.

[0173] See also Fig.16 , the figure compares the aerodynamic results obtained by using the expansion wave dot hypothesis analysis method proposed by the present invention and the aerodynamic results based on the numerical simulation of the Euler equation. The pressure distribution results show that after using the expansion wave dot hypothesis analysis method proposed by the present invention, the aerodynamic prediction is more accurate. The results obtained by using the expansion wave dot hypothesis represented by the solid line in the figure are almost completely coincident with the simulation results represented by the square points in the figure. The advantage of the present invention is reflected in the gray area, which is the pressure change area caused by the expansion wave being reflected by the wall and disturbed by the shock wave / expansion wave. By accurately predicting this part of the pressure distribution, the accuracy of theoretical prediction of aerodynamic characteristics can be greatly improved.

[0174] Embodiment 4:

[0175] Another embodiment of the present application relates to a two-dimensional diamond-shaped double-wing aerodynamic prediction device. The implementation details of the two-dimensional diamond-shaped double-wing aerodynamic prediction device of this embodiment are specifically described below. The following content is only for the convenience of understanding the implementation details provided, and is not necessary for the implementation of this solution. The schematic diagram of the two-dimensional diamond-shaped double-wing aerodynamic prediction device of this embodiment can be as follows Fig.17 As shown, there is a first module 801 for determining aerodynamic force and a second module 802 for determining aerodynamic force.

[0176] The first aerodynamic force determination module 801 is used to predict the aerodynamic force between the diamond double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave and the predetermined first slip line when the expansion wave intersects the oblique shock wave;

[0177] The second aerodynamic force determination module 802 is used to predict the aerodynamic force between the diamond wings according to the flow field properties of the two expansion waves before the intersection and the predetermined second slip line when the two expansion waves intersect;

[0178] The expansion wave is generated by the midpoint of the lower wing of the two-dimensional diamond-shaped double wings; the expansion waves that intersect are a fan-shaped area, and the Prandtl-Meyer expansion fan of the expansion waves that intersect is emitted from the vertex of the fan-shaped area.

[0179] An embodiment of the present application provides a two-dimensional diamond double-wing aerodynamic prediction device, comprising: an aerodynamic force determination first module, used to predict the aerodynamic force between the diamond double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line when the expansion wave intersects with the oblique shock wave;

[0180] The second aerodynamic force determination module is used to predict the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and the predetermined second slip line when the two expansion waves intersect;

[0181] The expansion wave is generated by the midpoint of the lower wing of the two-dimensional rhombus double wings; the intersecting expansion waves are a fan-shaped area, and the Prandtl-Meyer expansion fan of the intersecting expansion waves is emitted from the vertex of the fan-shaped area.

[0182] In summary, the present invention is based on the shock wave-expansion wave theory, and proposes the hypothesis that the expansion wave after being disturbed still has a fan-shaped area point. The above device provided by the present invention can accurately describe the complex flow field characteristics under the double-wing flow, and improve the accuracy and efficiency of aerodynamic prediction. The device is not only suitable for the existing diamond double-wing aerodynamic prediction, but can also be promoted and applied to the design of other supersonic aircraft in the future, and has broad application prospects and economic benefits.

[0183] It is worth mentioning that all modules involved in this embodiment are logic modules. In practical applications, a logic unit can be a physical unit, a part of a physical unit, or a combination of multiple physical units. In addition, in order to highlight the innovative part of this application, this embodiment does not introduce units that are not closely related to solving the technical problems proposed by this application, but this does not mean that there are no other units in this embodiment.

[0184] Embodiment five:

[0185] Another embodiment of the present application relates to an electronic device, such as Fig.18 As shown, including: the electronic equipment specifically includes the following contents:

[0186] Processor (processor) 1201, memory (memory) 1202, communication interface (CommunicationsInterface) 1203 and bus 1204;

[0187] The processor 1201, the memory 1202, and the communication interface 1203 communicate with each other through the bus 1204; the communication interface 1203 is used to realize information transmission between the server-side device and the user-side device and other related devices;

[0188] The processor 1201 is used to call the computer program in the memory 1202. When the processor executes the computer program, all steps in the method for predicting the aerodynamic force of the two-dimensional diamond-shaped double wing in the above embodiment are implemented. For example, when the processor executes the computer program, the following steps are implemented:

[0189] Step 100: When the expansion wave intersects the oblique shock wave, predicting the aerodynamic force between the diamond-shaped double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line;

[0190] Step 200: When two expansion waves intersect, predicting the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and a predetermined second slip line;

[0191] The expansion wave is generated by the midpoint of the lower wing of the two-dimensional rhombus double wings; the intersecting expansion waves are a fan-shaped area, and the Prandtl-Meyer expansion fan of the intersecting expansion waves is emitted from the vertex of the fan-shaped area.

[0192] Among them, the memory and the processor are connected in a bus manner, and the bus may include any number of interconnected buses and bridges, and the bus connects various circuits of one or more processors and memories together. The bus can also connect various other circuits such as peripherals, voltage regulators, and power management circuits, which are well known in the art and are therefore not further described herein. The bus interface provides an interface between the bus and the transceiver. The transceiver can be one element or multiple elements, such as multiple receivers and transmitters, providing a unit for communicating with various other devices on a transmission medium. The data processed by the processor is transmitted on a wireless medium via an antenna, and further, the antenna also receives data and transmits the data to the processor.

[0193] The processor is responsible for managing the bus and general processing, and can also provide various functions, including timing, peripheral interfaces, voltage regulation, power management, and other control functions. Memory can be used to store data used by the processor when performing operations.

[0194] Embodiment six:

[0195] Another embodiment of the present application relates to a computer-readable storage medium storing a computer program, which implements the above method embodiment when executed by a processor.

[0196] That is, those skilled in the art can understand that all or part of the steps in the above-mentioned embodiment method can be completed by instructing the relevant hardware through a program, and the program is stored in a storage medium, including a number of instructions to enable a device (which can be a single-chip microcomputer, chip, etc.) or a processor to execute all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (Read-Only Memory, referred to as: ROM), random access memory (Random Access Memory, referred to as: RAM), disk or optical disk and other media that can store program codes.

[0197] Those skilled in the art will appreciate that the above embodiments are specific embodiments for implementing the present application, and in actual applications, various changes may be made thereto in form and detail without departing from the spirit and scope of the present application.

Claims

1. A method for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing, characterized in that: include: When the expansion wave intersects the oblique shock wave, predicting the aerodynamic force between the diamond-shaped double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line; When two expansion waves intersect, predicting the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and a predetermined second slip line; The expansion wave is generated by the midpoint of the lower wing of the two-dimensional rhombus double wings; the intersecting expansion waves are a fan-shaped area, and the Prandtl-Meyer expansion fan of the intersecting expansion waves is emitted from the vertex of the fan-shaped area.

2. The prediction method according to claim 1, characterized in that: Predicting the aerodynamic force between the diamond-shaped double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line includes: Determining a first region where the expansion wave and the oblique shock wave intersect according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line; The aerodynamic force at any point in the first region is predicted according to the Prandtl-Meyer angle at the point.

3. The prediction method according to claim 2, characterized in that: Determining a first region where the expansion wave intersects the oblique shock wave according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line, comprises: Determine the Mach number of the fluid above the first slip line according to the emission position of the expansion wave and the aerodynamic parameters of the expansion wave, so as to determine a first boundary in the first region above the first slip line; Determine the Mach number of the fluid below the first slip line according to the emission position of the oblique shock wave and the aerodynamic parameters of the oblique shock wave, so as to determine a second boundary below the first slip line in the first region; The first area is determined according to the first boundary and the second boundary.

4. The prediction method according to claim 3, characterized in that: Determining a first boundary in the first region that is above the first slip line includes: Calculating a corresponding Mach cone angle according to the Mach number of the fluid above the first slip line to determine the first boundary; Determining a second boundary in the first region below the first slip line includes: The corresponding Mach cone angle is calculated according to the Mach number of the fluid below the first slip line to determine the second boundary.

5. The prediction method according to claim 1, characterized in that: The method of predicting the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and the predetermined second slip line includes: Determining a second region where the two expansion waves intersect according to flow field properties of the two expansion waves before the intersection and a predetermined second slip line; The aerodynamic force at any point in the second region is determined according to the Prandtl-Meyer angle of the point.

6. The prediction method according to claim 5, characterized in that: The determining, based on the flow field properties of the two expansion waves before the intersection and a predetermined second slip line, a second region where the two expansion waves intersect, comprises: Determining a third region of the two expansion waves before the intersection according to flow field properties of the two expansion waves before the intersection; A second region where two expansion waves intersect is determined based on the third region and the second slip line.

7. The prediction method according to any one of claims 1 to 6, characterized in that: When the expansion wave intersects the oblique shock wave, the expansion wave is reflected and expanded secondary on the upper wing of the two-dimensional diamond-shaped double wings; The aerodynamic parameters of the oblique shock wave include: the wavefront aerodynamic parameters and the waveback aerodynamic parameters of the oblique shock wave; the aerodynamic parameters of the expansion wave include: the wavefront aerodynamic parameters and the waveback aerodynamic parameters of the expansion wave.

8. A device for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing, characterized in that: include: an aerodynamic force determination first module, for predicting the aerodynamic force between the diamond-shaped double wings according to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave, and a predetermined first slip line when the expansion wave intersects the oblique shock wave; The second aerodynamic force determination module is used to predict the aerodynamic force between the diamond-shaped double wings according to the flow field properties of the two expansion waves before the intersection and the predetermined second slip line when the two expansion waves intersect; The expansion wave is generated by the midpoint of the lower wing of the two-dimensional rhombus double wings; the intersecting expansion waves are a fan-shaped area, and the Prandtl-Meyer expansion fan of the intersecting expansion waves is emitted from the vertex of the fan-shaped area.

9. An electronic device, characterized in that: include: at least one processor; as well as, a memory communicatively connected to the at least one processor; wherein, The memory stores instructions executable by the at least one processor, and the instructions are executed by the at least one processor to enable the at least one processor to execute the method for predicting aerodynamic force of a two-dimensional diamond-shaped biplane as claimed in any one of claims 1 to 7.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the method for predicting the aerodynamic force of a two-dimensional diamond-shaped double wing according to any one of claims 1 to 7 is implemented.

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