Hypersonic aircraft numerical simulation method, device, equipment and medium

Abstract

The invention discloses a hypersonic aircraft numerical simulation method, device and equipment and a medium, and relates to the field of aircraft numerical simulation, and the method comprises the steps: carrying out the modeling of a hypersonic aircraft airfoil according to a given hypersonic flight simulation working condition; constructing a reconstructed polynomial vector of each unit under the time step length by adopting a spatial reconstruction method of a weighted basic oscillation-free format of a non-equidistant template on the basis of the constructed initialized calculation flow field; correcting the reconstructed polynomial vector of each unit by adopting a correction keeping method; calculating a time discrete term of each unit under the time step length according to the reconstructed polynomial correction vector of each unit; lift force and resistance corresponding to different attack angles of the hypersonic aircraft airfoil model and the range of the attack angle when the lift force is maximum are determined according to the time discrete terms of all the units under all the time steps, and therefore the flight performance is determined, numerical simulation of the hypersonic aircraft can be effectively achieved, and numerical robustness is improved.

Description

Technical Field

[0001] The present application relates to the field of numerical simulation of aircraft, and in particular to a method, device, equipment and medium for numerical simulation of hypersonic aircraft. Background Art

[0002] In computational fluid dynamics (CFD), there are many widely used high-order numerical methods, such as Essentially Non-Oscillatory schemes (ENO), Weighted Essentially Non-Oscillatory (WENO), Discontinuous Galerkin (DG) method, etc., which have achieved great success in many industrial fields such as aerospace, automotive design, chemical industry processing, etc. However, in the numerical simulation of some extreme problems, such as the numerical simulation of hypersonic aircraft, the above widely used high-order numerical methods cannot maintain the positivity of physical quantities, resulting in the failure of the existing numerical simulation methods, and the numerical robustness of the above high-order numerical methods is poor. Summary of the invention

[0003] The purpose of this application is to provide a method, device, equipment and medium for numerical simulation of hypersonic aircraft, so as to effectively realize the numerical simulation of hypersonic aircraft and improve numerical robustness.

[0004] To achieve the above objectives, this application provides the following solutions.

[0005] In a first aspect, the present application provides a method for numerical simulation of a hypersonic aircraft, comprising: modeling a hypersonic aircraft airfoil according to a given hypersonic flight simulation condition, and determining an initialization calculation flow field; the given hypersonic flight simulation condition is that the inflow Mach number remains unchanged within a given time period, and the angle of attack changes with time; a triangular mesh in the initialization calculation flow field is taken as a unit.

[0006] Based on the initialized calculated flow field, at each time step, an improved weighted substantially oscillation-free format spatial reconstruction method is used to construct a reconstruction polynomial vector of each unit at the time step; the reconstruction polynomial vector includes: a density reconstruction polynomial, a momentum reconstruction polynomial and an energy reconstruction polynomial; the improved weighted substantially oscillation-free format is a weighted substantially oscillation-free format using unequally spaced templates.

[0007] At each time step, the reconstruction polynomial vector of each unit is corrected by using the correction method to obtain the reconstruction polynomial correction vector of each unit at that time step.

[0008] At each time step, the time discrete term of each unit at the time step is calculated according to the reconstruction polynomial correction vector of each unit; the time discrete term includes: the density distribution of the simulated flow field, the momentum distribution of the simulated flow field and the energy distribution of the simulated flow field.

[0009] The parameter values ​​of a hypersonic aircraft airfoil model under given hypersonic flight simulation conditions are determined according to the time discrete items of all units under all time steps; the parameter values ​​include: lift corresponding to different angles of attack, drag corresponding to different angles of attack, and the range of angles of attack at maximum lift; the parameter values ​​are used to determine the flight performance of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions.

[0010] In a second aspect, the present application provides a hypersonic aircraft numerical simulation device, which includes: a computational flow field construction module, which is used to model the hypersonic aircraft airfoil according to a given hypersonic flight simulation condition, and determine the initial computational flow field; the given hypersonic flight simulation condition is that the inflow Mach number remains unchanged within a given time period, and the angle of attack changes with time; a triangular mesh in the initialized computational flow field is taken as a unit.

[0011] A spatial reconstruction module is used to construct a reconstruction polynomial vector of each unit at each time step based on the initialized calculation flow field by using an improved weighted substantially non-oscillating format spatial reconstruction method at each time step; the reconstruction polynomial vector includes: a density reconstruction polynomial, a momentum reconstruction polynomial and an energy reconstruction polynomial; the improved weighted substantially non-oscillating format is a weighted substantially non-oscillating format using unequally spaced templates.

[0012] The correction module is used to correct the reconstruction polynomial vector of each unit at each time step by adopting a correction-preserving method to obtain a reconstruction polynomial correction vector of each unit at the time step.

[0013] The numerical calculation module is used to calculate the time discrete term of each unit at each time step according to the reconstruction polynomial correction vector of each unit at the time step; the time discrete term includes: the density distribution of the simulated flow field, the momentum distribution of the simulated flow field and the energy distribution of the simulated flow field.

[0014] A parameter determination module is used to determine the parameter values ​​of a hypersonic aircraft airfoil model under given hypersonic flight simulation conditions according to the time discrete items of all units under all time steps; the parameter values ​​include: lift corresponding to different angles of attack, drag corresponding to different angles of attack, and the range of angles of attack at maximum lift; the parameter values ​​are used to determine the flight performance of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions.

[0015] In a third aspect, the present application provides a computer device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the above-mentioned hypersonic aircraft numerical simulation method.

[0016] In a fourth aspect, the present application provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the above-mentioned hypersonic aircraft numerical simulation method.

[0017] According to the specific embodiments provided by the present application, the present application discloses the following technical effects: the present application provides a method, device, equipment and medium for numerical simulation of a hypersonic aircraft. Based on the initialization calculation flow field, at each time step, a spatial reconstruction method of a weighted essentially non-oscillatory format (Unequal-Sized Weighted Essentially Non-Oscillatory, US-WENO) of an unequally spaced template is used to construct a reconstructed polynomial vector of each unit at the time step. The weighted essentially non-oscillatory format of the unequally spaced template has the characteristics of arbitrary linear weights, a compact spatial template, and a more robust numerical format, thereby improving the numerical robustness; the positive preservation method is used to correct the reconstructed polynomial vector of each unit, which can maintain the positivity of the physical quantity and effectively realize the numerical simulation of the hypersonic aircraft, thereby determining the flight performance of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 A schematic diagram of the relationship between the inflow Mach number and angle of attack and flight performance provided in one embodiment of the present application.

[0020] Figure 2A schematic flow chart of a method for numerical simulation of a hypersonic aircraft provided in accordance with an embodiment of the present application.

[0021] Figure 3 A schematic diagram of a large space template provided for an embodiment of the present application.

[0022] Figure 4 A schematic diagram of a first small space template provided in an embodiment of the present application.

[0023] Figure 5 A schematic diagram of a second small space template provided in one embodiment of the present application.

[0024] Figure 6 A schematic diagram of a third small space template provided in an embodiment of the present application.

[0025] Figure 7 A schematic diagram of a fourth small space template provided in an embodiment of the present application.

[0026] Figure 8 A distribution diagram of detection points on a target unit provided in an embodiment of the present application.

[0027] Fig. 9 A schematic diagram of functional modules of a hypersonic aircraft numerical simulation device provided in another embodiment of the present application.

[0028] Fig.10 A schematic diagram of the structure of a computer device provided in one embodiment of the present application. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0030] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below with reference to the accompanying drawings and specific implementation methods.

[0031] In the flight simulation of the hypersonic aircraft airfoil, at different inflow Mach numbers and angle of attack Different flight performance will be produced under different flight conditions. It is a dimensionless number that represents the flight speed and is related to the local speed of sound. For example, in normal air, one Mach is approximately equal to 340m / s.

[0032] like Figure 1As shown, the hypersonic aircraft airfoil passes through a positive angle of attack , that is, lifting the wing upward to generate upward lift L To achieve flight. Within a certain range, as the angle of attack The increase in lift of the airfoil L will be raised; and when the angle of attack When the stall angle of attack is exceeded, the lift of the airfoil is L At the same time, the wing design needs to meet certain flight performance requirements. Among them, several key issues are: under this wing model, different inflow Mach numbers How much lift can it provide? L , the position of maximum lift, and the stall angle of attack. Numerical simulation is an important technical means to solve such problems. It can safely and stably determine the relevant parameters through computers and reduce the workload in actual industrial design.

[0033] Based on this, in an exemplary embodiment, Figure 2 As shown, a method for numerical simulation of a hypersonic aircraft is provided, comprising the following steps.

[0034] Step 101: Modeling a hypersonic aircraft airfoil according to a given hypersonic flight simulation condition, and determining an initialization calculation flow field.

[0035] Among them, the given hypersonic flight simulation condition is that the inflow Mach number remains unchanged within a given time period, and the angle of attack changes with time; a triangular grid in the initialization calculation flow field is taken as a unit.

[0036] Step 102: Based on the initialized calculated flow field, at each time step, an improved weighted substantially non-oscillating format spatial reconstruction method is used to construct a reconstruction polynomial vector of each unit at the time step.

[0037] The reconstruction polynomial vector includes: density reconstruction polynomial, momentum reconstruction polynomial and energy reconstruction polynomial; the improved weighted substantially non-oscillation format is a weighted substantially non-oscillation format using unequally spaced templates. The reconstruction polynomial vector is a draft-order polynomial vector.

[0038] Step 103: At each time step, the reconstruction polynomial vector of each unit is corrected by using a correction-preserving method to obtain a reconstruction polynomial correction vector of each unit at the time step.

[0039] Step 104: At each time step, the time discrete term of each unit at the time step is calculated according to the reconstruction polynomial correction vector of each unit.

[0040] The time discrete items include: the density distribution of the simulated flow field, the momentum distribution of the simulated flow field and the energy distribution of the simulated flow field.

[0041] Step 105: Determine the parameter values ​​of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions according to the time discrete items of all units under all time steps; the parameter values ​​include: lift corresponding to different angles of attack, drag corresponding to different angles of attack, and the range of angles of attack at maximum lift.

[0042] The parameter values ​​are used to determine the flight performance of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions.

[0043] Implementing the above steps 101 to 105 can effectively realize the numerical simulation of hypersonic aircraft and improve numerical robustness.

[0044] In another exemplary embodiment of the present application, step 101 specifically includes the following steps.

[0045] 11) Modeling the airfoil of a hypersonic aircraft to obtain an airfoil model. 12) Using triangles to divide the airfoil model to obtain an unstructured triangular mesh; the unstructured triangular mesh includes multiple triangular meshes. 13) Initializing calculation parameters according to a given hypersonic flight simulation condition; the calculation parameters include: the simulated flow field in the horizontal direction Speed u , the simulated flow field in the vertical direction Speed v , the total energy of the simulated flow field E and the pressure of the simulated flow field p 14) constructing an initialization calculation flow field according to the unstructured triangular mesh and the initialized calculation parameters.

[0046] The above step 101 can import the unstructured triangular mesh of the shape of the simulated supersonic problem and read the relevant data to obtain the initialization calculation flow field. In practical applications, a more specific implementation process is as follows.

[0047] After modeling a given hypersonic aircraft airfoil, the unstructured triangular mesh can be obtained by dividing the determined calculation area with triangles, and then the node information of the unstructured triangular mesh is read, where the parameter NNUM represents the number of nodes in the calculation mesh, the parameter ELEM represents the number of cells in the calculation mesh, the node coordinate information of the mesh is stored in the POINT array, and the adjacent relationship between the meshes is stored in the NEIGH array.

[0048] For the given hypersonic flight simulation conditions, initialize the calculation parameters and the inflow Mach number The value range of can be from 0.3 Mach to 5.0 Mach, realizing the simulation of flight conditions from 0.3 Mach subsonic flight to 5.0 Mach hypersonic flight. The value range is from 0 to 30 degrees. The calculation time step parameter CFL = 0.6, the gas medium parameter , according to this information, the initial physical flow field is assigned and the initialized calculation parameters are obtained.

[0049] .

[0050] in, represents the density of the simulated flow field, e is the internal energy of the simulated flow field gas, and initially , The simulated flow field is in the horizontal direction. Momentum , the simulated flow field is in the vertical direction Momentum .

[0051] In another exemplary embodiment of the present application, step 102 specifically includes the following steps.

[0052] 21) At the current time step, for the target unit, select a large space template from the initial calculation flow field ; The large space template Include target unit , adjacent units and sub-adjacent units; the adjacent units include: Adjacent first unit Unit 2 and Unit 3 The secondary adjacent unit includes: Adjacent Unit 4 and Unit 5 , and the second unit Adjacent Unit 6 and Unit 7 and the third unit Adjacent Unit 8 and Unit 9 The large space template can be expressed as , large space templates such as Figure 3 As shown, Figure 3 The serial numbers in correspond to the subscripts of each unit in the large space template.

[0053] 22) At the current time step, for the target unit, four small space templates are selected from the initial calculation flow field, and the four small space templates are: the first small space template , Second Small Space Template , the third small space template And the fourth small space template .like Figure 4 As shown, the first small space template Includes: Target Unit Unit 1 Unit 4 and Unit 5 .like Figure 5 As shown, the second small space template Includes: Target Unit Unit 2 Unit 6 and Unit 7 .like Figure 6 As shown, the third small space template Includes: Target Unit Unit 3 Unit 8 and Unit 9 .like Figure 7 As shown, the fourth small space template Includes: Target Unit Unit 1 Unit 2 and Unit 3 The first small space template can be expressed as ; The second small space template can be expressed as ; The third small space template can be expressed as ; The fourth small space template can be expressed as .

[0054] 23) Constructing a density reconstruction polynomial. Specifically: constructing a quadratic polynomial about density based on the large space template, and constructing four linear polynomials about density based on the four small space templates; calculating the smoothing factors of the quadratic polynomial about density and the four linear polynomials about density to obtain a density smoothing factor, and calculating the density nonlinear final weight based on the density smoothing factor; determining the density reconstruction polynomial based on the quadratic polynomial about density, the four linear polynomials about density, and the density nonlinear final weight.

[0055] 24) Construct momentum reconstruction polynomial. Specifically: construct a quadratic polynomial about momentum according to the large space template, and construct four linear polynomials about momentum according to the four small space templates; calculate the smoothing factors of the quadratic polynomial about momentum and the four linear polynomials about momentum to obtain the momentum smoothing factor, and calculate the momentum nonlinear weight final weight according to the momentum smoothing factor; determine the momentum reconstruction polynomial according to the quadratic polynomial about momentum, the four linear polynomials about momentum and the momentum nonlinear weight final weight.

[0056] 25) Constructing an energy reconstruction polynomial. Specifically: constructing a quadratic polynomial about energy based on the large space template, and constructing four linear polynomials about energy based on the four small space templates; calculating the smoothing factors of the quadratic polynomial about energy and the four linear polynomials about energy to obtain the energy smoothing factor, and calculating the energy nonlinear final weight based on the energy smoothing factor; determining the energy reconstruction polynomial based on the quadratic polynomial about energy, the four linear polynomials about energy, and the energy nonlinear final weight.

[0057] 26) According to the density reconstruction polynomial, momentum reconstruction polynomial and energy reconstruction polynomial determined for the target unit at the current time step, the reconstruction polynomial vector of the target unit at the time step is obtained.

[0058] The above methods for constructing density reconstruction polynomials, momentum reconstruction polynomials, and energy reconstruction polynomials are similar. Taking the density reconstruction polynomial as an example, the construction process of the density reconstruction polynomial is further explained in detail.

[0059] ①Choose a large space template , and then construct a quadratic polynomial about the density To obtain the third-order approximation of density. Since the condition is greater than the unknown quantity, the least square method with equal mean value on the target unit and minimum error on the remaining units is selected for reconstruction. Satisfies the following formula.

[0060] .

[0061] in, Represents the density mean of the target unit; Representation unit The density mean of ; Represents a large space template Except for the target unit The subscript of the unit outside.

[0062] ②Select four small space templates , , and Based on these small space templates, four linear polynomials about density are constructed respectively , Similarly, by least squares, Satisfies the following formula.

[0063] .

[0064] in, Representation unit The density mean of ; Represents a small space template Except for the target unit The subscript of the unit outside.

[0065] ③ Rewrite it according to the quadratic polynomial about density and four linear polynomials about density to obtain the following formula.

[0066] .

[0067] in, represents the linear weight of reconstruction, taking , .

[0068] ④Calculate the smoothing factors of each polynomial , , the smoothness factor is a quantity used to measure the smoothness of a polynomial, and its calculation formula is as follows.

[0069] .

[0070] in, represents the derivative index, ; represents the number of derivatives; Express The derivative index of ; Express The derivative index of ; Express beg subpartial derivative; Express beg Secondary partial derivative; Represents a linear polynomial on density Derivation; when hour, represents the smoothing factor of the quadratic polynomial with respect to density; when hour, Smoothing factor representing a linear polynomial in density.

[0071] ⑤ Calculate the final weight of nonlinear weight, the formula is as follows.

[0072] .

[0073] in, Represents the intermediate variables of the reconstruction process; represents the nonlinear weight before normalization; Represents the nonlinear weight after normalization; is a small positive number that avoids the denominator being zero. .

[0074] ⑥ Calculate the final density reconstruction polynomial, whose expression is as follows.

[0075] .

[0076] in, represents the density reconstruction polynomial; Represents the value of the simulated flow field in the horizontal direction; Represents the value of the simulated flow field in the vertical direction; Indicates the final density nonlinear weight corresponding to the large space template; Represents the linear weight of the reconstruction corresponding to the large space template; represents a quadratic polynomial about density; when hour, represents the linear weight of the reconstruction corresponding to the first small space template, represents the linear polynomial about density corresponding to the first small space template, represents the final density nonlinear weight corresponding to the first small space template; when hour, represents the linear weight of the reconstruction corresponding to the second smallest space template, Represents the linear polynomial about density corresponding to the second small space template, represents the final density nonlinear weight corresponding to the second smallest space template; when hour, represents the linear weight of the reconstruction corresponding to the third small space template, Represents the linear polynomial about density corresponding to the third small space template, represents the final density nonlinear weight corresponding to the third smallest space template; when hour, represents the linear weight of the reconstruction corresponding to the fourth small space template, Represents the linear polynomial about density corresponding to the fourth small space template, Represents the final density nonlinear weight corresponding to the fourth small space template.

[0077] From the above process, we can get the density reconstruction polynomial , the above operations can be repeated for momentum reconstruction polynomial and energy reconstruction polynomial to obtain the corresponding reconstruction polynomials, where and Respectively represent the simulated flow field in the horizontal direction The momentum polynomial and the simulated flow field in the horizontal direction The momentum polynomial of represents the energy reconstruction polynomial, so the final reconstruction polynomial vector It can be expressed as: , T Indicates transpose.

[0078] In another exemplary embodiment of the present application, designing a high-order correction method is very important for the development and application of computational fluid dynamics. When the existing computational fluid dynamics method is used for numerical simulation of hypersonic aircraft, the original correction method used has the following defects: the original correction method introduces an additional CFL (Courant-Friedrichs-Lewy) number restriction, resulting in a significant decrease in computational efficiency; the original correction method has requirements for the numerical integration points of flux calculation; the original correction method needs to rewrite the average value into a numerical integration rule, and on unstructured grids such as triangles and tetrahedrons, it is very difficult to construct such a set of integration points that meet the requirements, making it difficult to promote and apply it in unstructured grids; for different equations, the correction method needs to be redesigned according to the flux.

[0079] In order to overcome the defects of the above-mentioned original correction method, step 103 of the present application adopts a correction method to correct the reconstructed polynomial vector of each unit, and step 103 specifically includes the following steps.

[0080] 31) At the current time step, for the target unit, check whether the density satisfies positivity on the target unit and whether the pressure satisfies positivity on the target unit. Density satisfies positivity, that is, the density is greater than 0, and pressure satisfies positivity, that is, the pressure is greater than 0.

[0081] 32) If the density satisfies positivity on the target unit and the pressure satisfies positivity on the target unit, the reconstruction polynomial vector of the target unit at the current time step is determined as the reconstruction polynomial correction vector.

[0082] 33) If the density satisfies positivity on the target unit and the pressure does not satisfy positivity on the target unit, the over-estimated minimum pressure value is calculated, and the reconstruction polynomial vector of the target unit at the current time step is corrected according to the over-estimated minimum pressure value to obtain a reconstruction polynomial correction vector.

[0083] 34) If the density does not satisfy positivity on the target unit and the pressure satisfies positivity on the target unit, the over-estimated minimum value of the density reconstruction polynomial is calculated, and the density reconstruction polynomial in the reconstruction polynomial vector of the target unit at the current time step is corrected according to the over-estimated minimum value of the density reconstruction polynomial to obtain a corrected reconstruction polynomial vector, and the corrected reconstruction polynomial vector is determined as the reconstruction polynomial correction vector.

[0084] 35) If the density does not satisfy positivity on the target unit and the pressure does not satisfy positivity on the target unit, then the over-estimated minimum value of the density reconstruction polynomial is calculated, and the density reconstruction polynomial in the reconstruction polynomial vector of the target unit at the current time step is corrected according to the over-estimated minimum value of the density reconstruction polynomial to obtain a corrected reconstruction polynomial vector, and the over-estimated minimum value of the pressure is calculated, and the corrected reconstruction polynomial vector is corrected again according to the over-estimated minimum value of the pressure to obtain a reconstruction polynomial correction vector.

[0085] Next, we use the above-mentioned correction method to correct and reconstruct the polynomial vector The process is described in further detail.

[0086] ① Detect the positivity of the density at the detection point on the target unit. If the density positivity is satisfied, then the modified density reconstruction polynomial is set , that is, the density reconstruction polynomial is not modified, otherwise the next step is executed. The detection points on the target unit are as follows Figure 8 shown.

[0087] ② Calculate the over-estimated minimum value of the density reconstruction polynomial. The density reconstruction polynomial can be written as follows.

[0088] .

[0089] in, represents the coefficients of the constructed polynomial; Represents the value of the centroid of the rectangular area contained by the triangular unit in the horizontal direction; The value of the centroid of the rectangular area contained by the triangular unit in the vertical direction; p and q All are non-negative integers.

[0090] Consider the rectangular area contained by the triangular unit, consisting of the following four points Determine the rectangular area.

[0091] in The triangle unit is horizontally The minimum value of The triangle unit is horizontally The maximum value of The triangle unit is in the vertical direction The minimum value of The triangle unit is in the vertical direction The maximum value of .

[0092] .

[0093] in, , . Consider density reconstruction polynomial basis function The maximum value problem of It can be solved .

[0094] in, and represents the minimum and maximum values ​​of the density reconstruction polynomial basis function on the rectangular area, Represents a rectangular area, The centroid of the rectangular area contained by the triangular unit, ; Indicate point The function value of Indicate point The function value of Indicate point The function value of Indicate point The function value of Indicate point Therefore, the overestimated value of the density reconstruction polynomial is the minimum , defined as follows.

[0095] .

[0096] in, express The symbolic function of ,but ,otherwise .

[0097] ③The modified density reconstruction polynomial is expressed as: .

[0098] in, Represents a parameter from 0 to 1, the specific form is .

[0099] ④ Detect the positivity of the pressure. First, the corrected reconstruction polynomial vector is recorded as , the target unit mean vector is recorded as , Indicates that the simulated flow field of the target unit is in the horizontal direction x The momentum mean of Indicates that the simulated flow field of the target unit is in the vertical direction y The momentum mean of Represents the mean energy and pressure of the target unit , Represents the specific heat ratio, which is usually 1.4 for ideal gas. Calculate the pressure value at the detection point. If the pressure is positive, reconstruct the polynomial correction vector , otherwise perform the following correction steps.

[0100] ⑤Use the same operation as density to obtain the minimum value of overestimated pressure .

[0101] ⑥The reconstruction polynomial correction vector is expressed as: .in, It is a correction parameter ranging from 0 to 1, and its specific form is: .

[0102] In order to improve the computational efficiency and numerical robustness of the numerical simulation of hypersonic aircraft, this embodiment constructs a numerical solution method for hypersonic problems for unstructured grids based on US-WENO spatial reconstruction combined with a new correction method. The adopted US-WENO spatial reconstruction has the characteristics of arbitrary linear weights, and has the advantages of compact spatial templates and more robust numerical formats. The new correction method corrects the polynomial through detection and restriction operations. It does not rely on a specific quadrature formula, can use a larger CFL number, and has stronger numerical robustness and computational efficiency. In summary, this embodiment is simple, efficient, robust, easy to implement, and successfully solves or avoids the defects of traditional methods. The designed hypersonic aircraft numerical simulation method has more practical value and promotion prospects.

[0103] In another exemplary embodiment of the present application, step 104 specifically includes the following steps.

[0104] 1) At the current time step, for the target unit, the spatial discrete term is calculated according to the reconstruction polynomial correction vector of the target unit. The specific calculation process of this step is as follows.

[0105] After step 103, the reconstruction polynomial correction vector is obtained. , based on this reconstruction polynomial correction vector calculation space discrete term, the calculation formula is as follows.

[0106] .

[0107] in, Target unit The borders of express The area of express The unit external normal vector of represents the spatial discrete term, represents the numerical flux, represents the unit mean vector about time t, represents the cell mean vector, t Indicates time. , , , .

[0108] The line integral will be discretized using the two-point Gaussian quadrature formula on each edge. For example, and An edge with two Gaussian quadrature nodes and The calculation formula is as follows.

[0109] .

[0110] The weights corresponding to the two Gaussian quadrature nodes are Based on this formula, discretization is performed through numerical integration, and the discretization formula is as follows.

[0111] .

[0112] in, Represents the triangle The length of the side, Indicates The quadrature weight of the quadrature node, Indicates The first of quadrature nodes coordinate, Indicates The first of quadrature nodes coordinate, Indicates The unit external normal vector of the edge, Indicates The first The numerical flux at each quadrature node. , , which can be calculated by Lax-Friedrichs numerical flux, and the calculation formula is as follows.

[0113] .

[0114] in, Indicates the coordinate point Higher-order reconstruction values ​​of the medial approximation; Indicates the coordinate point Higher-order reconstruction values ​​for the outer approximation. Take The upper bound of the eigenvalues ​​of the Jacobian matrix in the direction, and are the high-order reconstruction values ​​approximated inside and outside different Gaussian points of the target unit, e.g. for: , Indicates the coordinate point The reconstruction polynomial correction vector at Can be obtained similarly.

[0115] 2) The spatial discrete term is analyzed using the third-order Runge-Kutta method Discretize to obtain the time discrete item of the target unit under this time step, and its calculation formula is as follows.

[0116] .

[0117] in, represents the time discretization term at the first time step of the third-order Runge–Kutta method; represents the time discretization term at the second time step of the third-order Runge–Kutta method; represents the third-order Runge–Kutta method. The time discrete term at time steps; represents the third-order Runge–Kutta method The time discrete term at time steps; A spatially discrete term representing the second time layer; A spatially discrete term representing the third time layer; represents the spatially discrete term of the first time layer; is the time step, The time discrete items include: the density distribution of the simulated flow field , Momentum distribution of the simulated flow field and , Energy distribution of the simulated flow field .

[0118] In another exemplary embodiment of the present application, step 105 specifically includes: calculating the lift coefficient and drag coefficient of the hypersonic aircraft airfoil model under a given hypersonic flight simulation condition according to the time discrete terms of all units under all time steps; calculating the lift corresponding to different angles of attack and the drag corresponding to different angles of attack in a given time period according to the lift coefficient, the drag coefficient, the density distribution of the simulated flow field, the inflow Mach number in a given time period, and the area of ​​the airfoil model; determining the range of the angle of attack at maximum lift according to the lift corresponding to different angles of attack; determining the parameter value of the hypersonic aircraft airfoil model under a given hypersonic flight simulation condition according to the lift corresponding to different angles of attack, the drag corresponding to different angles of attack, and the range of the angle of attack at maximum lift.

[0119] Specifically, steps 102 to 104 are repeated until the time discrete items of all units under all time steps are calculated, and the numerical calculation process is completed at this time, and the numerical model results, i.e., the time discrete items, are obtained. The numerical model results characterize the distribution of the flow field under this working condition. Steps 102 to 104 implement the use of numerical methods to simulate the hypersonic aircraft airfoil model.

[0120] According to the results of the numerical model, the simulation results of the corresponding hypersonic aircraft airfoil model under this condition are obtained, and the lift coefficient of the hypersonic aircraft airfoil model under this flight condition is obtained by post-processing. , drag coefficient , and surface pressure distribution, etc., further, according to the formula and Calculate lift and drag. Where, L Indicates lift; D Indicates resistance; ρ represents the calculated density; Ma Indicates the incoming flow Mach number, which is the initial setting; S Represents the area of ​​the airfoil model, which is a parameter related to the model and is fixed.

[0121] Among them, the lift coefficient is a quantity that represents the magnitude of lift, and the drag coefficient is similar. Through this quantitative parameter value, the flight performance of the defined airfoil model under the flight conditions of the incoming flow Mach number and angle of attack can be obtained. In practical applications, it is only necessary to set the angle of attack to gradually increase from 0 degrees to obtain the lift coefficient and drag coefficient at each angle of attack, and finally the change of lift and drag of this wing model with the change of angle of attack can be obtained. In addition, different incoming flow Mach numbers can be set and the above numerical experimental operations can be repeated. Based on the obtained angle of attack and lift coefficient diagram, the performance of this wing model can be determined. The designer can determine whether this model meets the requirements based on the flight performance given by the numerical solution, and then further iterate and modify the model, such as increasing the chord length of the wing, increasing the effective area, and increasing the curvature of the wing.

[0122] At this point, the lift and drag under a specific incoming flow Mach number and angle of attack are calculated. By resetting the angle of attack and repeating the above calculation process, the lift and drag of this model can be obtained. By adjusting the value of the angle of attack, different lift and drag can be obtained, and then the maximum lift of this model and the range of angles of attack where the maximum lift is obtained can be obtained.

[0123] This application gives a model, such as a hypersonic aircraft airfoil model, and specifies calculation conditions, such as specifying the incoming flow Mach number and angle of attack. Through the above calculation process, the flow field distribution (density, velocity, pressure, etc.) and aerodynamic force (lift, drag, lift coefficient, drag coefficient, etc.) can be obtained. Therefore, by setting different incoming flow Mach numbers and angles of attack, a curve of lift and drag changing with the incoming flow Mach number and angle of attack can be obtained. This curve can reflect the flight performance of the hypersonic aircraft airfoil model. Compared with the current method of determining flight performance through experimental methods, this application can be calculated through a program, which is simple and can avoid consuming a lot of resources. Further, the flight performance of the hypersonic aircraft airfoil model is determined, and the hypersonic aircraft airfoil model can be improved according to the flight performance (for example, changing the length, curvature, curve distribution, etc. of the airfoil), and the ideal distribution curve can be recalculated (for example, making the lift as large as possible). The numerical solution process of the present application is a numerical simulation of the airfoil under a specific incoming flow Mach number and angle of attack, which can provide data that can only be obtained through experimental methods. It is a simple and economical alternative to experimental methods.

[0124] Compared with traditional non-structural numerical simulation solvers, this application has the following advantages.

[0125] 1) US-WENO spatial reconstruction is adopted, which has the characteristics of arbitrary linear weights, compact spatial templates, and more robust numerical formats. 2) The new positive preservation method allows the use of a CFL number of 0.6 to simulate high-level problems, which has better computational efficiency. 3) The discretization of boundary fluxes can be any numerical integration point that meets the accuracy, which improves the practicality of the method.

[0126] Advantages 1) The reconstruction method is derived from the US-WENO spatial reconstruction, which selects a large central space template to achieve high-order accuracy and sets a low-order small space template to control the oscillation near the discontinuity. The nonlinear combination of polynomials of different orders is realized by calculating the smoothing factor and nonlinear weights. This new template selection and reconstruction method has the advantages of arbitrary linear weights and stronger numerical robustness.

[0127] Advantage 2) comes from the construction idea of ​​correcting the entire polynomial so that the entire polynomial satisfies the physical properties, that is, the density is greater than zero and the pressure is greater than zero. The traditional correction method chooses to correct the value at the Gauss-Lobatto integration node in the unit, so its correction is not complete, that is, it is possible that the corrected polynomial still has negative density or negative pressure in certain areas of the unit, even if the corrected polynomial meets the physical properties at the Gauss-Lobatto point value. Its incomplete correction results in the need to add an additional CFL number restriction to its correction method, while the new correction method designed in this application can ensure that the density and pressure polynomials are positive in the entire interval. Therefore, the new correction method does not need to introduce additional CFL number restrictions, which greatly improves the calculation efficiency and is very beneficial for large-scale engineering applications.

[0128] Advantage 3) The construction of the new correction-preserving format designed does not require the average value to be rewritten as a numerical integration rule, while the traditional correction-preserving method requires and needs to be brought into the format for derivation. The new method designed in this application only requires a set of nodes when constructing the polynomial, and it can be taken arbitrarily in essence, as long as the conditions for constructing the polynomial are met. Therefore, when calculating the numerical integral of the boundary flux in this application, any numerical integration rule that meets the design accuracy can be adopted, which is easy to promote and apply. At the same time, when the traditional correction-preserving method is applied to unstructured grids such as triangles and tetrahedrons, it is very difficult to construct a numerical integration rule that meets the conditions, and it is difficult to promote to a higher order. The new correction-preserving method designed in this application does not require such an integration rule, which greatly reduces the complexity of the new correction-preserving method in unstructured grids, further improving its scope of application in engineering problems.

[0129] The hypersonic aircraft numerical simulation method of all the above embodiments can be used as an unstructured numerical solver for hypersonic problems. For the hypersonic aircraft numerical simulation problem, an unstructured triangular grid and the incoming flow Mach number and angle of attack within a given time period are input for numerical simulation, and the numerical simulation results after steady-state convergence are given, such as Mach number distribution, pressure distribution, surface pressure coefficient distribution, etc., to complete the numerical simulation process, and the lift and drag of the calculation model are obtained according to the calculation, and the calculation angle of attack is adjusted. The calculation process is repeated to obtain the lift and drag under different angles of attack, and finally the maximum lift, drag and corresponding range of the angle of attack of this calculation model are obtained.

[0130] Based on the same inventive concept, the embodiment of the present application also provides a hypersonic aircraft numerical simulation device for implementing the hypersonic aircraft numerical simulation method involved above. The implementation scheme for solving the problem provided by the device is similar to the implementation scheme recorded in the above method, so the specific limitations in one or more hypersonic aircraft numerical simulation device embodiments provided below can refer to the limitations of the hypersonic aircraft numerical simulation method above, and will not be repeated here.

[0131] In an exemplary embodiment, Fig. 9 As shown, a hypersonic aircraft numerical simulation device is provided, which includes the following modules.

[0132] The computational flow field construction module 901 is used to model the hypersonic aircraft airfoil according to a given hypersonic flight simulation condition and determine the initial computational flow field; the given hypersonic flight simulation condition is that the inflow Mach number remains unchanged within a given time period, and the angle of attack changes with time; a triangular mesh in the initial computational flow field is taken as a unit.

[0133] The spatial reconstruction module 902 is used to construct a reconstruction polynomial vector of each unit at each time step based on the initialized calculated flow field by using an improved weighted substantially non-oscillation format spatial reconstruction method at each time step; the reconstruction polynomial vector includes: a density reconstruction polynomial, a momentum reconstruction polynomial and an energy reconstruction polynomial; the improved weighted substantially non-oscillation format is a weighted substantially non-oscillation format using unequally spaced templates.

[0134] The correction module 903 is used to correct the reconstruction polynomial vector of each unit at each time step by using a correction-preserving method to obtain a reconstruction polynomial correction vector of each unit at the time step.

[0135] The numerical calculation module 904 is used to calculate the time discrete term of each unit at each time step according to the reconstruction polynomial correction vector of each unit at the time step; the time discrete term includes: the density distribution of the simulated flow field, the momentum distribution of the simulated flow field and the energy distribution of the simulated flow field.

[0136] The parameter determination module 905 is used to determine the parameter values ​​of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions according to the time discrete items of all units under all time steps; the parameter values ​​include: the lift corresponding to different angles of attack, the drag corresponding to different angles of attack, and the range of the angle of attack at maximum lift; the parameter values ​​are used to determine the flight performance of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions.

[0137] The above-mentioned hypersonic aircraft numerical simulation device first calculates the lift and drag at different angles of attack for a given hypersonic aircraft airfoil at a given inflow Mach number, and gives the range of lift that can be provided and the range of angles of attack at maximum lift, and can also give key parameters such as the stall angle of attack. Secondly, different Mach numbers can be replaced to obtain the key flight parameters of this airfoil at different Mach numbers. The device can effectively realize the numerical simulation of hypersonic aircraft, improve numerical robustness, and thus determine the flight performance of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions.

[0138] In an exemplary embodiment, a computer device is provided. The computer device may be a server or a terminal. The internal structure diagram thereof may be as follows: Fig.10 As shown. The computer device includes a processor, a memory, an input / output interface (Input / Output, referred to as I / O) and a communication interface. Among them, the processor, the memory and the input / output interface are connected through a system bus, and the communication interface is connected to the system bus through the input / output interface. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store the initialization calculation flow field. The input / output interface of the computer device is used to exchange information between the processor and an external device. The communication interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a method for numerical simulation of a hypersonic aircraft is implemented.

[0139] Those skilled in the art will understand that Fig.10 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0140] In an exemplary embodiment, a computer device is further provided, including a memory and a processor, wherein a computer program is stored in the memory, and the processor implements the steps in the above-mentioned method embodiments when executing the computer program.

[0141] In an exemplary embodiment, a computer-readable storage medium is provided, storing a computer program, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0142] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to the memory, database or other medium used in the embodiments provided in this application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetoresistive random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM may be in various forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM).

[0143] The database involved in each embodiment provided in this application may include at least one of a relational database and a non-relational database. The non-relational database may include a distributed database based on blockchain, etc., but is not limited thereto. The processor involved in each embodiment provided in this application may be a general-purpose processor, a central processing unit, a graphics processor, a digital signal processor, a programmable logic device, etc., but is not limited thereto.

[0144] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0145] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and core ideas of this application. At the same time, for those skilled in the art, according to the ideas of this application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting this application.

Claims

1. A method for numerical simulation of a hypersonic aircraft, characterized in that: The hypersonic vehicle numerical simulation method comprises: Modeling a hypersonic aircraft airfoil according to a given hypersonic flight simulation condition to determine an initialization calculation flow field; the given hypersonic flight simulation condition is that the inflow Mach number remains unchanged within a given time period, and the angle of attack changes with time; a triangular grid in the initialization calculation flow field is taken as a unit; Based on the initialization calculation flow field, at each time step, a reconstruction polynomial vector of each unit at the time step is constructed by using an improved weighted substantially non-oscillating format spatial reconstruction method; the reconstruction polynomial vector includes: a density reconstruction polynomial, a momentum reconstruction polynomial and an energy reconstruction polynomial; the improved weighted substantially non-oscillating format is a weighted substantially non-oscillating format using unequally spaced templates; At each time step, the reconstruction polynomial vector of each unit is corrected by using the correction method to obtain the reconstruction polynomial correction vector of each unit at the time step; At each time step, a time discrete term of each unit at the time step is calculated according to a reconstruction polynomial correction vector of each unit; the time discrete term includes: a density distribution of the simulated flow field, a momentum distribution of the simulated flow field, and an energy distribution of the simulated flow field; The parameter values ​​of a hypersonic aircraft airfoil model under given hypersonic flight simulation conditions are determined according to the time discrete items of all units under all time steps; the parameter values ​​include: lift corresponding to different angles of attack, drag corresponding to different angles of attack, and the range of angles of attack at maximum lift; the parameter values ​​are used to determine the flight performance of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions.

2. The method for numerical simulation of a hypersonic vehicle according to claim 1, characterized in that: The hypersonic aircraft airfoil is modeled according to the given hypersonic flight simulation conditions, and the initialization calculation flow field is determined, including: Modeling the airfoil of a hypersonic vehicle to obtain an airfoil model; The airfoil model is divided into triangles to obtain an unstructured triangular mesh; the unstructured triangular mesh includes a plurality of triangular meshes; Initialize calculation parameters according to a given hypersonic flight simulation condition; the calculation parameters include: the velocity of the simulated flow field in the horizontal direction, the velocity of the simulated flow field in the vertical direction, the total energy of the simulated flow field, and the pressure of the simulated flow field; An initialized calculation flow field is constructed according to the unstructured triangular mesh and the initialized calculation parameters.

3. The method for numerical simulation of a hypersonic vehicle according to claim 1, characterized in that: Based on the initialization calculation flow field, at each time step, an improved weighted substantially non-oscillating format spatial reconstruction method is used to construct a reconstruction polynomial vector of each unit at the time step, specifically including: At the current time step, for the target unit, a large space template is selected from the initialized calculation flow field; the large space template includes the target unit, adjacent units and secondary adjacent units; the adjacent units include: the first unit, the second unit and the third unit adjacent to the target unit; the secondary adjacent units include: the fourth unit and the fifth unit adjacent to the first unit, the sixth unit and the seventh unit adjacent to the second unit, and the eighth unit and the ninth unit adjacent to the third unit; At the current time step, for the target unit, four small space templates are selected from the initialized calculation flow field, and the four small space templates are: a first small space template, a second small space template, a third small space template and a fourth small space template; the first small space template includes: a target unit, a first unit, a fourth unit and a fifth unit; the second small space template includes: a target unit, a second unit, a sixth unit and a seventh unit; the third small space template includes: a target unit, a third unit, an eighth unit and a ninth unit; the fourth small space template includes: a target unit, a first unit, a second unit and a third unit; Constructing a quadratic polynomial about density according to the large space template, and constructing four linear polynomials about density according to the four small space templates; Calculate the smoothing factors of the quadratic polynomial on density and four linear polynomials on density to obtain the density smoothing factors, and calculate the density nonlinear final weight according to the density smoothing factors; Determine a density reconstruction polynomial according to a quadratic polynomial on density, four linear polynomials on density and density nonlinear weights; Constructing a quadratic polynomial about momentum according to the large space template, and constructing four linear polynomials about momentum according to the four small space templates; Calculate the smoothing factors of the quadratic polynomial about momentum and four linear polynomials about momentum to obtain the momentum smoothing factor, and calculate the momentum nonlinear final weight according to the momentum smoothing factor; Determine a momentum reconstruction polynomial according to a quadratic polynomial about momentum, four linear polynomials about momentum and momentum nonlinear weights; Constructing a quadratic polynomial about energy according to the large space template, and constructing four linear polynomials about energy according to the four small space templates; Calculate the smoothing factors of the quadratic polynomial about energy and four linear polynomials about energy to obtain the energy smoothing factor, and calculate the energy nonlinear final weight according to the energy smoothing factor; Determine an energy reconstruction polynomial according to a quadratic polynomial about energy, four linear polynomials about energy and energy nonlinear weights; According to the density reconstruction polynomial, momentum reconstruction polynomial and energy reconstruction polynomial determined for the target unit at the current time step, a reconstruction polynomial vector of the target unit at the time step is obtained.

4. The method for numerical simulation of a hypersonic vehicle according to claim 1, characterized in that: At each time step, the reconstruction polynomial vector of each unit is corrected by using the correction method to obtain the reconstruction polynomial correction vector of each unit at the time step, specifically including: At the current time step, for the target unit, detecting whether the density satisfies positivity on the target unit and whether the pressure satisfies positivity on the target unit; If the density satisfies positivity on the target unit and the pressure satisfies positivity on the target unit, the reconstruction polynomial vector of the target unit at the current time step is determined as the reconstruction polynomial correction vector; If the density satisfies positivity on the target unit and the pressure does not satisfy positivity on the target unit, the over-estimated minimum pressure value is calculated, and the reconstruction polynomial vector of the target unit at the current time step is corrected according to the over-estimated minimum pressure value to obtain a reconstruction polynomial correction vector; If the density does not satisfy positivity on the target unit and the pressure satisfies positivity on the target unit, the over-estimated minimum value of the density reconstruction polynomial is calculated, and the density reconstruction polynomial in the reconstruction polynomial vector of the target unit at the current time step is corrected according to the over-estimated minimum value of the density reconstruction polynomial to obtain a corrected reconstruction polynomial vector, and the corrected reconstruction polynomial vector is determined as the reconstruction polynomial correction vector; If the density does not satisfy positivity on the target unit and the pressure does not satisfy positivity on the target unit, the over-estimated minimum value of the density reconstruction polynomial is calculated, and the density reconstruction polynomial in the reconstruction polynomial vector of the target unit at the current time step is corrected according to the over-estimated minimum value of the density reconstruction polynomial to obtain a corrected reconstruction polynomial vector, and the over-estimated minimum pressure value is calculated, and the corrected reconstruction polynomial vector is corrected again according to the over-estimated minimum pressure value to obtain a reconstruction polynomial correction vector.

5. The method for numerical simulation of a hypersonic vehicle according to claim 1, characterized in that: At each time step, the time discrete term of each unit at the time step is calculated according to the reconstruction polynomial correction vector of each unit, including: At the current time step, for the target unit, the spatial discrete term is calculated according to the reconstruction polynomial correction vector of the target unit; The spatial discrete term is discretized by using the third-order Runge-Kutta method to obtain the time discrete term of the target unit under the time step.

6. The method for numerical simulation of a hypersonic vehicle according to claim 1, characterized in that: The parameter values ​​of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions are determined according to the time discrete items of all units at all time steps, including: Calculate the lift coefficient and drag coefficient of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions according to the time discrete items of all units at all time steps; Calculating the lift corresponding to different angles of attack and the drag corresponding to different angles of attack within a given time period according to the lift coefficient, the drag coefficient, the density distribution of the simulated flow field, the inflow Mach number within a given time period, and the area of ​​the airfoil model; Determine the range of attack angles for maximum lift based on the lift corresponding to different attack angles; The parameter values ​​of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions are determined according to the lift corresponding to different angles of attack, the drag corresponding to different angles of attack and the range of angles of attack at maximum lift.

7. The method for numerical simulation of a hypersonic vehicle according to claim 3, characterized in that: The expression of the density reconstruction polynomial is: ； in, represents the density reconstruction polynomial; Represents the value of the simulated flow field in the horizontal direction; Represents the value of the simulated flow field in the vertical direction; Indicates the final density nonlinear weight corresponding to the large space template; Represents the linear weight of the reconstruction corresponding to the large space template; represents a quadratic polynomial about density; when hour, represents the linear weight of the reconstruction corresponding to the first small space template, represents the linear polynomial about density corresponding to the first small space template, represents the final density nonlinear weight corresponding to the first small space template; when hour, represents the linear weight of the reconstruction corresponding to the second smallest space template, Represents the linear polynomial about density corresponding to the second small space template, represents the final density nonlinear weight corresponding to the second smallest space template; when hour, represents the linear weight of the reconstruction corresponding to the third small space template, Represents the linear polynomial about density corresponding to the third small space template, represents the final density nonlinear weight corresponding to the third smallest space template; when hour, represents the linear weight of the reconstruction corresponding to the fourth small space template, Represents the linear polynomial about density corresponding to the fourth small space template, Represents the final density nonlinear weight corresponding to the fourth small space template.

8. A hypersonic vehicle numerical simulation device, characterized in that: The hypersonic aircraft numerical simulation device comprises: A computational flow field construction module is used to model a hypersonic aircraft airfoil according to a given hypersonic flight simulation condition and determine an initial computational flow field; the given hypersonic flight simulation condition is that the inflow Mach number remains unchanged within a given time period, and the angle of attack changes with time; a triangular grid in the initial computational flow field is taken as a unit; A spatial reconstruction module is used to construct a reconstruction polynomial vector of each unit at each time step based on the initialization calculation flow field by using an improved weighted substantially non-oscillation format spatial reconstruction method at each time step; the reconstruction polynomial vector includes: a density reconstruction polynomial, a momentum reconstruction polynomial and an energy reconstruction polynomial; the improved weighted substantially non-oscillation format is a weighted substantially non-oscillation format using unequally spaced templates; A correction module is used to correct the reconstruction polynomial vector of each unit at each time step by using a correction-preserving method to obtain a reconstruction polynomial correction vector of each unit at the time step; A numerical calculation module is used to calculate the time discrete term of each unit at each time step according to the reconstruction polynomial correction vector of each unit at the time step; the time discrete term includes: the density distribution of the simulated flow field, the momentum distribution of the simulated flow field and the energy distribution of the simulated flow field; A parameter determination module is used to determine the parameter values ​​of a hypersonic aircraft airfoil model under given hypersonic flight simulation conditions according to the time discrete items of all units under all time steps; the parameter values ​​include: lift corresponding to different angles of attack, drag corresponding to different angles of attack, and the range of angles of attack at maximum lift; the parameter values ​​are used to determine the flight performance of the hypersonic aircraft airfoil model under given hypersonic flight simulation conditions.

9. A computer device comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the hypersonic aircraft numerical simulation method according to any one of claims 1 to 7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the method for numerical simulation of a hypersonic aircraft according to any one of claims 1 to 7 is implemented.

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