Calculation method, equipment and medium for the standard model of compressible turbulence of ablative particles

Abstract

The present application discloses a method, device, and medium for calculating a standard model of compressible turbulence of ablative particles, belonging to the field of compressible turbulence. The method comprises: obtaining a target velocity spectrum vector of the compressible turbulence based on the energy equation according to the initial parameters of the compressible turbulence; performing an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain a target physical space velocity vector of the compressible turbulence; obtaining raw data of the compressible turbulence according to the target physical space velocity vector; the raw data includes: a density variable, a temperature variable, and a velocity vector that vary with time; obtaining statistics of the compressible turbulence according to the raw data of the compressible turbulence; and determining the friction and heat flow on the surface of the aircraft according to the statistics of the compressible turbulence. The present application can obtain statistics of compressible isotropic uniform turbulence of particles, and by studying the interaction between the compressible isotropic uniform turbulence and the ablative particles, it is possible to predict the friction and heat flow on the surface of the aircraft.

Description

Technical Field

[0001] The present application relates to the field of compressible turbulence, and in particular to a calculation method, device, equipment and computer-readable storage medium for a standard model of compressible turbulence of ablative particles. Background Art

[0002] Under extreme mechanical conditions, ablation can occur at the nose of an aircraft. Ablated particles can enter the downstream boundary layer, disrupting the flow in the compressible boundary layer and affecting the mechanisms that generate friction and heat flux. Lack of understanding of the mechanisms of friction and heat flux can lead to redundant aircraft designs and the inability to utilize effective flight paths. Therefore, it is necessary to study the interaction mechanism between compressible, isotropic, uniform turbulence and ablative particles to predict friction and heat flux in the ablative particle boundary layer.

[0003] Current direct numerical simulation methods are all aimed at the interaction mechanism between incompressible, isotropic, uniform turbulence and fluidized bed particles, and the parameter range of the particles is specific to fluidized bed problems. Its direct numerical simulation database is also targeted at subgrid models of fluidized bed-type particle two-phase flows. It is worth mentioning that because direct numerical simulation solvers require huge computational grids, this is beyond the capacity of contemporary supercomputing resources and technologies. Limited by the computational scale that direct numerical simulation can withstand, numerical software platforms that solve industrial-scale problems must adopt particle two-phase flow solvers based on subgrid models. Therefore, the role of direct numerical simulation is to provide an accurate database for the development of subgrid models.

[0004] Incompressible turbulence refers to turbulence in which the density of the fluid does not change much, such as air with a low flow rate, or water, oil, etc. Since the fluid is not compressible, there is no energy equation or the energy equation has little effect. Compressible turbulence refers to turbulence in which the density of the fluid changes greatly, such as gas with a high flow rate. Since the fluid is compressible, the energy equation cannot be ignored. The compressibility of the fluid can lead to changes in density and temperature, which in turn affects the dynamic and thermodynamic processes of compressible turbulence. Therefore, existing technical solutions cannot be used to study the interaction mechanism between compressible isotropic uniform turbulence and ablative particles. Summary of the Invention

[0005] The purpose of this application is to provide a calculation method, device, equipment and computer-readable storage medium for a standard model of compressible turbulence of ablative particles, which can obtain the statistics of compressible isotropic uniform turbulence of particles, and by studying the interaction between compressible isotropic uniform turbulence and ablative particles, it is possible to predict the friction and heat flow on the aircraft surface.

[0006] To achieve the above objectives, the present application provides a calculation method for a standard model of compressible turbulence of ablative particles, comprising:

[0007] According to initial parameters of the compressible turbulent flow, a target velocity spectrum vector of the compressible turbulent flow is obtained based on an energy equation;

[0008] Performing an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain a target physical space velocity vector of the compressible turbulent flow;

[0009] According to the target physical space velocity vector, raw data of the compressible turbulent flow is obtained; the raw data includes: a density variable, a temperature variable and a velocity vector that change with time;

[0010] Obtaining statistics of the compressible turbulent flow according to the original data of the compressible turbulent flow;

[0011] The friction and heat flow on the surface of the aircraft are determined based on the statistics of the compressible turbulent flow.

[0012] Optionally, performing an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain the target physical space velocity vector of the compressible turbulent flow includes:

[0013] Performing a step-by-step inverse Fourier spectrum transform on the target velocity spectrum vector to obtain the target physical space velocity vector of the compressible turbulent flow.

[0014] Optionally, obtaining the statistics of the compressible turbulent flow according to the original data of the compressible turbulent flow includes:

[0015] The original data of the compressible turbulent flow is input into a particle two-phase flow parallel calculation solver to obtain the statistics of the compressible turbulent flow.

[0016] Optionally, obtaining the target velocity spectrum vector of the compressible turbulent flow based on the energy equation according to the initial parameters of the compressible turbulent flow includes:

[0017] According to the initial parameters of compressible forced turbulence, the physical space velocity vector at each moment is obtained;

[0018] Performing a Fourier spectrum forward transform on the physical space velocity vector at each moment to obtain a velocity spectrum vector at each moment;

[0019] The turbulent kinetic energy is applied to the velocity spectrum vector at each moment to obtain the target velocity spectrum vector at each moment.

[0020] Optionally, obtaining the physical space velocity vector at each moment based on the initial parameters of the compressible forced turbulence includes:

[0021] The initial parameters of the compressible forced turbulence are input into the parallel calculation solver of the granular two-phase flow to obtain the physical space velocity vector at each moment.

[0022] Optionally, obtaining the target velocity spectrum vector of the compressible turbulent flow based on the energy equation according to the initial parameters of the compressible turbulent flow includes:

[0023] Obtaining an initial value energy spectrum of the compressible decaying turbulence according to initial parameters of the compressible decaying turbulence;

[0024] According to the initial value energy spectrum of the compressible decaying turbulence, a target velocity spectrum vector at the initial moment is obtained.

[0025] Optionally, obtaining the target velocity spectrum vector at the initial moment according to the initial value energy spectrum of the compressible decaying turbulence includes:

[0026] Obtaining an intermediate component of a velocity spectrum vector according to an initial value energy spectrum of the compressible decaying turbulence;

[0027] A target velocity spectrum vector at an initial moment is obtained according to the intermediate component of the velocity spectrum vector.

[0028] To achieve the above objectives, the present application also provides a calculation device for a standard model of compressible turbulence of ablative particles, comprising:

[0029] a target velocity spectrum vector module, configured to obtain a target velocity spectrum vector of the compressible turbulent flow based on an energy equation according to initial parameters of the compressible turbulent flow;

[0030] a target physical space velocity vector module, configured to perform an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain a target physical space velocity vector of the compressible turbulent flow;

[0031] A raw data module, configured to obtain raw data of the compressible turbulent flow according to the target physical space velocity vector; the raw data including: a density variable, a temperature variable, and a velocity vector that vary with time;

[0032] A statistics module, configured to obtain statistics of the compressible turbulent flow based on the original data of the compressible turbulent flow;

[0033] The friction and heat flow module is used to determine the friction and heat flow on the surface of the aircraft based on the statistics of the compressible turbulence.

[0034] To achieve the above objectives, the present application also provides a device for calculating a standard model of compressible turbulence of ablative particles, comprising:

[0035] Memory for storing computer programs;

[0036] The processor is configured to implement the steps of the above-mentioned calculation method of the compressible turbulence standard model of ablation particles when executing the computer program.

[0037] To achieve the above objectives, the present application also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the steps of the calculation method of the compressible turbulence standard model of ablation particles as described above are implemented.

[0038] The present application provides a calculation method for a standard model of compressible turbulence of ablative particles, comprising: obtaining a target velocity spectrum vector of the compressible turbulence based on an energy equation according to initial parameters of the compressible turbulence; performing an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain a target physical space velocity vector of the compressible turbulence; obtaining raw data of the compressible turbulence according to the target physical space velocity vector; the raw data including a density variable, a temperature variable and a velocity vector that vary with time; obtaining statistics of the compressible turbulence according to the raw data of the compressible turbulence; and determining the friction and heat flow on the surface of an aircraft according to the statistics of the compressible turbulence.

[0039] Clearly, this application can obtain statistics for compressible, isotropic, uniform turbulence of particles. By studying the interaction between compressible, isotropic, uniform turbulence and ablative particles, it can predict friction and heat flow on aircraft surfaces. Furthermore, it can be used to establish a database for direct numerical simulations, providing support for the development of corresponding subgrid simulations of particle two-phase flows. This application also provides a computational device, apparatus, and computer-readable storage medium for a standard model of compressible turbulence of ablative particles, all of which exhibit the aforementioned beneficial effects. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are merely embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without any creative work.

[0041] Figure 1 A flow chart of a calculation method for a standard model of compressible turbulence of ablative particles provided in an embodiment of the present application;

[0042] Figure 2 A schematic diagram of a flow chart of a calculation method for a standard model of compressible decay turbulence of ablative particles provided in an embodiment of the present application;

[0043] Figure 3 A schematic diagram of a flow chart of a calculation method for a standard model of compressible forced turbulence of ablative particles provided in an embodiment of the present application;

[0044] Figure 4Schematic diagram of parallel and reduced step-by-step Fourier transform in the X and Y directions provided in an embodiment of the present application;

[0045] Figure 5 This is a structural block diagram of a calculation device for a standard model of compressible turbulence of ablative particles provided in an embodiment of the present application. DETAILED DESCRIPTION

[0046] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0047] Please refer to Figure 1 , Figure 1 A flowchart of a method for calculating a standard model of compressible turbulence of ablative particles provided in an embodiment of the present application, the method may include:

[0048] S101: According to initial parameters of the compressible turbulent flow, a target velocity spectrum vector of the compressible turbulent flow is obtained based on an energy equation.

[0049] This embodiment does not limit the specific method for obtaining the target velocity spectrum vector. The specific method for obtaining the target velocity spectrum vector can be determined according to the type of compressible turbulence. For example, when the compressible turbulence is compressible forced turbulence, this embodiment can obtain the physical space velocity vector at each moment based on the initial parameters of the compressible forced turbulence; perform a Fourier spectrum forward transform on the physical space velocity vector at each moment to obtain the velocity spectrum vector at each moment; apply turbulent kinetic energy to the velocity spectrum vector at each moment to obtain the target velocity spectrum vector at each moment; when the compressible turbulence is compressible decaying turbulence, this embodiment can obtain the initial value energy spectrum of the compressible decaying turbulence based on the initial parameters of the compressible decaying turbulence; and obtain the target velocity spectrum vector at the initial moment based on the initial value energy spectrum of the compressible decaying turbulence. It should be noted that the compressible turbulence in this embodiment is all isotropic uniform turbulence. Isotropic uniform forced turbulence is a statistically steady-state turbulence. By applying random forces to the flow field, a statistically steady-state random turbulence field is generated. It is used to study the evolution mechanism of particle turbulence and establish sub-grid models. Isotropic uniform decay turbulence is a type of unsteady statistically steady turbulence. By applying random forces to the initial flow field, a random turbulence field with initial statistical stability is generated. Due to the dissipative effect of fluid viscosity, its turbulent physical quantities decay over time. It is used to study the evolution mechanism of particle turbulence and establish sub-grid models.

[0050] This embodiment does not limit the specific method for obtaining the physical space velocity vector at each moment based on the initial parameters of the compressible forced turbulence. As long as the physical space velocity vector at each moment can be obtained, it will suffice. For example, the initial parameters of the compressible forced turbulence can be input into a parallel computation solver for granular two-phase flow to obtain the physical space velocity vector at each moment. Furthermore, to improve computational efficiency, this embodiment can perform a step-by-step forward Fourier spectral transform on the physical space velocity vector at each moment to obtain the velocity spectrum vector at each moment.

[0051] This embodiment does not limit the specific method of obtaining the target velocity spectrum vector at the initial moment based on the initial value energy spectrum of the compressible decaying turbulence. It is sufficient as long as the target velocity spectrum vector at the initial moment can be obtained. For example, the middle component of the velocity spectrum vector can be obtained based on the initial value energy spectrum of the compressible decaying turbulence; and the target velocity spectrum vector at the initial moment can be obtained based on the middle component of the velocity spectrum vector.

[0052] S102: Performing an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain a target physical space velocity vector of the compressible turbulence.

[0053] Furthermore, in order to improve computational efficiency, this embodiment may perform a step-by-step inverse Fourier spectrum transform on the target velocity spectrum vector to obtain the target physical space velocity vector of the compressible turbulent flow.

[0054] S103: Obtaining original data of compressible turbulence according to the target physical space velocity vector; the original data includes: density variables, temperature variables, and velocity vectors that vary with time.

[0055] This embodiment does not limit the specific method of obtaining the original data of compressible turbulence based on the target physical space velocity vector, as long as it is ensured that the original data of compressible turbulence can be obtained. For example, the target physical space velocity vector can be input into the particle turbulence solver to obtain the original data of compressible turbulence.

[0056] It should be noted that the compressible turbulence in this embodiment is compressible and the energy equation needs to be considered. Therefore, according to the initial parameters of the compressible turbulence, the target velocity spectrum vector of the compressible turbulence is obtained based on the energy equation, and thus the density variables and temperature variables that change with time are obtained.

[0057] S104: Obtain statistics of the compressible turbulence according to the original data of the compressible turbulence.

[0058] This embodiment does not limit the specific method for obtaining the statistics of compressible turbulence based on the original data of compressible turbulence. It is sufficient as long as the statistics of compressible turbulence can be obtained. For example, the original data of compressible turbulence can be input into the particle two-phase flow parallel calculation solver to obtain the original variables of compressible turbulence; and the statistics of compressible turbulence can be obtained based on the original variables of compressible turbulence and the calculation equation of turbulence statistics. It should be noted that this embodiment is highly compatible and can be coupled with any particle two-phase flow parallel calculation solver to calculate the statistics of compressible turbulence, thereby achieving efficient and rapid output of the particle turbulence mechanism characteristics given by the standard test model.

[0059] This embodiment does not limit the specific type of the statistics of the compressible turbulence. For example, the statistics of the compressible turbulence may include the turbulence statistics of the fluid phase or the turbulence statistics of the dispersed particle phase.

[0060] This embodiment does not limit the specific type of the calculation equation of the turbulence statistics. The specific type of the calculation equation of the turbulence statistics can be determined according to the specific type of the statistics of the compressible turbulence. For example, when the statistics of the compressible turbulence are the turbulence statistics of the fluid phase, the sampling space of the calculation equation of the turbulence statistics is based on Euler coordinate points; when the statistics of the compressible turbulence are the turbulence statistics of the diffuse particle phase, the sampling space of the calculation equation of the turbulence statistics is based on Lagrangian coordinate points.

[0061] S105: Determine the friction and heat flow on the surface of the aircraft based on the statistics of the compressible turbulence.

[0062] Based on the above embodiments, the present application can obtain the statistics of compressible isotropic uniform turbulence of particles. On the one hand, by studying the interaction between compressible isotropic uniform turbulence and ablative particles, the friction and heat flow on the aircraft surface can be predicted; on the other hand, it can be used to establish a relevant direct numerical simulation database to provide support for the establishment of corresponding particle two-phase flow sub-grid simulation.

[0063] The following is a specific example to illustrate the calculation process of the above-mentioned standard model of compressible turbulence of ablative particles. Please refer to Figure 2 and Figure 4 , Figure 2 This is a flow chart of a calculation method for a standard model of compressible decay turbulence of ablative particles provided in an embodiment of the present application. Figure 4 This is a schematic diagram of the parallel and reduced step-by-step Fourier transform in the X and Y directions provided in an embodiment of the present application. In this embodiment, the compressible turbulence is a compressible isotropic uniformly decaying turbulence. The specific process is as follows:

[0064] 1. Under the conditions of given initial turbulent kinetic energy k0, initial turbulent dissipation rate ε0 and fluid kinematic viscosity ν, the initial energy spectrum E of compressible isotropic uniform decay turbulence is given by constructing a large-scale energy spectrum. k (κ).

[0065] The initial turbulence constant is C0=1.5, C L =6.78, C η = 0.4, β = 5.2, p0 = 2, π = 3.14. The turbulence correlation scale is L, the turbulence viscosity scale is η, the wave number vector components are κ1, κ2, κ3, and the wave number in the spectral sphere space is:

[0066]

[0067] parameter function f L and f η The expression is:

[0068]

[0069] Turbulent kinetic energy spectrum E k The expression of (κ):

[0070]

[0071] 2. Define θ1, θ2, θ3 as the three components of the phase angle vector. Define v hat_1 ,v hat_2 ,v hat_3 are the three intermediate components of the velocity vector in the spectral space (i.e., velocity spectrum vector), and define κ v is the middle wave number in the spectral space.

[0072] Define u hat_1 ,u hat_2 ,u hat_3 are the three components of the velocity vector in the spectral space, which are obtained through the intermediate transformation equations (4) and (5).

[0073]

[0074]

[0075] 3. Velocity vector u in spectral space at the initial moment hat_1 ,u hat_2 ,u hat_3 After the determination, the velocity vectors u1, u2, u3 based on the Cartesian coordinate system (i.e., the physical space velocity vectors) can be obtained by Fourier spectrum transformation (here, inverse Fourier spectrum transformation). The obtained u1, u2, u3 are the initial velocity values ​​of the compressible isotropic uniform decay turbulence. The parallel Fourier transform method can be found in Figure 4 .

[0076] 4. When the raw data generated by the particle turbulence solver are density, temperature, and velocity vectors, the Fourier spectral transform described above modifies the initial velocity field by changing the velocity spectrum in the spectral space. The generated raw data is coupled to the particle two-phase flow parallel computation solver, which outputs statistics for compressible isotropic uniformly decaying turbulence, resulting in a series of compressible isotropic uniformly decaying turbulence statistics.

[0077] The turbulence statistics of the entrained fluid phase are as follows:

[0078] The expressions of turbulent kinetic energy k and turbulent dissipation rate ε are:

[0079]

[0080] Among them, u represents the turbulent velocity, ν represents the fluid kinematic viscosity, and u i represents the fluid velocity vector (Einstein index representation), x j represents the position vector (Einstein metric representation).

[0081] Turbulent viscosity scale η, turbulent viscosity velocity u η , turbulent viscosity time τ η The expression of the turbulence-related scale L is:

[0082]

[0083] Where ν represents the fluid kinematic viscosity, ε represents the turbulent dissipation rate, and k represents the turbulent kinetic energy.

[0084] Turbulent Reynolds number Re L , Taylor microscale λ g , Taylor Reynolds number R λ and the pulsation Mach number M t The expression:

[0085]

[0086] Where k represents the turbulent kinetic energy, L represents the turbulence-related scale, ν represents the fluid kinematic viscosity, η represents the turbulent viscosity scale, and u' represents the pulsating velocity.

[0087] The expressions of the streamwise autocorrelation function f(r) and the spanwise autocorrelation function g(r) are:

[0088]

[0089] Among them, u L represents the flow velocity along the sampling direction, u Nrepresents the normal velocity along the sampling direction, u represents the turbulent velocity, x represents the reference position, and r represents the distance between the two positions. Under the condition of isotropic uniform turbulence, the three velocities are the same, that is, u L =u N =u.

[0090] The expressions of turbulent energy spectrum E(κ) and turbulent dissipation spectrum ε(κ) are:

[0091]

[0092] Among them, ν represents the fluid kinematic viscosity, k represents the turbulent kinetic energy, and u hat (κ) represents the velocity spectrum.

[0093] The statistics of the dispersed particle phase are constructed in exactly the same way as those of the carrying fluid phase. The only difference is that the sampling space of the carrying fluid phase is based on Eulerian coordinate points, while the sampling space of the dispersed particle phase is based on Lagrangian coordinate points.

[0094] The following is a specific example to illustrate the calculation process of the above-mentioned standard model of compressible turbulence of ablative particles. Please refer to Figure 3 and Figure 4 , Figure 3 This is a flow chart of a calculation method for a standard model of compressible forced turbulence of eroded particles provided in an embodiment of the present application. Figure 4 This is a schematic diagram of the parallel and reduced step-by-step Fourier transform in the X and Y directions provided in an embodiment of the present application. In this embodiment, the compressible turbulence is a compressible isotropic uniform forced turbulence. The process is specifically as follows:

[0095] 1. At each moment, the initial parameters of the compressible forced turbulence are input into the particle two-phase flow parallel calculation solver to obtain the velocity vector of the Cartesian coordinate system (i.e., the physical space velocity vector); the velocity vectors u1, u2, u3 of the Cartesian coordinate system are transformed into the spectral space by Fourier spectral forward transformation to obtain the velocity vector of the spectral space (i.e., the velocity spectrum vector) u hat_1 ,u hat_2 ,u hat_3 ; Its parallel Fourier transform method can be found in Figure 4 ;

[0096] 2. Apply turbulent kinetic energy to the velocity vector u in spectral space hat_1 ,u hat_2 ,u hat_3 On, that is, applying a statistical steady-state random energy spectrum;

[0097] 3. The velocity vector u in the spectral space at each moment hat_1 ,u hat_2 ,u hat_3After the determination, the velocity vectors u1, u2, u3 based on the Cartesian coordinate system can be obtained by inverse Fourier spectrum transformation; the parallel Fourier transform method can be found in Figure 4 ;

[0098] 4. When the particle turbulence solver reaches statistical steady state, the raw data it generates are: density, temperature, and velocity vector. The aforementioned inverse Fourier spectral transform modifies the initial velocity field by changing the velocity spectrum in the spectral space. The generated raw data is coupled to the particle two-phase flow parallel calculation solver, which outputs statistics of compressible isotropic uniform forced turbulence, resulting in a series of compressible isotropic uniform forced turbulence statistical information. The turbulence statistics of the fluid phase and the statistics of the dispersed particle phase can be referred to in the above embodiments.

[0099] The following is an introduction to a calculation device, equipment and computer-readable storage medium for a compressible turbulence standard model of an ablative particle provided in an embodiment of the present application. The calculation device, equipment and computer-readable storage medium for a compressible turbulence standard model of an ablative particle described below can be referenced to the calculation method for a compressible turbulence standard model of an ablative particle described above.

[0100] Please refer to Figure 5 , Figure 5 This is a block diagram of a device for calculating a standard model of compressible turbulence of ablative particles provided in an embodiment of the present application. The device may include:

[0101] The target velocity spectrum vector module 100 is used to obtain the target velocity spectrum vector of the compressible turbulent flow based on the initial parameters of the compressible turbulent flow and the energy equation;

[0102] A target physical space velocity vector module 200 is used to perform an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain a target physical space velocity vector of compressible turbulence;

[0103] The raw data module 300 is used to obtain raw data of compressible turbulence according to the target physical space velocity vector; the raw data includes: density variables, temperature variables and velocity vectors that change with time;

[0104] The statistics module 400 is used to obtain statistics of the compressible turbulent flow based on the original data of the compressible turbulent flow;

[0105] The friction and heat flow module 500 is used to determine the friction and heat flow on the surface of the aircraft based on the statistics of compressible turbulence.

[0106] Based on the above embodiments, the present application can obtain the statistics of compressible isotropic uniform turbulence of particles. On the one hand, by studying the interaction between compressible isotropic uniform turbulence and ablative particles, the friction and heat flow on the aircraft surface can be predicted; on the other hand, it can be used to establish a relevant direct numerical simulation database to provide support for the establishment of corresponding particle two-phase flow sub-grid simulation.

[0107] Based on the above embodiment, the target physical space velocity vector module 200 is specifically configured to perform a step-by-step Fourier spectrum inverse transform on the target velocity spectrum vector to obtain the target physical space velocity vector of the compressible turbulent flow.

[0108] Based on the above embodiments, the statistics module 400 is specifically used to input the original data of the compressible turbulent flow into the granular two-phase flow parallel calculation solver to obtain the statistics of the compressible turbulent flow.

[0109] Based on the above embodiments, the target velocity spectrum vector module 100 may include:

[0110] A physical space velocity vector unit is used to obtain the physical space velocity vector at each moment according to the initial parameters of the compressible forced turbulence;

[0111] The velocity spectrum vector unit is used to perform Fourier spectrum forward transform on the physical space velocity vector at each moment to obtain the velocity spectrum vector at each moment;

[0112] The target velocity spectrum vector unit is used to apply turbulent kinetic energy to the velocity spectrum vector at each moment to obtain the target velocity spectrum vector at each moment.

[0113] Based on the above embodiments, the physical space velocity vector unit is specifically used to input the initial parameters of the compressible forced turbulence into the granular two-phase flow parallel calculation solver to obtain the physical space velocity vector at each moment.

[0114] Based on the above embodiments, the target velocity spectrum vector module 100 may include:

[0115] An initial value energy spectrum unit is used to obtain an initial value energy spectrum of the compressible decaying turbulence according to the initial parameters of the compressible decaying turbulence;

[0116] The target velocity spectrum vector unit is used to obtain the target velocity spectrum vector at the initial moment according to the initial value energy spectrum of the compressible decay turbulence.

[0117] Based on the above embodiments, the target velocity spectrum vector unit is specifically used to obtain the intermediate component of the velocity spectrum vector according to the initial value energy spectrum of the compressible decay turbulence; and obtain the target velocity spectrum vector at the initial moment according to the intermediate component of the velocity spectrum vector.

[0118] Based on the above embodiments, the present application further provides a device for calculating a standard model of compressible turbulence with an ablative particle, comprising: a memory and a processor, wherein the memory is configured to store a computer program; and the processor is configured to implement the steps of the method for calculating a standard model of compressible turbulence with an ablative particle when executing the computer program. Of course, the device may also include various necessary network interfaces, a power supply, and other components.

[0119] The present application also provides a computer-readable storage medium having a computer program stored thereon. When executed by a processor, the computer program implements the steps of the calculation method for the standard model of compressible turbulence of ablative particles described in each of the above embodiments. The storage medium may include a USB flash drive, a mobile hard drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk, among other media capable of storing program code.

[0120] Specific examples are used herein to illustrate the principles and implementation methods of the present application, and the various embodiments are in a progressive relationship. Each embodiment focuses on the differences from other embodiments, and the same or similar parts between the various embodiments can be referred to each other. For the devices disclosed in the embodiments, please refer to the corresponding method section description. The description of the above embodiments is only used to help understand the method of the present application and its core idea. For ordinary technicians in this technical field, without departing from the principles of the present application, several improvements and modifications can be made to the present application, and these improvements and modifications also fall within the scope of protection of the claims of the present application.

[0121] It should also be noted that, in this specification, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of additional identical elements in the process, method, article, or device comprising the element.

Claims

1. A calculation method for a standard model of compressible turbulence of ablative particles, characterized in that: include: According to initial parameters of the compressible turbulent flow, a target velocity spectrum vector of the compressible turbulent flow is obtained based on an energy equation; Performing an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain a target physical space velocity vector of the compressible turbulent flow; According to the target physical space velocity vector, raw data of the compressible turbulent flow is obtained; the raw data includes: a density variable, a temperature variable and a velocity vector that change with time; Obtaining statistics of the compressible turbulent flow according to the original data of the compressible turbulent flow; The friction and heat flow on the surface of the aircraft are determined based on the statistics of the compressible turbulent flow.

2. The calculation method of the compressible turbulence standard model of ablation particles according to claim 1, characterized in that: The performing an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain the target physical space velocity vector of the compressible turbulent flow includes: Performing a step-by-step inverse Fourier spectrum transform on the target velocity spectrum vector to obtain the target physical space velocity vector of the compressible turbulent flow.

3. The calculation method of the compressible turbulence standard model of ablation particles according to claim 1, characterized in that: The obtaining of statistics of the compressible turbulent flow according to the original data of the compressible turbulent flow comprises: The original data of the compressible turbulent flow is input into a particle two-phase flow parallel calculation solver to obtain the statistics of the compressible turbulent flow.

4. The calculation method of the compressible turbulence standard model of ablation particles according to any one of claims 1 to 3, characterized in that: The method of obtaining the target velocity spectrum vector of the compressible turbulent flow based on the energy equation according to the initial parameters of the compressible turbulent flow comprises: According to the initial parameters of compressible forced turbulence, the physical space velocity vector at each moment is obtained; Performing a Fourier spectrum forward transform on the physical space velocity vector at each moment to obtain a velocity spectrum vector at each moment; The turbulent kinetic energy is applied to the velocity spectrum vector at each moment to obtain the target velocity spectrum vector at each moment.

5. The calculation method of the compressible turbulence standard model of ablation particles according to claim 4, characterized in that: The physical space velocity vector at each moment is obtained based on the initial parameters of the compressible forced turbulence, including: The initial parameters of the compressible forced turbulence are input into the parallel calculation solver of the granular two-phase flow to obtain the physical space velocity vector at each moment.

6. The calculation method of the compressible turbulence standard model of ablative particles according to any one of claims 1 to 3, characterized in that: The method of obtaining the target velocity spectrum vector of the compressible turbulent flow based on the energy equation according to the initial parameters of the compressible turbulent flow comprises: Obtaining an initial value energy spectrum of the compressible decaying turbulence according to initial parameters of the compressible decaying turbulence; According to the initial value energy spectrum of the compressible decaying turbulence, a target velocity spectrum vector at the initial moment is obtained.

7. The calculation method of the compressible turbulence standard model of ablative particles according to claim 6, characterized in that: The step of obtaining a target velocity spectrum vector at an initial moment based on the initial value energy spectrum of the compressible decaying turbulence comprises: Obtaining an intermediate component of a velocity spectrum vector according to an initial value energy spectrum of the compressible decaying turbulence; A target velocity spectrum vector at an initial moment is obtained according to the intermediate component of the velocity spectrum vector.

8. A device for calculating a standard model of compressible turbulence of ablative particles, characterized in that: include: a target velocity spectrum vector module, configured to obtain a target velocity spectrum vector of the compressible turbulent flow based on an energy equation according to initial parameters of the compressible turbulent flow; a target physical space velocity vector module, configured to perform an inverse Fourier spectrum transform on the target velocity spectrum vector to obtain a target physical space velocity vector of the compressible turbulent flow; A raw data module, configured to obtain raw data of the compressible turbulent flow according to the target physical space velocity vector; the raw data including: a density variable, a temperature variable, and a velocity vector that vary with time; A statistics module, configured to obtain statistics of the compressible turbulent flow based on the original data of the compressible turbulent flow; The friction and heat flow module is used to determine the friction and heat flow on the surface of the aircraft based on the statistics of the compressible turbulence.

9. A device for calculating a standard model of compressible turbulence of ablative particles, characterized in that: include: Memory for storing computer programs; A processor is configured to implement the steps of the calculation method of the compressible turbulence standard model of ablation particles according to any one of claims 1 to 7 when executing the computer program.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps of the calculation method of the ablation particle compressible turbulence standard model according to any one of claims 1 to 7.

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