CN110826208B - Pneumatic numerical simulation accelerated convergence method - Google Patents
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Abstract
The invention provides a pneumatic numerical simulation accelerated convergence method, which comprises the following steps: 1. generating a grid file for numerical calculation; 2. carrying out numerical calculation of a first working condition based on the grid file until aerodynamic force and aerodynamic moment coefficients under the working condition are sufficiently converged, and initializing a flow field before carrying out numerical calculation; 3. and performing numerical calculation of a second working condition based on the flow field data obtained under the first working condition until aerodynamic and aerodynamic moment coefficients under the working condition are sufficiently converged, wherein the flow field does not need to be reinitialized before the numerical calculation of the second working condition is performed, and the parameters under the first working condition and the second working condition meet the following requirements: the attack angle and the sideslip angle of the current working condition and the previous working condition meet the angle of | alpha n ‑α n‑1 |+|β n ‑β n‑1 Less than or equal to 4 degrees, and the calculation of Ma satisfies the condition of Ma n ‑Ma n‑1 The | < 0.5; and 4, sequentially carrying out numerical calculation on the rest working conditions according to the numerical calculation method under the second working condition in the step 3. The method can quickly and accurately acquire a large number of working condition pneumatic data of the aircraft, can obviously reduce the calculated amount and saves the calculated resources.
Description
Technical Field
The invention relates to the technical field of aircraft computational aerodynamics, in particular to a pneumatic numerical simulation acceleration convergence method.
Background
Computational Fluid Dynamics (CFD) is rapidly developed along with continuous development of physical models, numerical algorithms and computer software and hardware levels in the last hundred years since birth, and gradually becomes an important means for aerodynamic layout design and wind tunnel test check in aircraft development.
At present, a refined structural grid is generally adopted for high-precision numerical simulation, the calculation grid quantity is large when the geometric shape state of the aircraft is simulated in detail, tens of millions of grids and even hundreds of millions of grids are frequently used, the demand on calculation resources is high, in addition, in the case of high price of a wind tunnel test, in the aircraft scheme demonstration and design stage, the whole set of aerodynamic performance data of the aircraft, including the aerodynamic data in different attack angles, sideslip angles, rudder deflection angles and Reynolds number states, is obtained by means of numerical simulation, the calculation state is large, the numerical calculation quantity is increased rapidly, and the scheme demonstration and the design progress are even affected in severe cases.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, provides a pneumatic numerical simulation accelerated convergence method, and can solve the technical problems in the prior pneumatic numerical simulation method.
The technical solution of the invention is as follows: the method for accelerating convergence of the aerodynamic numerical simulation is provided, and comprises the following steps:
and 3, performing numerical calculation of a second working condition based on the flow field data obtained under the first working condition until aerodynamic force and aerodynamic moment coefficients under the working condition are sufficiently converged, wherein the flow field does not need to be reinitialized before the numerical calculation of the second working condition is performed, and parameters under the first working condition and the second working condition need to meet: the attack angle and the sideslip angle of the current working condition and the previous working condition should satisfy | alpha n -α n-1 |+|β n -β n-1 | < 4 °, ma should be satisfied by calculating n -Ma n-1 Less than or equal to 0.5; n represents the current working condition, n-1 represents the last working condition, alpha represents an attack angle, and beta represents a sideslip angle;
and 4, sequentially performing numerical calculation of the rest working conditions according to the numerical calculation method under the second working condition in the step 3, wherein the numerical calculation of the current working condition is performed based on the flow field data under the previous working condition.
Further, the step 3 further comprises: the boundary conditions need to be reset before numerical calculations for the second operating regime can be made.
Further, the boundary conditions that need to be reset include: angle of attack of incoming flow, angle of sideslip Ma, or atmospheric parameters.
Further, the flow field data includes: speed, temperature, density and pressure.
Further, in the method, whether aerodynamic and aerodynamic moment coefficients are sufficiently converged is determined based on the magnitude of each of the parties Cheng Cancha involved in the numerical calculation.
Further, in the method, res is satisfied when each party Cheng Cancha involved in the numerical calculation satisfies res (Continuous) ≤1×10 -5 And res Momentum ≤1×10 -5 And res (Energy) ≤1×10 -6 Then the corresponding power and aerodynamic moment coefficients are fully converged.
Further, the method further comprises: when the data criterion of all parties Cheng Cancha involved in the numerical calculation fails, whether the aerodynamic moment coefficient is sufficiently converged is judged in the following way:
the standard deviation of the aerodynamic moment coefficient meets SD by 100 steps per iteration aero When the aerodynamic moment coefficient is less than or equal to 0.001, the aerodynamic moment coefficient is fully converged.
By applying the technical scheme, the method for accelerating convergence of pneumatic numerical simulation is provided, except for the first working condition, when numerical calculation under other working conditions is carried out, the method is different from the prior art, a flow field does not need to be initialized again, only the converged flow field data of the above working condition is taken as a reference, and meanwhile, the attack angle and the sideslip angle in the adjacent working conditions are enabled to be simultaneously; and the Mach number is calculated, and the numerical calculation of the current working condition can be accurately finished when the Mach number respectively meets the set conditions. The method can quickly and accurately acquire a large amount of working condition aerodynamic data of the aircraft, can obviously reduce the calculated amount, saves the calculated resources, and improves the overall calculation efficiency by 30 to 70 percent compared with the prior art.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 shows a schematic flow diagram of a prior art pneumatic numerical simulation method;
FIG. 2 is a flow chart of a pneumatic numerical simulation accelerated convergence method according to an embodiment of the present invention;
FIG. 3 shows a convergence history of aerodynamic coefficients for different operating conditions provided by an embodiment of the invention.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be obtained by a person skilled in the art without inventive step based on the embodiments of the present invention, are within the scope of protection of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be discussed further in subsequent figures.
As related to the background art, as shown in fig. 1, fig. 1 shows a schematic flow diagram of an existing pneumatic numerical simulation method, in the existing pneumatic numerical simulation calculation, a cyclic process as shown in fig. 1 needs to be developed for a plurality of working conditions, that is, each time one working condition calculation is performed, a flow field needs to be initialized in sequence, the numerical simulation calculation for the plurality of working conditions is performed in sequence, and the calculation state is large, so that the numerical calculation amount is increased rapidly. The scheme of the embodiment of the invention is proposed to solve the problem.
As shown in fig. 2, an embodiment of the present invention provides a method for accelerating convergence in aerodynamic numerical simulation, the method including the following steps:
and 3, performing numerical calculation of a second working condition based on the flow field data obtained under the first working condition until the aerodynamic force and aerodynamic moment coefficients under the working condition are sufficiently converged, wherein the flow field does not need to be reinitialized before the numerical calculation of the second working condition is performed, and the parameters under the first working condition and the second working condition need to meet the following requirements: the attack angle and the sideslip angle of the current working condition and the previous working condition meet the angle of | alpha n -α n-1 |+|β n -β n-1 | < 4 °, ma should be satisfied by calculating n -Ma n-1 |≤0.5；n represents the current working condition, n-1 represents the last working condition, alpha represents an attack angle, and beta represents a sideslip angle;
and 4, sequentially performing numerical calculation of the rest working conditions according to the numerical calculation method under the second working condition in the step 3, wherein the numerical calculation of the current working condition is performed based on the flow field data under the previous working condition.
Therefore, except for the first working condition, when numerical calculation is carried out under other working conditions, the method is different from the prior art, a flow field does not need to be initialized again, only the converged flow field data of the above working condition is taken as a reference, and meanwhile, the attack angle and the sideslip angle in the adjacent working conditions are enabled; and the Mach number is calculated and simultaneously meets the set conditions, so that the numerical calculation of the current working condition can be accurately finished. The method can rapidly and accurately acquire a large amount of working condition pneumatic data of the aircraft, can obviously reduce the calculated amount, saves the calculated resources, and improves the overall calculation efficiency by 30-70% compared with the prior art.
In the embodiment of the invention, the current working condition refers to the second working condition, and the last working condition refers to the first working condition.
In the embodiment of the invention, the grid generation in the step 1 can be obtained by adopting the conventional means in the field.
Preferably, the plurality of working conditions involved in the method are all calculated by using the same grid.
In the embodiment of the present invention, when performing the numerical simulation calculation under the first working condition, the numerical simulation calculation can be implemented by using a conventional method, for example, including related calculation settings (boundary condition setting, calculation format setting, and the like), flow field initialization, and the like, which is not described in detail herein.
In the embodiment of the invention, the key point is that the numerical simulation calculation under the other working conditions except the first working condition is different from the prior art, for example, when the second working condition is calculated, if the operation such as flow field initialization is required to be carried out according to the prior method like the calculation flow of the first working condition, but when the numerical simulation calculation under the second working condition is carried out, the flow field initialization is not required, and the calculation is carried out only based on the converged calculation result (flow field data after the calculation of the first working condition) of the last working condition, so that the numerical simulation calculation under the first working condition is greatly reducedCalculated quantity, but at the same time, in order to ensure the precision, parameters related to adjacent working conditions need to satisfy | alpha n -α n-1 |+|β n -β n-1 Less than or equal to 4 degrees, and the calculation of Ma satisfies the condition of Ma n -Ma n-1 Less than or equal to 0.5; under this condition, for example, the numerical calculation result under the second operating condition can be accurately obtained.
Further, in the present invention, the step 3 further includes: the boundary conditions need to be reset before numerical calculations for the second operating regime can be made.
Optionally, the boundary conditions that need to be reset include: an incoming flow attack angle, a sideslip angle Ma or atmospheric parameters, etc. Wherein, those skilled in the art should understand that the specific boundary conditions are not limited thereto and are known in the art.
Further, in the present invention, the flow field data includes: speed, temperature, density, pressure, etc., without limitation.
Further, in the method, in order to judge whether the calculation result under each working condition is sufficiently converged, whether the aerodynamic force and the aerodynamic moment coefficient are sufficiently converged is judged based on the magnitude of each party Cheng Cancha involved in numerical calculation.
Preferably, res is satisfied when each party Cheng Cancha involved in the numerical calculation satisfies res (Continuous) ≤1×10 -5 And res Momentum ≤1×10 -5 And res (Energy) ≤1×10 -6 Then the corresponding power and aerodynamic moment coefficients are sufficiently convergent.
Those skilled in the art will appreciate that the acquisition of each party Cheng Cancha involved in the numerical calculation is well known in the art and will not be described in detail herein.
Optionally, the method further includes: when the data criterion of all parties Cheng Cancha involved in the numerical calculation fails, whether the aerodynamic moment coefficient is sufficiently converged is judged in the following way:
standard deviation SD of aerodynamic moment coefficient per 100 steps of iteration aero When the aerodynamic moment coefficient is less than or equal to 0.001, the aerodynamic moment coefficient is fully converged.
In the embodiment of the present invention, the aerodynamic moment coefficients include, for example, cx, cy, cz, mx, my, and mz.
According to the method disclosed by the embodiment of the invention, numerical simulation calculation of 5 working conditions is completed, the convergence history curves of the aerodynamic coefficients of different working conditions are shown in figure 3, and the figure shows that the calculated amount of other working conditions except the first working condition is obviously reduced, and the overall calculation efficiency is improved by about 30-70%.
For ease of description, spatially relative terms such as "over … …", "over … …", "over … …", "over", etc. may be used herein to describe the spatial positional relationship of one device or feature to another device or feature as shown in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A pneumatic numerical simulation accelerated convergence method is characterized by comprising the following steps:
step 1, generating a grid file for numerical calculation;
step 2, performing numerical calculation of a first working condition based on the grid file until aerodynamic force and aerodynamic moment coefficients under the working condition are sufficiently converged, wherein a flow field needs to be initialized before the numerical calculation;
and 3, performing numerical calculation of a second working condition based on the flow field data obtained under the first working condition until aerodynamic force and aerodynamic moment coefficients under the working condition are sufficiently converged, wherein the flow field does not need to be reinitialized before the numerical calculation of the second working condition is performed, and parameters under the first working condition and the second working condition need to meet: the attack angle and the sideslip angle of the current working condition and the previous working condition should satisfy | alpha n -α n-1 |+|β n -β n-1 The angle is less than or equal to 4 degrees, and the calculation of Ma meets the angle of Ma n -Ma n-1 The | < 0.5; n represents the current working condition, n-1 represents the last working condition, alpha represents an attack angle, and beta represents a sideslip angle;
and 4, sequentially performing numerical calculation of the rest working conditions according to the numerical calculation method under the second working condition in the step 3, wherein the numerical calculation of the current working condition is performed based on the flow field data under the previous working condition.
2. The pneumatic numerical simulation accelerated convergence method according to claim 1, wherein the step 3 further comprises: the boundary conditions need to be reset before numerical calculation for the second operating condition can be performed.
3. The aerodynamic numerical simulation accelerated convergence method according to claim 2, wherein the boundary conditions to be reset include: angle of attack of incoming flow, angle of sideslip Ma, or atmospheric parameters.
4. The aerodynamic numerical simulation accelerated convergence method according to claim 1, wherein the flow field data comprises: speed, temperature, density and pressure.
5. The method for accelerating convergence through pneumatic numerical simulation according to claims 1-4, wherein the method determines whether the aerodynamic and aerodynamic moment coefficients are sufficiently converged based on the magnitude of each of Cheng Cancha involved in the numerical calculation.
6. The pneumatic numerical simulation acceleration convergence method according to claim 5, characterized in that in the method, when each party Cheng Cancha involved in numerical calculation satisfies res (Continuous) ≤1×10 -5 And res Momentum ≤1×10 -5 And res (Energy) ≤1×10 -6 Then the corresponding power and aerodynamic moment coefficients are sufficiently convergent.
7. The aerodynamic numerical simulation accelerated convergence method of claim 5, further comprising: when the data criterion of all parties Cheng Cancha involved in the numerical calculation fails, whether the aerodynamic moment coefficient is sufficiently converged is judged in the following way:
the standard deviation of the aerodynamic moment coefficient meets SD by 100 steps per iteration aero When the aerodynamic moment coefficient is less than or equal to 0.001, the aerodynamic moment coefficient is fully converged.
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