CN116522827B - Flow variable reconstruction method, equipment and device for calculation of aerodynamic thermal environment - Google Patents
Flow variable reconstruction method, equipment and device for calculation of aerodynamic thermal environment Download PDFInfo
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Abstract
The invention provides a flow variable reconstruction method, equipment and a device for calculation of a aerodynamic thermal environment, which relate to the technical field of computational fluid mechanics, and the method comprises the following steps: determining the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface, searching and recording the numbers of the adjacent grid cells, if the grid cell boundary surface is marked as a first number representing a first type, adopting a one-dimensional limiter to reconstruct the variables, and if the grid cell boundary surface is marked as a second number representing a second type, adopting a multi-dimensional limiter to reconstruct the variables. The reconstruction method provided by the invention can select the limiter according to the type of the boundary surface of the grid unit, so that the reconstruction method is suitable for numerical simulation of any grid type, and effectively improves the flow characteristic resolving power of complex wave system interference including shock waves, contact discontinuities and the like on the premise of ensuring stable flow calculation, thereby realizing high-precision simulation of the pneumatic heating problem of the aircraft with complex appearance.
Description
Technical Field
The invention relates to the technical field of computational fluid mechanics, in particular to a flow variable reconstruction method, equipment and a device for aerodynamic thermal environment calculation.
Background
For hypersonic complex flow, various discontinuous and high gradient areas including shock waves, contact discontinuities, shear layers, boundary layers and the like exist in the flow field, and strict requirements are put on the accuracy and stability of a calculation method. The limiter adds 'limited' negative dissipation to a low-order format with higher dissipation so as to reduce the dissipation level to the greatest extent under the premise of ensuring stability of the numerical format, and improve format precision.
For a structural network, various classical one-dimensional TVD limiters including van Leer, minmod, superbee, van Albada and the like are provided in the related technology, and stable and accurate simulation of multidimensional flow is realized by respectively applying the one-dimensional limiter technology to each dimension.
However, with the increasing complexity of the computing profile, the difficulty of generating high quality structural grids suitable for hypersonic pneumatic heating is increasing, with the advent of unstructured grid technologies that are not constrained by grid type and grid topology.
For unstructured grids, a one-dimensional TVD limiter technology cannot be applied because no obvious dimension decomposition direction exists due to the disorder of the grids, so that multidimensional limiters such as Barth and Venkatakrishan appear, but the multidimensional limiters have insufficient flow characteristic resolution capability for complex wave system interference including shock waves, contact discontinuities and the like, and how to improve flow field resolution and flow simulation precision becomes one of key technologies for unstructured grid calculation.
Disclosure of Invention
In view of the foregoing drawbacks and disadvantages of the prior art, the present invention is directed to a method, apparatus, and device for flow variable reconstruction for calculation of a aerodynamic thermal environment.
In a first aspect, the present invention provides a method for reconstructing a flow variable of a aerodynamic thermal environment calculation, the method comprising:
a step of searching adjacent grid cells of the grid cell boundary surface: determining the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface for any grid cell boundary surface, and searching and recording the numbers of the adjacent grid cells; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or if the adjacent grid cells are triangular grid cells and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, and searching and recording the cell numbers of the local structured cells according to the first number; if the grid cell boundary surface is the other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, and searching for a cell number for recording a local unstructured cell according to the second number;
A grid cell boundary surface flow variable reconstruction step: performing variable reconstruction according to the type of the intelligent transformation limiter of the type of the boundary surface of the grid unit; if the grid cell boundary surface is marked as the first number, adopting a one-dimensional limiter to reconstruct variables; and if the grid cell boundary surface is marked as the second number, adopting a multidimensional limiter to reconstruct the variables.
In one possible implementation manner, the searching for the unit number of the recording local structural unit according to the first number includes:
numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
marking the serial number of the grid cell boundary surface on the adjacent grid cells of the 1 st layer as the first serial number;
sequentially judging node numbers contained in other boundary surfaces of the 1 st layer adjacent grid cells, searching other grid cell boundary surfaces of the 1 st layer adjacent grid cells, which have no shared node with the first number, and marking the searched grid cell boundary surfaces as the second number;
the adjacent grid cells marked as the boundary surface of the second numbered grid cell are regarded as layer 2 adjacent grid cells.
In a possible implementation manner, the searching for the unit number of the local unstructured unit according to the second number includes:
numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
the third number is taken as a layer 2 adjacent grid cell.
In one possible implementation, the one-dimensional limiter includes some or all of the following:
a minmod limiter;
a van Leer limiter;
a van Albada limiter;
superbee limiter.
In one possible implementation, the multi-dimensional limiter includes some or all of the following:
a path limiter;
venkatakrishan limiter;
the path correction limiter.
In one possible implementation, before the step of reconstructing the grid cell boundary surface flow variable, the method further includes:
reading in calculation parameters and calculation control parameters;
reading and processing the computing grid and boundary condition information thereof;
initializing and calculating flow fields for all grid cells;
assigning a boundary condition;
after the grid cell boundary surface flow variable reconstruction step, the method further comprises the following steps:
performing a convection flux term calculation;
judging a viscosity flux item, and if the viscosity exists, calculating a viscosity coefficient and calculating a viscosity flux; if the viscosity does not exist, judging a source item, if the source item exists, calculating the source item, and if the source item does not exist, calculating residual statistics and pneumatic parameters;
Calculating a time step;
performing time item pushing;
and (3) carrying out convergence judgment, returning to the step of assigning the boundary conditions if the calculation is not converged, and ending the calculation if the calculation is converged.
In one possible implementation, the traffic item calculation format includes some or all of the following:
Roe；
van Leer；
AUSM series method;
a mixed windward method;
the rotating Riemann method.
In one possible implementation manner, the performing viscosity coefficient calculation includes:
carrying out laminar flow viscosity coefficient calculation and turbulent flow viscosity coefficient calculation;
the viscous flux calculation includes:
the tack flux calculations were performed using the full tack format and thin layer approximation method.
In a second aspect, the present invention also provides a flow variable reconstruction device for aerodynamic thermal environment calculation, comprising one or more processors;
a memory for storing one or more programs that, when executed by the one or more processors, cause the one or more processors to implement the steps of:
a step of searching adjacent grid cells of the grid cell boundary surface: determining the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface for any grid cell boundary surface, and searching and recording the numbers of the adjacent grid cells; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or if the adjacent grid cells are triangular grid cells and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, and searching and recording the cell numbers of the local structured cells according to the first number; if the grid cell boundary surface is the other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, and searching for a cell number for recording a local unstructured cell according to the second number;
A grid cell boundary surface flow variable reconstruction step: performing variable reconstruction according to the type of the intelligent transformation limiter of the type of the boundary surface of the grid unit; if the grid cell boundary surface is marked as the first number, adopting a one-dimensional limiter to reconstruct variables; and if the grid cell boundary surface is marked as the second number, adopting a multidimensional limiter to reconstruct the variables.
In one possible implementation, the processor is specifically configured to:
numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
marking the serial number of the grid cell boundary surface on the adjacent grid cells of the 1 st layer as the first serial number;
sequentially judging node numbers contained in other boundary surfaces of the 1 st layer adjacent grid cells, searching other grid cell boundary surfaces of the 1 st layer adjacent grid cells, which have no shared node with the first number, and marking the searched grid cell boundary surfaces as the second number;
the adjacent grid cells marked as the boundary surface of the second numbered grid cell are regarded as layer 2 adjacent grid cells.
In one possible implementation, the processor is specifically configured to:
Numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
the third number is taken as a layer 2 adjacent grid cell.
In one possible implementation, the one-dimensional limiter includes some or all of the following:
a minmod limiter;
a van Leer limiter;
a van Albada limiter;
superbee limiter.
In one possible implementation, the multi-dimensional limiter includes some or all of the following:
a path limiter;
venkatakrishan limiter;
the path correction limiter.
In one possible implementation, before the grid cell boundary surface flow variable reconstruction step, the processor is further configured to:
reading in calculation parameters and calculation control parameters;
reading and processing the computing grid and boundary condition information thereof;
initializing and calculating flow fields for all grid cells;
assigning a boundary condition;
after the grid cell boundary surface flow variable reconstruction step, the processor is further configured to:
performing a convection flux term calculation;
judging a viscosity flux item, and if the viscosity exists, calculating a viscosity coefficient and calculating a viscosity flux; if the viscosity does not exist, judging a source item, if the source item exists, calculating the source item, and if the source item does not exist, calculating residual statistics and pneumatic parameters;
Calculating a time step;
performing time item pushing;
and (3) carrying out convergence judgment, returning to the step of assigning the boundary condition if the calculation is not converged, and ending the calculation if the calculation is converged.
In one possible implementation, the traffic item calculation format includes some or all of the following:
Roe；
van Leer；
AUSM series method;
a mixed windward method;
the rotating Riemann method.
In one possible implementation, the processor is specifically configured to:
carrying out laminar flow viscosity coefficient calculation and turbulent flow viscosity coefficient calculation;
the processor is specifically configured to:
the tack flux calculations were performed using the full tack format and thin layer approximation method.
In a third aspect, the present invention also provides a flow variable reconstruction device for aerodynamic thermal environment calculation, including:
the adjacent grid cell searching module is used for determining the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of an adjacent grid cell of the grid cell boundary surface aiming at any grid cell boundary surface, and searching and recording the number of the adjacent grid cell; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or if the adjacent grid cells are triangular grid cells and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, and searching and recording the cell numbers of the local structured cells according to the first number; if the grid cell boundary surface is the other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, and searching for a cell number for recording a local unstructured cell according to the second number;
The flow variable reconstruction module is used for performing variable reconstruction according to the type of the intelligent transformation limiter of the type of the boundary surface of the grid unit; if the grid cell boundary surface is marked as the first number, adopting a one-dimensional limiter to reconstruct variables; and if the grid cell boundary surface is marked as the second number, adopting a multidimensional limiter to reconstruct the variables.
In one possible implementation, the adjacent grid cell searching module is specifically configured to:
numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
marking the serial number of the grid cell boundary surface on the adjacent grid cells of the 1 st layer as the first serial number;
sequentially judging node numbers contained in other boundary surfaces of the 1 st layer adjacent grid cells, searching other grid cell boundary surfaces of the 1 st layer adjacent grid cells, which have no shared node with the first number, and marking the searched grid cell boundary surfaces as the second number;
the adjacent grid cells marked as the boundary surface of the second numbered grid cell are regarded as layer 2 adjacent grid cells.
In one possible implementation, the adjacent grid cell searching module is specifically configured to:
Numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
the third number is taken as a layer 2 adjacent grid cell.
In one possible implementation, the one-dimensional limiter includes some or all of the following:
a minmod limiter;
a van Leer limiter;
a van Albada limiter;
superbee limiter.
In one possible implementation, the multi-dimensional limiter includes some or all of the following:
a path limiter;
venkatakrishan limiter;
the path correction limiter.
In a possible implementation manner, the apparatus further includes a calculation module, before the step of reconstructing the grid cell boundary surface flow variation, the calculation module is configured to:
reading in calculation parameters and calculation control parameters;
reading and processing the computing grid and boundary condition information thereof;
initializing and calculating flow fields for all grid cells;
assigning a boundary condition;
after the grid cell boundary surface flow variable reconstruction step, the calculation module is configured to:
performing a convection flux term calculation;
judging a viscosity flux item, and if the viscosity exists, calculating a viscosity coefficient and calculating a viscosity flux; if the viscosity does not exist, judging a source item, if the source item exists, calculating the source item, and if the source item does not exist, calculating residual statistics and pneumatic parameters;
Calculating a time step;
performing time item pushing;
and (3) carrying out convergence judgment, returning to the step of assigning the boundary condition if the calculation is not converged, and ending the calculation if the calculation is converged.
In one possible implementation, the traffic item calculation format includes some or all of the following:
Roe；
van Leer；
AUSM series method;
a mixed windward method;
the rotating Riemann method.
In one possible implementation manner, the computing module is specifically configured to:
carrying out laminar flow viscosity coefficient calculation and turbulent flow viscosity coefficient calculation;
the computing module is specifically configured to:
the tack flux calculations were performed using the full tack format and thin layer approximation method.
In summary, the present invention provides a method, an apparatus, and a device for reconstructing a flow variable calculated in a aerodynamic thermal environment, where the method includes: firstly, searching adjacent grid cells of a grid cell boundary surface, specifically, if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or the adjacent grid cells are triangular grid single rings and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, searching for a cell number used for recording a local structured cell, if the adjacent grid cell boundary surface is other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, searching for a cell number used for recording a local unstructured cell, and then reconstructing a flow variable of the grid cell boundary surface, specifically, if the grid cell boundary surface is marked as the first number, reconstructing the variable by adopting a one-dimensional limiter, and if the cell boundary surface is marked as the second number, reconstructing the variable by adopting a multidimensional limiter. The reconstruction method provided by the invention can select the limiter according to the type of the boundary surface of the grid unit, so that the reconstruction method can be suitable for numerical simulation of any grid type, can effectively improve the flow characteristic resolving power of complex wave system interference including shock waves, contact discontinuities and the like on the premise of ensuring stable flow calculation, and realizes high-precision simulation of the pneumatic heating problem of the aircraft with complex appearance.
Drawings
FIG. 1 is a schematic flow chart of a method for reconstructing flow variables calculated in a aerodynamic thermal environment according to an embodiment of the present invention;
FIG. 2 is a schematic flow chart of a numerical simulation method adapting to any grid type according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a complete flow chart of a method for reconstructing a flow variable calculated in a aerodynamic thermal environment according to an embodiment of the present invention;
FIG. 4 is a diagram of a fourth type of shock interference flow field according to an embodiment of the present invention;
FIG. 5 is a schematic diagram showing the comparison of the heat flow of the wall surface and the test results according to the embodiment of the present invention;
FIG. 6 is a schematic structural diagram of a flow variable reconstruction device for aerodynamic thermal environment calculation according to an embodiment of the present invention;
fig. 7 is a schematic structural diagram of a flow variable reconstruction device for aerodynamic thermal environment calculation according to an embodiment of the present invention.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the invention are shown in the drawings.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
As mentioned in the background art, the invention provides a flow variable reconstruction method, equipment and device for calculation of a aerodynamic thermal environment, which can be applied to CFD software for prediction of hypersonic flow.
Referring to fig. 1, a flow chart of a flow variable reconstruction method for calculating a aerodynamic thermal environment according to an embodiment of the present invention is shown, where the method includes the following steps:
s101, searching adjacent grid cells of the grid cell boundary surface: determining the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface for any grid cell boundary surface, and searching and recording the numbers of the adjacent grid cells; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or if the adjacent grid cells are triangular grid cells and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, and searching and recording the cell numbers of the local structured cells according to the first number; if the grid cell boundary surface is the other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, and searching for a cell number for recording a local unstructured cell according to the second number;
S102, reconstructing the grid cell boundary surface flow variable: performing variable reconstruction according to the type of the intelligent transformation limiter of the type of the boundary surface of the grid unit; if the grid cell boundary surface is marked as the first number, adopting a one-dimensional limiter to reconstruct variables; and if the grid cell boundary surface is marked as the second number, adopting a multidimensional limiter to reconstruct the variables.
According to the embodiment of the invention, firstly, adjacent grid cells of the grid cell boundary surface are searched, specifically, for any grid cell boundary surface, the type of the grid cell boundary surface is determined according to the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface, and the numbers of the adjacent grid cells are searched and recorded according to the determined type of the grid cell boundary surface; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or the adjacent grid cells are triangular grid single rings and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, searching for the cell number of the local structured cell according to the first number, marking the grid cell boundary surface as a second number used for representing a second type if the grid cell boundary surface is other grid cell boundary surface, searching for the cell number of the local unstructured cell according to the second number, and then reconstructing the flow variable of the grid cell boundary surface. The reconstruction method provided by the invention can select the limiter according to the type of the boundary surface of the grid unit, so that the reconstruction method can be suitable for numerical simulation of any grid type, can effectively improve the flow characteristic resolving power of complex wave system interference including shock waves, contact discontinuities and the like on the premise of ensuring stable flow calculation, and realizes high-precision simulation of the pneumatic heating problem of the aircraft with complex appearance.
The embodiments of the present invention may be applied to any type of mesh, such as tetrahedral mesh, triangular prism mesh, pyramid mesh, hexahedral mesh, cartesian mesh, polyhedral mesh, and any type of hybrid mesh. The method specifically comprises a grid cell boundary surface adjacent cell searching step and a grid cell boundary surface flow variable reconstruction step, and can be used for CFD software under any unstructured grid finite volume frame.
In a specific implementation, if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells, representing cells containing local structuring, and determining the type of the grid cell boundary surface as a first type; if the adjacent grid cells are triangular prism grid cells and the boundary surfaces of the grid cells are triangles, representing the cells containing local structuring, and determining the type of the boundary surfaces of the grid cells as a first type; if the adjacent grid cells are other grid cells or the grid cell boundary surfaces are other shapes, namely other conditions except the two conditions, the local structural cells are not contained, and the type of the grid cell boundary surfaces is determined to be the second type.
In a specific implementation, the first number may be "0", the second number may be "1", and the third number may be "-1".
In one embodiment, when the unit numbers of the local structural units are searched and recorded according to the first number, that is, when the local structural units are contained, the adjacent grid unit numbers of the grid unit boundary surfaces can be recorded as the adjacent units of the 1 st layer; marking the number of the boundary surface of the grid cell on the adjacent grid cell of the 1 st layer as 0; and sequentially judging node numbers contained in other boundary surfaces of the 1 st layer adjacent grid cells, searching other grid boundary surfaces of the 1 st layer adjacent grid cells, which have no shared node with the grid cell boundary surface '0', marking the searched grid cell boundary surface number as '1', and then taking the adjacent grid cells of the grid cell boundary surface marked as '1' as the 2 nd layer adjacent grid cells.
If the grid cell boundary surface is marked as "0", a one-dimensional limiter is used for the variable reconstruction.
In another embodiment, when the unit numbers of the local unstructured units are searched and recorded according to the second number, that is, when the local unstructured units are not contained, the adjacent grid unit numbers of the grid unit boundary surface can be recorded as the adjacent units of the 1 st layer; record number "-1" is the layer 2 adjacent grid cell.
If the grid cell boundary surface is marked "1", a multi-dimensional limiter is used for the variable reconstruction.
The one-dimensional limiter in the embodiment of the invention may include some or all of the following:
a minmod limiter;
a van Leer limiter;
a van Albada limiter;
superbee limiter.
The multi-dimensional limiter may include some or all of the following:
a path limiter;
venkatakrishan limiter;
the path correction limiter.
In specific implementation, the variable reconstruction by using the one-dimensional limiter and the variable reconstruction by using the multi-dimensional limiter are the same as those in the prior art, and are not described herein.
Before the variable reconstruction, the embodiment of the invention firstly reads in the calculation parameters and the calculation control parameters, then reads in and processes the calculation grids and the boundary condition information thereof, then initializes the calculation flow field for all grid units, and finally carries out assignment on the boundary conditions.
After the variable reconstruction is carried out, firstly, calculation of a circulation quantity item is carried out, then judgment of a viscosity flux item is carried out, if viscosity exists, calculation of a viscosity coefficient and calculation of a viscosity flux are carried out, if no viscosity exists, judgment of a source item is carried out, if the source item exists, calculation of the source item is carried out, calculation of residual error statistics and pneumatic parameters is carried out, calculation of a time step is carried out, time item promotion is carried out, finally convergence judgment is carried out, if calculation is not converged, a step of assigning a boundary condition is carried out, if calculation is converged, and calculation is ended.
In one embodiment, the flow term calculation may be performed using the following method:
the Roe method, the van Leer method, the AUSM series method, the hybrid windward method, and the rotating Riemann method.
In one embodiment, the viscosity coefficient calculation may be performed as a laminar viscosity coefficient calculation and a turbulent viscosity coefficient calculation; tack flux calculations the tack flux calculations may be performed using full tack format and thin layer approximation methods.
The present invention is described below with reference to specific examples for the purpose of facilitating understanding.
As shown in fig. 2, a flow chart of a numerical simulation method adapting to any grid type provided in an embodiment of the present invention specifically includes the following steps:
s201, reading in calculation parameters and calculation control parameters;
the calculated parameters and calculated control parameters may include control equation type, thermodynamic and transport method selection, turbulence model, convection term format, viscous term format, one-dimensional limiter type, three-dimensional limiter type, time-marching method, among others.
S202, reading and processing the computing grid and boundary condition information thereof;
the boundary condition information may include grid node coordinates, grid cell connection relationships, grid parallel partitioning, grid metric coefficients, boundary condition types, and parameters, among others.
S203, initializing all grid cells, and calculating a flow field;
initializing all grid cells, wherein the initializing of all grid cells comprises giving original variables such as density, speed, pressure and the like to the center of the grid cells;
s204, assigning a boundary condition;
specifically, according to the boundary condition type and the parameters read in S202, the original variable values of density, speed, pressure and the like of the centers of the adjacent grid cells of the grid cell boundary surface are obtained.
S205, reconstructing the grid cell boundary surface flow variable;
in units T j The following are examples:
wherein q is the reconstructed original variable, q j Is unit T j R is the position vector of the reconstruction point, r j Is unit T j The position vector at the cell center is used to determine the position of the cell,is unit T j Variable gradient phi of (1) j Is unit T j Is provided.
In step 205, the process of reconstructing the variable employs the method for reconstructing the flow variable calculated in the aerodynamic thermal environment according to the embodiment of the present invention, specifically, as shown in fig. 3.
Fig. 3 is a complete flow chart of a flow variable reconstruction method for aerodynamic thermal environment calculation, which specifically includes the following steps:
s301, determining the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface;
S302, if the adjacent grid cells of the grid cell boundary surface are hexahedrons, executing S305;
s303, if the adjacent grid cells of the grid cell boundary surface are triangular prisms and the grid cell boundary surface is triangular, executing S305;
s304, if the adjacent grid cells of the grid cell boundary surface are other shapes except hexahedron and triangular prism, and/or the grid cell boundary surface is other shapes except triangle, executing S310;
s305, determining that the local structuring element is contained;
s306, numbering adjacent grid cells of the grid cell boundary surface as 1 st layer adjacent grid cells;
s307, numbering the grid cell boundary surface which is not co-located with the grid cell boundary surface as '1';
s308, numbering grid cells adjacent to the grid cell boundary surface numbered as 1 as a layer 2 adjacent grid cell;
s309, performing variable reconstruction by adopting a one-dimensional limiter;
s310, determining that the non-local structural units are contained;
s311, numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
s312, the number '-1' is the adjacent grid cell of the 2 nd layer;
s313, performing variable reconstruction by adopting a multidimensional limiter.
According to the embodiment of the invention, the convection flux at the two sides of the interface is calculated by utilizing the original variables at the two sides of the interface of the grid unit obtained in the grid unit interface flow variable reconstruction step. Performing variable reconstruction according to the type of the intelligent transformation limiter of the boundary surface type of the grid unit; if the boundary surface is marked with a 0 type boundary surface, adopting a one-dimensional limiter to reconstruct variables; if the boundary surface is marked with a type of '1', a multidimensional limiter is adopted for variable reconstruction.
S206, calculating a flux item;
in particular, the unified form of convection flux can be generally expressed as:
wherein, the liquid crystal display device comprises a liquid crystal display device,representing the convection flux at the interface along the out-of-interface normal, < >>Represent convection flux, Q L Representing the left reconstruction value, Q, of the interface R Representing the right reconstruction value of the interface, n jk Representing the external normal vector of the interface.
The difference between different convection formats is the convection fluxDifferent from the way in which the stream flux item calculation format is constructed, the selectable stream flux item calculation format includes: roe, van Leer, AUSM series, hybrid windward and spinning riman.
S207, judging whether a sticky item exists, if so, executing S208, otherwise, executing S210;
s208, performing viscosity coefficient calculation;
in a specific implementation, the viscosity coefficient calculation includes: laminar and turbulent viscosity coefficients. The laminar flow viscosity coefficient is calculated according to the type of the transportation method read in S201, and the turbulent flow viscosity coefficient is calculated according to the turbulent flow model read in S201.
S209, calculating a viscous flux item;
in implementations, the selectable sticky flux calculation format includes: full tack format and thin layer approximation methods.
S210, judging whether a source item exists, if so, executing S211, otherwise, executing S212;
S211, performing source item calculation;
specifically, the source term calculation may be performed according to the control equation type read in S201.
S212, carrying out residual error statistics and pneumatic parameter calculation;
specifically, residual statistics include density, speed, energy residuals; the aerodynamic parameter calculation includes aerodynamic force/moment coefficient and wall surface heat flow parameter.
S213, calculating a time step;
in particular, a local time-step technique may be employed to accelerate the convergence of the stationary solution. For unit Tj, the local time step is preferably:
Δt in equation (3) j Represents the time step, |T j The i is the volume of the grid cell,representing characteristic values e jk Area vector representing boundary surface, |e jk The l represents the area value of the boundary surface, and CFL represents the stable condition number.
CFL <1 is generally required for explicit methods, and larger CFL values may be desirable for implicit methods.
S214, performing time item pushing;
specifically, the time item pushing method may be a lus method, and the specific form is:
/>
|T in equation (4) j The i is the volume of the grid cell,the difference between the n+1th and n th steps is represented, the superscript n represents the last moment (known quantity), Δt is the time step, the right-hand term +.>The flux values of the opposite term, the viscous term and the source term are added by adding S206 to S211.
S215, judging whether convergence is carried out, if so, ending, otherwise, executing S204.
Specifically, convergence is determined when the residual is smaller than a certain set value.
The present invention will be further described with reference to specific examples.
And carrying out aerodynamic thermal numerical simulation on the fourth type of shock wave interference.
As shown in FIG. 4, the fourth type of shock wave interference flow field structure diagram obtained by calculation using the method of the present invention is a mixed grid comprising hexahedron, triangular prism, tetrahedron, pyramid, etc., wherein the Mach number of free incoming flow is 9.95, the attack angle is 0.0 DEG, and the Reynolds number of incoming flow is 1.66×10 5 m -1 The incoming flow static temperature is 52.5K, and the wall surface temperature is 293.0K, so that an interference structure is generated between the incident oblique shock wave calculated by the method and the cylindrical front edge bow shock wave, and a local high heat conduction area is formed after the interference area, so that a high heat flow area is formed on the wall surface.
The wall heat flow is compared with the test results as shown in FIG. 5, where the abscissa theta in FIG. 5 represents the angle and the ordinate Q w The heat flow value is represented, result is a calculated value obtained by adopting the method of the invention, and exp is a test value. As can be seen from FIG. 5, the method of the present invention calculates the peak value of 570kW/m of heat flow in the shock interference area 2 The calculated heat flow result is well matched with the test measurement result, and the relative error is within 10%, so that the method has good prediction capability on the heat flow value of the wall surface which is concerned in engineering practice.
Based on the same inventive concept, the invention also provides a flow variable reconstruction device for the boundary surface of the grid unit, the principle of solving the problem of the device is similar to that of the flow variable reconstruction method calculated by any one of the aerodynamic thermal environments, and the repetition is omitted.
As shown in fig. 6, a schematic structural diagram of a flow variable reconstruction device for aerodynamic thermal environment calculation provided by the present invention, the device includes one or more processors 601;
a memory 602 for storing one or more programs that, when executed by the one or more processors, cause the one or more processors 601 to implement the steps of:
a step of searching adjacent grid cells of the grid cell boundary surface: determining the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface for any grid cell boundary surface, and searching and recording the numbers of the adjacent grid cells; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or if the adjacent grid cells are triangular grid cells and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, and searching and recording the cell numbers of the local structured cells according to the first number; if the grid cell boundary surface is the other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, and searching for a cell number for recording a local unstructured cell according to the second number;
A grid cell boundary surface flow variable reconstruction step: performing variable reconstruction according to the type of the intelligent transformation limiter of the type of the boundary surface of the grid unit; if the grid cell boundary surface is marked as the first number, adopting a one-dimensional limiter to reconstruct variables; and if the grid cell boundary surface is marked as the second number, adopting a multidimensional limiter to reconstruct the variables.
In one possible implementation, the processor 601 is specifically configured to:
numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
marking the serial number of the grid cell boundary surface on the adjacent grid cells of the 1 st layer as the first serial number;
sequentially judging node numbers contained in other boundary surfaces of the 1 st layer adjacent grid cells, searching other grid cell boundary surfaces of the 1 st layer adjacent grid cells, which have no shared node with the first number, and marking the searched grid cell boundary surfaces as the second number;
the adjacent grid cells marked as the boundary surface of the second numbered grid cell are regarded as layer 2 adjacent grid cells.
In one possible implementation, the processor 601 is specifically configured to:
Numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
the third number is taken as a layer 2 adjacent grid cell.
In one possible implementation, the one-dimensional limiter includes some or all of the following:
a minmod limiter;
a van Leer limiter;
a van Albada limiter;
superbee limiter.
In one possible implementation, the multi-dimensional limiter includes some or all of the following:
a path limiter;
venkatakrishan limiter;
the path correction limiter.
In a possible implementation, before the grid cell boundary surface flow variable reconstruction step, the processor 601 is further configured to:
reading in calculation parameters and calculation control parameters;
reading and processing the computing grid and boundary condition information thereof;
initializing and calculating flow fields for all grid cells;
assigning a boundary condition;
after the grid cell boundary surface flow variable reconstruction step, the processor 601 is further configured to:
performing a convection flux term calculation;
judging a viscosity flux item, and if the viscosity exists, calculating a viscosity coefficient and calculating a viscosity flux; if the viscosity does not exist, judging a source item, if the source item exists, calculating the source item, and if the source item does not exist, calculating residual statistics and pneumatic parameters;
Calculating a time step;
performing time item pushing;
and (3) carrying out convergence judgment, returning to the step of assigning the boundary condition if the calculation is not converged, and ending the calculation if the calculation is converged.
In one possible implementation, the traffic item calculation format includes some or all of the following:
Roe；
van Leer；
AUSM series method;
a mixed windward method;
the rotating Riemann method.
In one possible implementation, the processor 601 is specifically configured to:
carrying out laminar flow viscosity coefficient calculation and turbulent flow viscosity coefficient calculation;
the processor is specifically configured to:
the tack flux calculations were performed using the full tack format and thin layer approximation method.
Based on the same inventive concept, the invention also provides a flow variable reconstruction device for the boundary surface of the grid unit, the principle of solving the problem of the device is similar to that of the flow variable reconstruction method calculated by any one of the aerodynamic thermal environments, and the repetition is omitted.
As shown in fig. 7, a flow variable reconstruction device for calculating a aerodynamic thermal environment according to an embodiment of the present invention includes:
the adjacent grid cell searching module 701 determines the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface for any grid cell boundary surface, and searches for and records the number of the adjacent grid cells; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or if the adjacent grid cells are triangular grid cells and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, and searching and recording the cell numbers of the local structured cells according to the first number; if the grid cell boundary surface is the other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, and searching for a cell number for recording a local unstructured cell according to the second number;
A flow variable reconstruction module 702, configured to perform variable reconstruction according to the type of the intelligent transformation limiter type of the grid cell boundary surface; if the grid cell boundary surface is marked as the first number, adopting a one-dimensional limiter to reconstruct variables; and if the grid cell boundary surface is marked as the second number, adopting a multidimensional limiter to reconstruct the variables.
In one possible implementation, the neighboring grid cell search module 701 is specifically configured to:
numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
marking the serial number of the grid cell boundary surface on the adjacent grid cells of the 1 st layer as the first serial number;
sequentially judging node numbers contained in other boundary surfaces of the 1 st layer adjacent grid cells, searching other grid cell boundary surfaces of the 1 st layer adjacent grid cells, which have no shared node with the first number, and marking the searched grid cell boundary surfaces as the second number;
the adjacent grid cells marked as the boundary surface of the second numbered grid cell are regarded as layer 2 adjacent grid cells.
In one possible implementation, the neighboring grid cell search module 701 is specifically configured to:
Numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells;
the third number is taken as a layer 2 adjacent grid cell.
In one possible implementation, the one-dimensional limiter includes some or all of the following:
a minmod limiter;
a van Leer limiter;
a van Albada limiter;
superbee limiter.
In one possible implementation, the multi-dimensional limiter includes some or all of the following:
a path limiter;
venkatakrishan limiter;
the path correction limiter.
In a possible implementation manner, the apparatus further includes a calculation module 703, where before the step of reconstructing the grid cell boundary surface flow variation, the calculation module 703 is configured to:
reading in calculation parameters and calculation control parameters;
reading and processing the computing grid and boundary condition information thereof;
initializing and calculating flow fields for all grid cells;
assigning a boundary condition;
after the grid cell boundary surface flow variable reconstruction step, the calculation module 703 is configured to:
performing a convection flux term calculation;
judging a viscosity flux item, and if the viscosity exists, calculating a viscosity coefficient and calculating a viscosity flux; if the viscosity does not exist, judging a source item, if the source item exists, calculating the source item, and if the source item does not exist, calculating residual statistics and pneumatic parameters;
Calculating a time step;
performing time item pushing;
and (3) carrying out convergence judgment, returning to the step of assigning the boundary condition if the calculation is not converged, and ending the calculation if the calculation is converged.
In one possible implementation, the traffic item calculation format includes some or all of the following:
Roe；
van Leer；
AUSM series method;
a mixed windward method;
the rotating Riemann method.
In one possible implementation, the computing module 703 is specifically configured to:
carrying out laminar flow viscosity coefficient calculation and turbulent flow viscosity coefficient calculation;
the computing module 703 is specifically configured to:
the tack flux calculations were performed using the full tack format and thin layer approximation method.
The invention provides a flow variable reconstruction method, equipment and a device for calculation of a aerodynamic thermal environment, wherein the method comprises the following steps: firstly, searching adjacent grid cells of a grid cell boundary surface, specifically, if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or the adjacent grid cells are triangular grid single rings and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, searching for a cell number used for recording a local structured cell, if the adjacent grid cell boundary surface is other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, searching for a cell number used for recording a local unstructured cell, and then reconstructing a flow variable of the grid cell boundary surface, specifically, if the grid cell boundary surface is marked as the first number, reconstructing the variable by adopting a one-dimensional limiter, and if the cell boundary surface is marked as the second type, reconstructing the variable by adopting a multidimensional limiter. The reconstruction method provided by the invention can select the limiter according to the type of the boundary surface of the grid unit, so that the reconstruction method can be suitable for numerical simulation of any grid type, can effectively improve the flow characteristic resolving power of complex wave system interference including shock waves, contact discontinuities and the like on the premise of ensuring stable flow calculation, and realizes high-precision simulation of the pneumatic heating problem of the aircraft with complex appearance.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the method of the present invention and its core ideas. The foregoing is merely illustrative of the preferred embodiments of this invention, and it is noted that there is objectively no limit to the specific structure disclosed herein, since numerous modifications, adaptations and variations can be made by those skilled in the art without departing from the principles of the invention, and the above-described features can be combined in any suitable manner; such modifications, variations and combinations, or the direct application of the inventive concepts and aspects to other applications without modification, are contemplated as falling within the scope of the present invention.
Claims (8)
1. A method for reconstructing a flow variation of a calculation of a aerodynamic thermal environment, the method comprising:
a step of searching adjacent grid cells of the grid cell boundary surface: determining the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of the adjacent grid cells of the grid cell boundary surface for any grid cell boundary surface, and searching and recording the numbers of the adjacent grid cells; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or if the adjacent grid cells are triangular grid cells and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, and searching and recording the cell numbers of the local structured cells according to the first number; if the grid cell boundary surface is the other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, and searching for a cell number for recording a local unstructured cell according to the second number;
The searching for the unit number of the recording local structuring unit according to the first number includes: numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells; marking the serial number of the grid cell boundary surface on the adjacent grid cells of the 1 st layer as the first serial number; sequentially judging node numbers contained in other boundary surfaces of the 1 st layer adjacent grid cells, searching other grid cell boundary surfaces of the 1 st layer adjacent grid cells, which have no shared node with the first number, and marking the searched grid cell boundary surfaces as the second number; taking the adjacent grid cells marked as the grid cell boundary surface of the second number as a layer 2 adjacent grid cell;
the searching for the unit number of the local unstructured unit according to the second number includes: numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells; taking the third number as a layer 2 adjacent grid unit;
a grid cell boundary surface flow variable reconstruction step: performing variable reconstruction according to the type of the intelligent transformation limiter of the type of the boundary surface of the grid unit; if the grid cell boundary surface is marked as the first number, adopting a one-dimensional limiter to reconstruct variables; if the grid cell boundary surface is marked as the second number, adopting a multidimensional limiter to reconstruct variables;
And (5) performing aerodynamic thermal environment calculation by using the reconstructed variables.
2. The method of claim 1, wherein the one-dimensional limiter comprises some or all of:
a minmod limiter;
a van Leer limiter;
a van Albada limiter;
superbee limiter.
3. The method of claim 1, wherein the multi-dimensional limiter comprises some or all of:
a path limiter;
venkatakrishan limiter;
the path correction limiter.
4. A method according to any one of claims 1 to 3, wherein prior to the grid cell boundary surface flow variation reconstruction step, further comprising:
reading in calculation parameters and calculation control parameters;
reading and processing the computing grid and boundary condition information thereof;
initializing and calculating flow fields for all grid cells;
assigning a boundary condition;
after the grid cell boundary surface flow variable reconstruction step, the method further comprises the following steps:
performing a convection flux term calculation;
judging a viscosity flux item, and if the viscosity exists, calculating a viscosity coefficient and calculating a viscosity flux; if the viscosity does not exist, judging a source item, if the source item exists, calculating the source item, and if the source item does not exist, calculating residual statistics and pneumatic parameters;
Calculating a time step;
performing time item pushing;
and (3) carrying out convergence judgment, returning to the step of assigning the boundary conditions if the calculation is not converged, and ending the calculation if the calculation is converged.
5. The method of claim 4, wherein the traffic item calculation format includes some or all of the following:
Roe；
van Leer；
AUSM series method;
a mixed windward method;
the rotating Riemann method.
6. The method of claim 4, wherein said performing a viscosity coefficient calculation comprises:
carrying out laminar flow viscosity coefficient calculation and turbulent flow viscosity coefficient calculation;
the viscous flux calculation includes:
the tack flux calculations were performed using the full tack format and thin layer approximation method.
7. A flow variable reconstruction device for aerodynamic thermal environment calculation, comprising one or more processors;
a memory for storing one or more programs that, when executed by the one or more processors, cause the one or more processors to implement a method of flow variable reconstruction for aerodynamic thermal environment computation of any one of claims 1-6.
8. A flow variable reconstruction device for calculation of a aerodynamic thermal environment, comprising:
The adjacent grid cell searching module is used for determining the type of the grid cell boundary surface according to the shape of the grid cell boundary surface and the shape of an adjacent grid cell of the grid cell boundary surface aiming at any grid cell boundary surface, and searching and recording the number of the adjacent grid cell; if the adjacent grid cells of the grid cell boundary surface are hexahedral grid cells or if the adjacent grid cells are triangular grid cells and the grid cell boundary surface is triangular, marking the grid cell boundary surface as a first number used for representing a first type, and searching and recording the cell numbers of the local structured cells according to the first number; if the grid cell boundary surface is the other grid cell boundary surface, marking the grid cell boundary surface as a second number used for representing a second type, and searching for a cell number for recording a local unstructured cell according to the second number;
the searching for the unit number of the recording local structuring unit according to the first number includes: numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells; marking the serial number of the grid cell boundary surface on the adjacent grid cells of the 1 st layer as the first serial number; sequentially judging node numbers contained in other boundary surfaces of the 1 st layer adjacent grid cells, searching other grid cell boundary surfaces of the 1 st layer adjacent grid cells, which have no shared node with the first number, and marking the searched grid cell boundary surfaces as the second number; taking the adjacent grid cells marked as the grid cell boundary surface of the second number as a layer 2 adjacent grid cell;
The searching for the unit number of the local unstructured unit according to the second number includes: numbering adjacent grid cells of the grid cell boundary surface as a 1 st layer of adjacent grid cells; taking the third number as a layer 2 adjacent grid unit;
the flow variable reconstruction module is used for performing variable reconstruction according to the type of the intelligent transformation limiter of the type of the boundary surface of the grid unit; if the grid cell boundary surface is marked as the first number, adopting a one-dimensional limiter to reconstruct variables; if the grid cell boundary surface is marked as the second number, adopting a multidimensional limiter to reconstruct variables; and (5) performing aerodynamic thermal environment calculation by using the reconstructed variables.
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