CN117787144A - SST turbulence model correction method and system for supersonic shock boundary layer interference - Google Patents
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Abstract
The invention belongs to the technical field of fluid mechanics, and particularly discloses a supersonic shock boundary layer interference-oriented SST turbulence model correction method and system, wherein the method comprises the following steps: obtaining turbulence energy, specific dissipation rate and turbulence movement viscosity; calculating an effective specific dissipation ratio; calculating a corrected turbulence movement viscosity; calculating a correction coefficient; obtaining a normalized pressure gradient; acquiring a relation between the standardized pressure gradient and the correction coefficient; bringing the acquired standardized pressure gradient into a relation to obtain a correction coefficient; the Bradshaw constant in the limiter was modified with a correction factor to calculate turbulence motion viscosity. According to the invention, the Bradshaw constant is corrected through the functional relation between the correction coefficient and the standardized pressure gradient, so that the limiter can change along with the change of the pressure gradient, the prediction error caused by the constant in the Bradshaw hypothesis is reduced, and the prediction accuracy of the SST model on the disturbance of the supersonic shock wave/turbulent boundary layer is further improved.
Description
Technical Field
The invention belongs to the technical field of fluid mechanics, and particularly relates to an SST turbulence model correction method and system for supersonic shock boundary layer interference.
Background
The SST (Shear-Stress Transport) turbulence model is one of the mainstream models for computing aerospace engineering turbulence in the Reynolds-average Navier-Stokes (RANS) method. The model has good prediction accuracy for small separation turbulence at subsonic velocity. However, this model has a large prediction error for the supersonic shock/boundary layer disturbance complex separation flow due to the restriction of the Bradshaw constant in the limiter. The prediction result of the model on the ultrasonic shock wave/boundary layer disturbance complex separation flow can be improved by artificially adjusting the value of the Bradshaw constant, but the model has strong experience and poor universality and often has the defect of failure in consideration of the experience. In particular, merely changing the magnitude of the Bradshaw constant value tends to improve the split stream prediction results while at the same time causing the model to have reduced prediction accuracy for other flow conditions.
Therefore, how to achieve the aim of improving the prediction result of the SST model on the ultrasonic shock wave/boundary layer interference complex separation flow and simultaneously considering the original prediction accuracy of the SST model on the subsonic small separation flow is a problem to be solved in the field.
Disclosure of Invention
In view of the above, the invention provides a method and a system for modifying an SST turbulence model for supersonic shock boundary layer interference, which are used for improving the prediction accuracy of the SST model by modifying the Bradshaw constant in a limiter.
In order to solve the technical problems, the technical scheme of the invention is to adopt an SST turbulence model correction method facing to the interference of a supersonic shock boundary layer, which comprises the following steps:
solving a control equation of turbulent transportation variables in the SST turbulent model to obtain turbulent energySpecific dissipation ratio->And turbulent motion viscosity->；
By using turbulent energyAnd turbulent motion viscosity->Calculating the effective specific dissipation ratio->；
By using anisotropic componentsTime mean strain rate tensor->Calculate the corrected turbulence movement viscosity +.>；
Using modified turbulence movement viscosityTurbulent energy->Calculating the modified effective specific dissipation ratio +.>And using the modified effective specific dissipation ratio +.>Sum of specific dissipation ratio->Calculate correction factor->；
Calculating a pressure gradientAnd according to the density->Speed->And dynamic viscosity->Normalizing it to obtain normalized pressure gradient +.>；
By combining several correction coefficientsSeveral normalized pressure gradients +.>Fitting the data to obtain normalized pressure gradient +.>And correction coefficient->A relation between them;
normalized pressure gradient to be obtainedCarrying-in relation to obtain correction factor->The method comprises the steps of carrying out a first treatment on the surface of the By means of correction factors->Correction limiter Bradshaw constant +.>For calculating turbulence movement viscosity->。
As an improvement, the formula is utilized
;
;
;
Calculating turbulence energySpecific dissipation ratio->And turbulent motion viscosity->；
In the above equation
;
；
；
；
;
;
;
;
;
;
Wherein,is a partial derivative operation symbol->For time (I)>For density (I)>For speed->For the Kronecker symbol, x is the coordinate axis, subscript +.>And->Index for spatial dimension>Is momentum viscosity->，/>For exercise viscosity +.>Is of vortex size>Is rotation rate tensor +.>For object plane distance->Viscosity for turbulent momentum->，/>Is a natural base number, a 1 Is a Bradshaw constant; sigma (sigma) k 、σ ω 、σ ω2 β, β are constant parameters.
As an improvement, the formula is utilized
;
Calculating an effective specific dissipation ratio, whereinFor an effective specific dissipation ratio->For turbulent motion, add>Is a turbulent motion viscosity.
As an improvement, a corrected turbulence movement viscosity is calculatedThe method of (1) comprises:
high-credibility Reynolds stress calculation method based on direct numerical simulation or large vortex simulation methodAnd turbulence energy calculation anisotropy component +.>The formula is:
;
wherein,for the opposite component->Reynolds stress for high confidence +.>For turbulent motion, add>Is a Kronecker symbol;
calculating a time-averaged strain rate tensor from the RANS velocity fieldThe formula is as follows:
;
wherein,is the time-averaged strain rate tensor, +.>Is a partial derivative operation symbol->For speed, x is the coordinate axis, subscript +.>And->Index for spatial dimension;
turbulence motion viscosity corrected by least square inverse calculationThe formula is as follows:
;
wherein,viscosity for modified turbulent motion.
As an improvement, the formula is utilized
;
The modified effective specific dissipation ratio is calculated, wherein,for a modified effective specific dissipation ratio +.>For modified turbulence movement viscosity +.>Is turbulent energy;
using the formula
;
Calculating a correction factor, wherein,for correction factor +.>For an effective specific dissipation ratio->For a modified effective specific dissipation ratio.
As an improvement, the RANS solver coupled to the SST turbulence model calculates the pressure gradient as:
;
;
wherein,for pressure gradient +.>Is a partial derivative operation symbol, p is pressure, < ->The velocity vector is the velocity vector, x, y and z are the space coordinate axes, and u, v and w are the velocities in the x, y and z axes respectively;
the pressure gradient is normalized, and the formula is:
;
wherein,for normalizing the pressure gradient, +.>For density (I)>Is momentum viscous.
As an improvement, the relation between the normalized pressure gradient and the correction coefficient is:
;
;
wherein,for correction factor +.>To normalize the pressure gradient.
The invention also provides an SST turbulence model correction system facing the supersonic shock boundary layer interference, which is used for realizing the SST turbulence model correction method facing the supersonic shock boundary layer interference, and comprises the following steps:
the control equation solving module is used for solving a control equation of a turbulent flow transportation variable in the SST turbulent flow model to obtain turbulent flow energySpecific dissipation ratio->And turbulent motion viscosity->；
An effective specific dissipation ratio acquisition module for utilizing turbulent energyAnd turbulent motion viscosity->Calculating the effective specific dissipation ratio->；
Turbulence motion viscosity correction module for utilizing anisotropic componentsTime mean strain rate tensor->Calculate the corrected turbulence movement viscosity +.>；
Correction coefficient acquisition module for using corrected turbulence motion viscosityTurbulent energy->Calculating the modified effective specific dissipation ratio +.>And using the modified effective specific dissipation ratio +.>Sum of specific dissipation ratio->Calculate correction factor->；
Pressure gradient normalization module for calculating pressure gradientAnd according to the density->Speed->Dynamic viscosityNormalizing it to obtain normalized pressure gradient +.>；
A data fitting module for fitting a plurality of correction coefficientsSeveral normalized pressure gradients +.>Fitting the data to obtain normalized pressure gradient +.>And correction coefficient->A relation between them;
a constant correction module for correcting the obtained normalized pressure gradientCarrying-in relation to obtain correction factor->The method comprises the steps of carrying out a first treatment on the surface of the And uses correction coefficient->Correction limiter Bradshaw constant +.>For calculating turbulence movement viscosity->。
The invention has the advantages that:
the method comprises the steps of obtaining a functional relation between a correction coefficient and a standardized pressure gradient in advance through a data fitting mode; when in use, the standardized pressure gradient is brought into the functional relation, and a correction coefficient is calculated; bradshaw constant in limiter by correction coefficientThe corrections are made and then the turbulence motion viscosity is recalculated and assigned to the RANS equation. The invention relates to a method for correcting the Bradshaw constant by correcting the function relation of the coefficient and the normalized pressure gradient>And correction is carried out, so that the limiter can change along with the change of the pressure gradient, the prediction error caused by a constant in the Bradshaw hypothesis is reduced, and the prediction accuracy of the SST model on the disturbance of the supersonic shock wave/turbulence boundary layer is further improved.
In addition, after the functional relation between the correction coefficient and the standardized pressure gradient is obtained, the correction coefficient can be directly used in engineering, so that the efficiency of engineering application is greatly improved, and the expenditure of calculation force is reduced.
Drawings
FIG. 1 is a flow chart of the present invention.
Fig. 2 is a schematic structural diagram of the present invention.
Fig. 3A, 3B are comparisons of wall force coefficient distributions for 24 ° compression corner calculations, where 3A is the pressure coefficient and 3B is the friction resistance coefficient.
Fig. 4A, 4B are comparisons of wall force coefficient distributions for 14 ° compression corner calculations, where 4A is the pressure coefficient and 4B is the friction resistance coefficient.
Fig. 5A and 5B are comparisons of wall force coefficient distributions for 24 ° flat panel calculations, where 5A is the pressure coefficient and 5B is the friction resistance coefficient.
Detailed Description
In order to make the technical scheme of the present invention better understood by those skilled in the art, the present invention will be further described in detail with reference to the following specific embodiments.
Chinese patent CN202210844359.1 discloses a prediction scheme of split flow under strong reverse pressure gradient, which obtains a calculation grid according to the external dimension of the model, and reads the incoming flow parameters; according to the grid, the condition parameters and the incoming flow parameters, an SST turbulence model is taken as a basic frame, gradient factors related to pressure gradient and velocity gradient are constructed, automatic correction is realized under a strong gradient region of a mode constant, and therefore the vortex viscosity coefficient added with a limiter based on the Bradshaw hypothesis is corrected.
In the prior art, the construction of gradient factors related to pressure gradient and velocity gradient needs parameters based on models and assumptions, and a certain error may be introduced; and secondly, complex model construction and gradient factor calculation are carried out, so that the method is not suitable for engineering.
In order to solve the problem, as shown in fig. 1, the invention provides a method for correcting an SST turbulence model for supersonic shock boundary layer interference, comprising the following steps:
s1, solving a control equation of turbulent transport variables in an SST turbulent model to obtain turbulent energySpecific dissipation ratio->And turbulent motion viscosity->；
SST (Shear Stress Transport) turbulence model is a mathematical model for calculating fluid turbulence. The main function is to simulate and predict the turbulent flow of fluid when performing Computational Fluid Dynamics (CFD) analysis to obtain more accurate flow field data. In this step, turbulent energy is obtained by solving a control equation for turbulent transport variables in the SST turbulent modelSpecific dissipation ratio->And turbulent motion viscosity->. Specifically, the control equation is
In the above equation
；
The turbulence energy generates the items:；
specific dissipation ratio generation term:；
cross diffusion term:
wherein,is a partial derivative operation symbol->For time (I)>For density (I)>For speed->For the Kronecker symbol, x is the coordinate axis, subscript +.>And->Index for spatial dimension>Is momentum viscosity->，/>For exercise viscosity +.>Is of vortex size>Is rotation rate tensor +.>For object plane distance->Viscosity for turbulent momentum->，/>Is a natural base number, a 1 Is a Bradshaw constant; sigma (sigma) k 、σ ω 、σ ω2 β, β are constant parameters.
S2 utilizing turbulent energyAnd turbulent motion viscosity->Calculating the effective specific dissipation ratio->。
In the SST turbulence model, the specific dissipation ratio and the effective specific dissipation ratio are important physical quantities used to describe the turbulent shear stress and turbulent dissipation process.
The specific dissipation ratio represents the rate of change of velocity produced by the rotating vortex in turbulence. It describes the generation and disruption of vortices during turbulent motion. The specific dissipation ratio equation describes how the specific dissipation ratio varies with time and space. In the SST turbulence model, the specific dissipation ratio equation is obtained by solving the transport equation, which considers the diffusion and generation terms of the specific dissipation ratio.
While the effective specific dissipation ratio is a modified specific dissipation ratio intended to more accurately characterize turbulent dissipation. The effective specific dissipation ratio considers the interaction of vortex viscosity and turbulence energy in the specific dissipation ratio equation by introducing a correction factor, thereby improving the precision of the model.
In this step, the formula is used
Calculating an effective specific dissipation ratio, whereinFor an effective specific dissipation ratio->For turbulent motion, add>Is a turbulent motion viscosity.
S3 utilizing anisotropic componentsTime mean strain rate tensor->Calculate the corrected turbulence movement viscosity +.>The method specifically comprises the following steps:
s31, calculating high-reliability Reynolds stress based on direct numerical simulation or large vortex simulation methodAnd turbulence energy calculation anisotropy component +.>The formula is:
wherein,for the opposite component->Reynolds stress for high confidence +.>For turbulent motion, add>Is a Kronecker symbol;
s32 calculates the time-average strain rate tensor from the RANS (Reynolds-average Navier-Stokes Reynolds average turbulence) velocity fieldThe formula is as follows:
wherein,is the time-averaged strain rate tensor, +.>Is a partial derivative operationSymbol (S)>For speed, x is the coordinate axis, subscript +.>And->Index for spatial dimension;
s33, using least square method to calculate back corrected turbulence movement viscosityThe formula is as follows:
wherein,viscosity for modified turbulent motion. In turbulence simulation, the viscosity of the turbulent motion is one parameter in the simulation calculation. A least squares method is often used in simulation calculations to optimize this parameter to make the simulation result more accurate. The process of parameter optimization using the least squares method is called back calculation (calculation) and adjusts certain parameters in the simulation by comparing with actual observed data so that the simulation result is closer to the actual situation. In turbulent flow simulation, the objective of back calculation is to reduce the error between the simulation result and the actual observed data by adjusting the viscosity parameter, thereby improving the accuracy of the simulation.
S4 using modified turbulence motion viscosityTurbulent energy->Calculating the modified effective specific dissipation ratio +.>And make use of repairPositive effective specific dissipation ratio->Sum of specific dissipation ratio->Calculate correction factor->The method comprises the steps of carrying out a first treatment on the surface of the Specifically, the formula is utilized
The modified effective specific dissipation ratio is calculated, wherein,for a modified effective specific dissipation ratio +.>For modified turbulence movement viscosity +.>Is turbulent energy;
using the formula
Calculating a correction factor, wherein,for correction factor +.>For an effective specific dissipation ratio->For a modified effective specific dissipation ratio.
By using turbulent energyAnd turbulent motion viscosity->Calculated effective specific dissipation ratio->In practice, there is a certain error due to the turbulence movement viscosity +.>Is a function of the error of (a). Thus, after the viscosity of the turbulent motion is corrected in the previous step, further correction of the effective specific dissipation ratio is required. And effective specific dissipation ratio->Effective specific dissipation ratio with correction +.>Ratio of->The actual correction factor is used to represent the error rate between the two.
S5 calculating the pressure gradientAnd according to the density->Speed->And dynamic viscosity->Normalizing it to obtain normalized pressure gradient +.>The method comprises the steps of carrying out a first treatment on the surface of the The method specifically comprises the following steps:
s51, a RANS solver coupled with an SST turbulence model calculates the pressure gradient, and the formula is as follows:
wherein,for pressure gradient +.>Is a partial derivative operation symbol, p is pressure, < ->The velocity vector is the velocity vector, x, y and z are the space coordinate axes, and u, v and w are the velocities in the x, y and z axes respectively;
s52, normalizing the pressure gradient, wherein the formula is as follows:
wherein,for normalizing the pressure gradient, +.>For density (I)>Is momentum viscous.
Obtaining corrected turbulence motion viscosity in step S3The method of the method has huge consumption and more limiting conditions, and cannot be applied to engineering. And the correction coefficient is obtained in step S4>The calculation result based on step S3 is required, and thus cannot be applied to engineering as well. Steps S3, S4 and the object of this stepThe method is characterized in that a plurality of correction coefficients and normalized pressure gradients are obtained through limited calculation examples, so that the functional relation between the correction coefficients and the normalized pressure gradients is obtained through a data fitting mode. When engineering application is carried out, the standard pressure gradient is taken as an independent variable, the correction coefficient is taken as a dependent variable, and the correction coefficient is obtained through the function relation between the standard pressure gradient and the dependent variable to adjust the Bradshaw constant, so that a large amount of calculation is not needed, and the efficiency is improved.
S6, a plurality of correction coefficientsSeveral normalized pressure gradients +.>Fitting the data to obtain normalized pressure gradient +.>And correction coefficient->And a relational expression between the two.
Data fitting is a process of approximating or adapting a set of actual observed data by a mathematical function. Given a set of observed data points, the goal of data fitting is to find a functional model that best fits the data points, thereby better predicting and describing the behavior of the data.
Specifically, in turbulence simulation, by performing simulation calculations on a series of examples, data for some correction factors and normalized pressure gradients can be obtained. To obtain a functional relationship between these data, a method of data fitting may be used.
The process of fitting data typically involves selecting an appropriate mathematical function model (e.g., linear function, polynomial function, exponential function, etc.), and then determining the parameters of the function model by minimizing the fitting error (typically using a least squares method) so that the fitted function best approximates the observed data.
By fitting the data, a functional model can be obtained that can be used to interpolate, extrapolate, or predict the value of an unknown data point. In this way, the relationship of this fitting function can be used to derive a functional relationship between the correction factor and the normalized pressure gradient, so that predictions and calculations can be made without additional experimental data.
In the invention, a plurality of correction coefficients calculated in the steps S3 to S5,Several normalized pressure gradients +.>Are all observed data (i.e. actual data), and the objective of this step is to determine the functional relationship between the two by means of the observed data.
The relation between the normalized pressure gradient and the correction coefficient in the invention is as follows:
wherein,for correction factor +.>To normalize the pressure gradient.
S7 normalized pressure gradient to be acquiredCarrying-in relation to obtain correction factor->The method comprises the steps of carrying out a first treatment on the surface of the By means of correction factors->Correction limiter Bradshaw constant->For calculating turbulence movement viscosity->。
During engineering application, the pressure gradient is normalizedCarrying-in relation to obtain correction factor->Correction coefficient->As Bradshaw constant->Coefficient of-> Substitution of +.>To calculate turbulent motion viscosityThe specific formula is as follows:
the letter meaning is referred to in step S1.
The correction effect of the above method is verified by an example for the invention. Typical example operating conditions for supersonic shock/boundary layer disturbances are shown in the following table:
the following is a comparison of the separation vortex parameters predicted by the different methods, wherein DNS represents a direct numerical simulation, EXP represents an experiment, SST represents a traditional SST turbulence model, and SST-mod represents a modified SST model of the method
As shown, fig. 3A and 3B are exemplary wall force coefficient distributions for a 24 ° compression corner, where 3A is the pressure coefficient and 3B is the friction resistance coefficient.
Fig. 4A, 4B are comparisons of wall force coefficient distributions for 14 ° compression corner calculations, where 4A is the pressure coefficient and 4B is the friction resistance coefficient.
Fig. 5A and 5B are comparisons of wall force coefficient distributions for 24 ° flat panel calculations, where 5A is the pressure coefficient and 5B is the friction resistance coefficient.
As can be seen from the above table and the above graph, the predicted result is closer to the true value than the conventional SST turbulence model after the correction method provided by the invention is adopted.
As shown in fig. 2, the present invention further provides an SST turbulence model correction system for supersonic shock boundary layer interference, which is configured to implement the above-mentioned SST turbulence model correction method for supersonic shock boundary layer interference, and includes:
the control equation solving module is used for solving a control equation of a turbulent flow transportation variable in the SST turbulent flow model to obtain turbulent flow energySpecific dissipation ratio->And turbulent motion viscosity->；
An effective specific dissipation ratio acquisition module for utilizing turbulent energyAnd turbulent motion viscosity->Calculating the effective specific dissipation ratio->；
Turbulence motion viscosity correction module for utilizing anisotropic componentsTime mean strain rate tensor->Calculate the corrected turbulence movement viscosity +.>；
Correction coefficient acquisition module for using corrected turbulence motion viscosityTurbulent energy->Calculating the modified effective specific dissipation ratio +.>And using the modified effective specific dissipation ratio +.>Sum of specific dissipation ratio->Calculate correction factor->；
Pressure gradient normalization module for calculating pressure gradientAnd according to the density->Speed->Dynamic viscosityNormalizing it to obtain normalized pressure gradient +.>；
A data fitting module for fitting a plurality of correction coefficientsSeveral normalized pressure gradients +.>Fitting the data to obtain normalized pressure gradient +.>And correction coefficient->A relation between them;
a constant correction module for correcting the obtained normalized pressure gradientCarrying-in relation to obtain correction factor->The method comprises the steps of carrying out a first treatment on the surface of the And uses correction coefficient->Correction limiter Bradshaw constant +.>For calculating turbulence movement viscosity->。
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that the above-mentioned preferred embodiment should not be construed as limiting the invention, and the scope of the invention should be defined by the appended claims. It will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the spirit and scope of the invention, and such modifications and adaptations are intended to be comprehended within the scope of the invention.
Claims (8)
1. A supersonic shock boundary layer interference-oriented SST turbulence model correction method is characterized by comprising the following steps:
solving a control equation of turbulent transportation variables in the SST turbulent model to obtain turbulent energySpecific dissipation ratio->And turbulent motion viscosity->；
By using turbulent energyAnd turbulent motion viscosity->Calculating the effective specific dissipation ratio->；
By using anisotropic componentsTime mean strain rate tensor->Calculate the corrected turbulence movement viscosity +.>；
Using modified turbulence movement viscosityTurbulent energy->Calculation of correctionsIs +.>And using the modified effective specific dissipation ratio +.>Sum of specific dissipation ratio->Calculate correction factor->；
Calculating a pressure gradientAnd according to the density->Speed->And dynamic viscosity->Normalizing it to obtain normalized pressure gradient +.>；
By combining several correction coefficientsSeveral normalized pressure gradients +.>Fitting the data to obtain a standardized pressure gradientAnd correction coefficient->A relation between them;
normalized pressure gradient to be obtainedCarrying-in relation to obtain correction factor->The method comprises the steps of carrying out a first treatment on the surface of the By means of correction factors->Correction limiter Bradshaw constant +.>For calculating turbulence movement viscosity->。
2. The method for modifying an SST turbulence model for supersonic shock boundary layer interference according to claim 1, wherein the method comprises the following steps:
using the formula
;
;
;
Calculating turbulence energySpecific dissipation ratio->And turbulent motion viscosity->；
In the above equation
;
；
；
；
;
;
;
;
;
;
Wherein,is a partial derivative operation symbol->For time (I)>For density (I)>For speed->For Kronecker symbol, subscriptAnd->For the spatial dimension index, x is the coordinate axis, +.>Is momentum viscosity->，/>For exercise viscosity +.>Is of vortex size>Is rotation rate tensor +.>For object plane distance->Viscosity for turbulent momentum->，/>Is a natural base number, a 1 Is a Bradshaw constant; sigma (sigma) k 、σ ω 、σ ω2 β, β are constant parameters.
3. The method for modifying an SST turbulence model for boundary layer disturbance of a supersonic shock wave according to claim 1, wherein the method is characterized by using a formula
;
Calculating an effective specific dissipation ratio, whereinFor an effective specific dissipation ratio->For turbulent motion, add>Is a turbulent motion viscosity.
4. The method for modifying an SST turbulence model for boundary layer disturbance of a supersonic shock wave according to claim 1, wherein the modified turbulence motion viscosity is calculatedThe method of (1) comprises:
high-credibility Reynolds stress calculation method based on direct numerical simulation or large vortex simulation methodAnd turbulent energy calculationAnisotropic component->The formula is:
;
wherein,for the opposite component->Reynolds stress for high confidence +.>For turbulent motion, add>Is a Kronecker symbol;
calculating a time-averaged strain rate tensor from the RANS velocity fieldThe formula is as follows:
;
wherein,is the time-averaged strain rate tensor, +.>Is a partial derivative operation symbol->For speed, x is the coordinate axis, subscript +.>And->Index for spatial dimension;
turbulence motion viscosity corrected by least square inverse calculationThe formula is as follows:
;
wherein,viscosity for modified turbulent motion.
5. The method for modifying an SST turbulence model for supersonic shock boundary layer interference according to claim 1, wherein the method comprises the following steps:
using the formula
;
The modified effective specific dissipation ratio is calculated, wherein,for a modified effective specific dissipation ratio +.>For modified turbulence movement viscosity +.>Is turbulent energy;
using the formula
;
Calculating a correction factor, wherein,for correction factor +.>For an effective specific dissipation ratio->For a modified effective specific dissipation ratio.
6. The method for modifying an SST turbulence model for supersonic shock boundary layer interference according to claim 1, wherein the method comprises the following steps:
the RANS solver coupled to the SST turbulence model calculates the pressure gradient as:
;
;
wherein,for pressure gradient +.>Is a partial derivative operation symbol, p is pressure, < ->The velocity vector is the velocity vector, x, y and z are the space coordinate axes, and u, v and w are the velocities in the x, y and z axes respectively;
the pressure gradient is normalized, and the formula is:
;
wherein,for normalizing the pressure gradient, +.>For density (I)>Is momentum viscous.
7. The method for modifying an SST turbulence model for supersonic shock boundary layer interference according to claim 1, wherein the relation between the normalized pressure gradient and the modification coefficient is:
;
;
wherein,for correction factor +.>To normalize the pressure gradient.
8. An SST turbulence model correction system for supersonic shock boundary layer interference, configured to implement the SST turbulence model correction method for supersonic shock boundary layer interference described in any one of claims 1 to 7, and characterized by comprising:
the control equation solving module is used for solving a control equation of a turbulent flow transportation variable in the SST turbulent flow model to obtain turbulent flow energySpecific dissipation ratio->And turbulent motion viscosity->；
An effective specific dissipation ratio acquisition module for utilizing turbulent energyAnd turbulent motion viscosity->Calculating the effective specific dissipation ratio->；
Turbulence motion viscosity correction module for utilizing anisotropic componentsTime mean strain rate tensor->Calculate the corrected turbulence movement viscosity +.>；
Correction coefficient acquisition module for using corrected turbulence motion viscosityTurbulent energy->Calculating the modified effective specific dissipation ratio +.>And using the modified effective specific dissipation ratio +.>Sum of specific dissipation ratio->Calculate correction factor->；
Pressure gradient normalization module for calculating pressure gradientAnd according to the density->Speed->And dynamic viscosity->Normalizing it to obtain normalized pressure gradient +.>；
A data fitting module for fitting a plurality of correction coefficientsSeveral normalized pressure gradients +.>Fitting the data to obtain normalized pressure gradient +.>And correction coefficient->A relation between them;
the constant correction module is used for correcting the constant,normalized pressure gradient for takingCarrying-in relation to obtain correction factor->The method comprises the steps of carrying out a first treatment on the surface of the And uses correction coefficient->Correction limiter Bradshaw constant +.>For calculating turbulence movement viscosity->。
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