CN114154441A - Method for generating and simulating and calculating environmental turbulence field of aircraft - Google Patents

Method for generating and simulating and calculating environmental turbulence field of aircraft Download PDF

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CN114154441A
CN114154441A CN202210123994.0A CN202210123994A CN114154441A CN 114154441 A CN114154441 A CN 114154441A CN 202210123994 A CN202210123994 A CN 202210123994A CN 114154441 A CN114154441 A CN 114154441A
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aircraft
turbulence
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velocity
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CN114154441B (en
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胡伟波
万兵兵
董康生
涂国华
陈坚强
袁先旭
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Computational Aerodynamics Institute of China Aerodynamics Research and Development Center
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Abstract

The invention discloses a method for generating and simulating an environmental turbulence field of an aircraft, which relates to the field of computational fluid dynamics and comprises the following steps: obtaining a set random three-dimensional speed disturbance field, and then obtaining a transient speed disturbance field; superposing the transient speed disturbance field to a preset average flow field to obtain a physical turbulence speed field, and obtaining a turbulence inlet boundary condition based on the physical turbulence speed field; finishing the boundary condition setting and initial condition setting of an aircraft calculation domain based on the aircraft inflow information and the boundary condition of a turbulence inlet, and dividing grids of the aircraft calculation domain; performing simulation calculation on the environment flow field of the aircraft based on the grid information, the boundary condition setting information and the initial condition setting information; the invention can reduce the size of the calculation domain, cancel the auxiliary calculation domain and save the calculation time and cost; eliminating low-frequency uncertain disturbance which may be introduced to obtain more real turbulence; and reducing modifications to the source code to quickly and efficiently obtain desired turbulent entry conditions.

Description

Method for generating and simulating and calculating environmental turbulence field of aircraft
Technical Field
The invention relates to the field of computational fluid dynamics, in particular to a method for generating and simulating an environmental turbulence field of an aircraft.
Background
Turbulence is a turbulent flow state, and is one of the unsolved problems in the third century and is also an important flow characteristic which must be considered in the development and design of modern aircrafts due to the characteristics of complexity, nonlinearity, three-dimensionality, dynamics, randomness and the like. High-precision numerical simulation based on a computational fluid dynamics method is one of important means for researching turbulence and also is an important means for disclosing the flow field phenomenon related to the turbulence and the basic problems such as the generation and evolution mechanism thereof.
The main methods of high-precision numerical simulation include large eddy simulation and direct numerical simulation. When the method is used for researching the turbulence related problems, a flow field calculation domain and corresponding boundary conditions need to be set, wherein the boundary conditions of the turbulence inlet which accord with the physical law are set, and the method is crucial to the calculation accuracy and the effectiveness of simulation. At present, three main inlet turbulence generation methods suitable for large vortex simulation and direct numerical simulation are provided: natural evolution, scale transformation and cyclic methods. The natural development method needs to set a super-large calculation domain, then a laminar boundary condition is applied at an inlet, and the gradual transition evolution of the laminar flow into the turbulent flow is waited. Because the high-density grid is needed for the large vortex simulation and the direct numerical simulation, the calculation amount is huge, and the calculation amount is multiplied by an oversized calculation domain, so that the method has no operability in actual calculation and cannot be really applied. The scale transformation method needs to add an auxiliary computing domain, apply periodic conditions in the independent auxiliary computing domain to enable turbulence to naturally develop, extract obtained data after obtaining mature turbulence, and apply the data to the inlet of the main computing domain. This approach greatly reduces the length of the computation domain, however, since it still requires an auxiliary computation domain to implement, the time and computation costs are still high; and because the two simulations are independent of each other, the effect of the downstream of the main computation domain on the inlet turbulence conditions is not considered. The circular method is a derivative method of the scale transformation method, and the method selects a part of the upstream of the main calculation domain as an auxiliary calculation domain, and reapplies the outlet data of the auxiliary calculation domain to the inlet through the scale transformation, so as to obtain the proper turbulence condition. However, this method introduces low-frequency uncertain disturbance, which is not suitable for studying the low-frequency phenomenon of the flow field. Meanwhile, the method needs special setting for the calculation domain, and the modification amount of the program is large.
Disclosure of Invention
The invention provides a method for generating and simulating an environmental turbulence field of an aircraft, aiming at reducing the size of a calculation domain, canceling an auxiliary calculation domain and saving calculation time and cost; eliminating low-frequency uncertain disturbance which may be introduced to obtain more real turbulence; and reducing modifications to the source code to quickly and efficiently obtain desired turbulent entry conditions.
In order to achieve the above object, the present invention provides a method for generating and simulating an aircraft environmental turbulence field, the method comprising:
step 1: obtaining a turbulence entrance boundary condition of an aircraft computational domain;
step 2: finishing the boundary condition setting and initial condition setting of an aircraft calculation domain based on the aircraft inflow information and the turbulence inlet boundary condition, and dividing the grids of the aircraft calculation domain;
and step 3: performing simulation calculation on an environment flow field of the aircraft based on the grid information of the aircraft calculation domain, the boundary condition setting information and the initial condition setting information of the aircraft calculation domain;
wherein, the step 1 specifically comprises:
step 1.1: obtaining the set random three-dimensional speed disturbance field;
step 1.2: obtaining a transient speed disturbance field based on the set random three-dimensional speed disturbance field;
step 1.3: and superposing the transient speed disturbance field to a preset average flow field to obtain a physical turbulence speed field, and obtaining a turbulence entrance boundary condition of an aircraft calculation domain based on the physical turbulence speed field.
The principle of the invention is as follows: the method comprises the steps of enabling a flow field to meet an average flow condition and a two-point spatial correlation condition through a set random three-dimensional velocity disturbance field, enabling the flow field to meet a two-point temporal correlation condition through a transformation coefficient, introducing general reference Reynolds stress, enabling a transient velocity disturbance field to meet single-point correlation and second-order statistics, ensuring that the generated turbulent flow field meets the average flow condition, time and spatial scales, first-order and second-order statistics of a physical turbulent flow field through comprehensive application of calculation steps, and ensuring the calculation efficiency while ensuring the precision because the process is simple and easy to operate and is an independent calculation process without setting an additional calculation domain or changing an original core calculation code.
Preferably, the step 1.2 specifically includes:
obtaining a conversion coefficient based on the set random three-dimensional speed disturbance field;
and obtaining the transient speed disturbance field based on the conversion coefficient and the universal reference Reynolds stress.
Preferably, the step 1.1 specifically includes:
defining a discrete filter function
Figure 972729DEST_PATH_IMAGE001
N is a positive integer, and a random three-dimensional speed disturbance field is set
Figure 296394DEST_PATH_IMAGE002
Expressed as:
Figure 607290DEST_PATH_IMAGE003
Figure 268078DEST_PATH_IMAGE004
is a random number sequence with a total number of m,
Figure 738243DEST_PATH_IMAGE005
is and
Figure 826284DEST_PATH_IMAGE006
the corresponding random number coefficients, k and l are integers, k =1, 2, 3, … ….
Preferably, a random number sequence
Figure 499842DEST_PATH_IMAGE007
Has a mean of 0 and a variance of 1. The design can meet the two-point correlation condition, and the relation is the necessary characteristic of a real turbulent flow field.
Preferably, the first and second liquid crystal materials are,
Figure 964322DEST_PATH_IMAGE008
the calculation method is as follows:
Figure 898780DEST_PATH_IMAGE009
wherein, the intermediate amount
Figure 157723DEST_PATH_IMAGE010
The calculation method is as follows:
Figure 567844DEST_PATH_IMAGE011
wherein the content of the first and second substances,
Figure 570435DEST_PATH_IMAGE012
is composed of
Figure 500345DEST_PATH_IMAGE013
Time of flight
Figure 195769DEST_PATH_IMAGE010
The square of the square,
Figure 968553DEST_PATH_IMAGE014
is a spatial signature parameter.
Preferably, the first and second liquid crystal materials are,
Figure 633889DEST_PATH_IMAGE015
the conversion coefficient is calculated in the following way:
Figure 542939DEST_PATH_IMAGE017
wherein the nth time step is divided into
Figure 143685DEST_PATH_IMAGE018
The set random three-dimensional velocity perturbation field of (2) is recorded as
Figure 138186DEST_PATH_IMAGE019
N-1 time step
Figure 623525DEST_PATH_IMAGE020
The set random three-dimensional velocity perturbation field of (2) is recorded as
Figure 387082DEST_PATH_IMAGE021
，
Figure 424308DEST_PATH_IMAGE022
In order to be a step of time,
Figure 765159DEST_PATH_IMAGE023
is a time stamp parameter.
Preferably, the transient speed disturbance field is calculated by:
Figure 913244DEST_PATH_IMAGE025
wherein the content of the first and second substances,
Figure 796886DEST_PATH_IMAGE026
、
Figure 880380DEST_PATH_IMAGE027
and
Figure 583894DEST_PATH_IMAGE028
velocity components in three directions of coordinate axes in the transient velocity disturbance field,
Figure 270090DEST_PATH_IMAGE029
，
Figure 8239DEST_PATH_IMAGE030
，
Figure 783340DEST_PATH_IMAGE031
，
Figure 974150DEST_PATH_IMAGE032
，
Figure 464037DEST_PATH_IMAGE033
is a common reference reynolds stress;
Figure 666479DEST_PATH_IMAGE034
、
Figure 216409DEST_PATH_IMAGE035
and
Figure 894515DEST_PATH_IMAGE036
the conversion coefficients in the three directions x, y and z, respectively.
Preferably, the calculation method for obtaining the physical turbulent flow velocity field by superimposing the transient velocity disturbance field on the preset average flow field is as follows:
Figure 188093DEST_PATH_IMAGE038
wherein the content of the first and second substances,
Figure 759889DEST_PATH_IMAGE039
、
Figure 480720DEST_PATH_IMAGE040
and
Figure 646123DEST_PATH_IMAGE041
velocity components in three directions of coordinate axes in the physical turbulence velocity field,
Figure 353179DEST_PATH_IMAGE042
average velocity components in three directions of coordinate axes in the preset average flow field are obtained.
Preferably, the aircraft incoming flow information includes: velocity, temperature, and pressure of the incoming environment of the aircraft.
Preferably, the method further comprises step 4:
and 3, calculating to obtain flow field parameters of the aircraft around any point in the flow field based on the simulation calculation result in the step 3, and calculating to obtain performance parameters of the aircraft based on the flow field parameters.
One or more technical schemes provided by the invention at least have the following technical effects or advantages:
the method does not need an additional auxiliary calculation domain, and reduces the complexity and the calculation cost of the simulation calculation of the environmental flow field of the aircraft;
the method considers the influence of downstream flow on the upstream inlet turbulent flow field, and the obtained turbulent flow field is more real, so that the simulation calculation of the environmental flow field of the aircraft is more accurate;
the method does not introduce low-frequency uncertain interference, and the obtained turbulent flow field is more reasonable, so that the simulation calculation of the environmental flow field of the aircraft is more accurate;
the method has high turbulent flow development speed, can obtain mature turbulent flow within a small flow direction length range, and can reduce the cost and the calculation amount of the simulation calculation of the environmental flow field of the aircraft.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention;
FIG. 1 is a schematic flow diagram of a method of ambient turbulence field generation and simulation calculation for an aircraft;
FIG. 2 is a schematic diagram of a comparison of turbulence calculation domain sizes for a natural evolution method and the present method;
FIG. 3 is a velocity profile verification plot;
FIG. 4 is a verification plot of Reynolds stress profile curves.
Detailed Description
In order that the above objects, features and advantages of the present invention can be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings. It should be noted that the embodiments of the present invention and features of the embodiments may be combined with each other without conflicting with each other.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those specifically described and thus the scope of the present invention is not limited by the specific embodiments disclosed below.
Example one
Referring to fig. 1, fig. 1 is a schematic flow chart of a method for generating and simulating an aircraft environmental turbulence field, the method for generating and simulating an aircraft environmental turbulence field according to the present invention includes:
step 1: obtaining a turbulence entrance boundary condition of an aircraft computational domain;
step 2: finishing the boundary condition setting and initial condition setting of an aircraft calculation domain based on the aircraft inflow information and the turbulence inlet boundary condition, and dividing the grids of the aircraft calculation domain;
and step 3: performing simulation calculation on an environment flow field of the aircraft based on the grid information of the aircraft calculation domain, the boundary condition setting information and the initial condition setting information of the aircraft calculation domain;
wherein, the step 1 specifically comprises:
step 1.1: obtaining a set random three-dimensional speed perturbation field;
step 1.2: obtaining a transient speed disturbance field based on the set random three-dimensional speed disturbance field;
step 1.3: and superposing the transient speed disturbance field to a preset average flow field to obtain a physical turbulence speed field, and obtaining a turbulence entrance boundary condition of an aircraft calculation domain based on the physical turbulence speed field.
In the present embodiment, the boundary condition of the turbulence inlet does not include three sub-steps, and a three-dimensional velocity disturbance field is obtained and satisfies the two-point correlation condition; secondly, converting the obtained set three-dimensional speed disturbance field into a real transient speed disturbance field, and enabling the real transient speed disturbance field to meet the cross-correlation condition; and finally, superposing the obtained transient speed disturbance field on a specified average flow field to obtain the synthesized physical turbulence. Wherein the two-point correlation and cross-correlation characteristics are the necessary characteristics of a real turbulent flow field.
The specific technical scheme is as follows:
obtaining a set random three-dimensional velocity perturbation field:
for simplicity of explanation, a one-dimensional physical problem is taken as an example for explanation. First, a discrete filter function is defined
Figure 920426DEST_PATH_IMAGE001
(N is a positive integer), then a random perturbation field can be expressed as:
Figure 546579DEST_PATH_IMAGE003
（1）
wherein the content of the first and second substances,
Figure 199278DEST_PATH_IMAGE004
is a series of random numbers with a total number m,
Figure 959292DEST_PATH_IMAGE005
are the corresponding random number coefficients (k and l are integers, where k =1, 2, 3, … …). In order to satisfy the two-point correlation condition, a random number sequence
Figure 381046DEST_PATH_IMAGE007
The conditions of mean 0 and variance 1 are satisfied. The random number coefficient may be obtained by the following equation:
Figure 443680DEST_PATH_IMAGE009
（2）
wherein, the intermediate amount
Figure 193461DEST_PATH_IMAGE010
Calculated from the following formula:
Figure 632533DEST_PATH_IMAGE011
Figure 908794DEST_PATH_IMAGE012
is composed of
Figure 142329DEST_PATH_IMAGE013
Time of flight
Figure 628674DEST_PATH_IMAGE010
The square of the square,
Figure 605857DEST_PATH_IMAGE014
random numbers for the spatial signature parameters, equal to the ratio of the inertial measure to the grid size
Figure 2203DEST_PATH_IMAGE043
Mersennetwist can be used (for a specific method, see Matsumoto M, Nishimura T. Mersene twister: a 623-dimensional equivalent irregular uniform pseudo-random number generator [ J)]ACM transformations on Modeling and Computer Simulation, 1998, 8(1): 3-30.) method, using equation (1) to obtain the assumed three-dimensional velocity perturbation field, and dividing the nth time step into
Figure 282006DEST_PATH_IMAGE018
The three-dimensional velocity disturbance field is marked as
Figure 396593DEST_PATH_IMAGE019
。
Obtaining a real transient speed disturbance field:
first, the conversion coefficient is obtained
Figure 911888DEST_PATH_IMAGE015
：
Figure 287374DEST_PATH_IMAGE044
（3）
Wherein the content of the first and second substances,
Figure 862712DEST_PATH_IMAGE022
in order to be a step of time,
Figure 199015DEST_PATH_IMAGE023
is a time-stamp parameter equal to the ratio of the inertial scale to the velocity of the main flow. Thereby realizing a real three-dimensional transient speed disturbance field
Figure 518001DEST_PATH_IMAGE045
Comprises the following steps:
Figure 498727DEST_PATH_IMAGE046
(4)
wherein the content of the first and second substances,
Figure 510545DEST_PATH_IMAGE029
，
Figure 68565DEST_PATH_IMAGE030
，
Figure 315876DEST_PATH_IMAGE031
，
Figure 541321DEST_PATH_IMAGE047
，
Figure 599407DEST_PATH_IMAGE033
this data is derived from any existing turbulence field reference data for a given universal reference reynolds stress.
And (3) superposing to obtain a complete physical turbulence velocity field:
Figure 910302DEST_PATH_IMAGE048
wherein the content of the first and second substances,
Figure 836670DEST_PATH_IMAGE049
the velocity components in three directions of the coordinate axes,
Figure 775676DEST_PATH_IMAGE042
the average velocity components for the three directions can be obtained by integrating the boundary layer equation.
Obtaining performance parameters of the aircraft:
after the inlet boundary condition of the aircraft computational domain is obtained, other boundary conditions and initial conditions of the computational domain are set according to the speed, temperature and pressure of the inflow environment of the aircraft, grids of the computational domain are divided, and then the environmental flow field of the aircraft can be simulated and calculated by using a large vortex simulation or direct numerical simulation method (Pope S B. turboflow [ M ]. Cambridge University Press, 2000.), so that flow field parameters of the aircraft around any point in the flow field, such as pressure, density, speed and the like, are obtained, and further performance parameters of the aircraft, such as lift force, resistance and the like, can be obtained through simple calculation.
Example two
Referring to fig. 2, fig. 2 is a schematic diagram illustrating a comparison between sizes of turbulence calculation domains of a natural development method and a method, where 1 in fig. 2 is a turbulence calculation domain corresponding to the natural development method, and 2 in fig. 2 is a turbulence calculation domain corresponding to the method, and it can be seen from fig. 2 that the size of the calculation domain of the method is significantly smaller than that of the turbulence calculation domain corresponding to the natural development method.
The method comprises the following specific implementation steps:
the following description will be given by taking a flat plate example as an example of performing high-precision simulation by using a large vortex simulation method. The main flow parameters of the initial flow field are: reynolds number
Figure 394876DEST_PATH_IMAGE050
Mach number of
Figure 927489DEST_PATH_IMAGE051
Stagnation pressure
Figure 267334DEST_PATH_IMAGE052
Stagnation temperature
Figure 936213DEST_PATH_IMAGE053
The inlet boundary layer has a thickness of
Figure 726315DEST_PATH_IMAGE054
。
Determining the size of the calculation domain of the example, the length of the calculation domain flowing to the x direction is
Figure 870857DEST_PATH_IMAGE055
The y-direction perpendicular to the plate is calculated as the field length
Figure 873448DEST_PATH_IMAGE056
The span-wise z-direction calculated field length is
Figure 662413DEST_PATH_IMAGE057
(ii) a Carrying out grid division on the calculation domain to obtain the grid sizes of the wall surfaces in three directions x, y and z
Figure 357836DEST_PATH_IMAGE058
。
Obtaining average parameters of the flow field at the inlet according to the main flow parameters and the boundary layer equation, wherein the average parameters comprise average speed
Figure 474828DEST_PATH_IMAGE059
Mean temperature of
Figure 546689DEST_PATH_IMAGE060
And mean pressure
Figure 455739DEST_PATH_IMAGE061
。
Determining a three-dimensional random number field according to the Mersennetwist method
Figure 276776DEST_PATH_IMAGE062
(ii) a According to the formula:
Figure 271277DEST_PATH_IMAGE009
Figure 615670DEST_PATH_IMAGE011
determining corresponding coefficients
Figure 520173DEST_PATH_IMAGE063
Wherein is
Figure 291819DEST_PATH_IMAGE064
The ratio of the inertia scale of the corresponding direction to the grid size, the inertia scale is the characteristic scale of the flow field, and the thickness of the boundary layer can be taken
Figure 773616DEST_PATH_IMAGE065
Then, then
Figure 311914DEST_PATH_IMAGE066
. And calculating the vertical wall surface and the expansion direction and the like.
Obtaining a disturbance field of a set speed
Figure 523452DEST_PATH_IMAGE067
：
Figure 731580DEST_PATH_IMAGE069
Wherein the content of the first and second substances,
Figure 435094DEST_PATH_IMAGE070
is arbitrarily greater than
Figure DEST_PATH_IMAGE071
The number of the integer (c) of (d),
Figure 527815DEST_PATH_IMAGE072
is arbitrarily greater than
Figure 265963DEST_PATH_IMAGE073
The number of the integer (c) of (d),
Figure 379413DEST_PATH_IMAGE074
is arbitrarily greater than
Figure DEST_PATH_IMAGE075
Is an integer of (1).
Calculating the conversion coefficient according to
Figure 226015DEST_PATH_IMAGE076
：
Figure 715902DEST_PATH_IMAGE078
Wherein the content of the first and second substances,
Figure 183924DEST_PATH_IMAGE022
which represents a step of time in size,
Figure 733854DEST_PATH_IMAGE018
represents the value of the n-th step,
Figure 411960DEST_PATH_IMAGE023
is the inertia scale and the main flow velocity
Figure 830172DEST_PATH_IMAGE079
The inertia scale is the characteristic scale of the flow field, and the thickness of the boundary layer can be taken
Figure 277334DEST_PATH_IMAGE065
Then, then
Figure DEST_PATH_IMAGE080
。
Calculating a turbulent velocity disturbance field according with a physical law:
Figure 404690DEST_PATH_IMAGE081
wherein the content of the first and second substances,
Figure 757042DEST_PATH_IMAGE029
，
Figure 854311DEST_PATH_IMAGE030
，
Figure 31346DEST_PATH_IMAGE031
，
Figure 188658DEST_PATH_IMAGE047
,
Figure 841356DEST_PATH_IMAGE033
this data is derived from any existing turbulence field reference data for a given universal reference reynolds stress.
And (3) superposing to obtain a final turbulent flow field:
Figure 601371DEST_PATH_IMAGE082
obtaining performance parameters of the aircraft:
after the inlet boundary condition of the aircraft computational domain is obtained, other boundary conditions and initial conditions of the computational domain are set according to the speed, temperature and pressure of the inflow environment of the aircraft, grids of the computational domain are divided, and then the environmental flow field of the aircraft can be simulated and calculated by using a large vortex simulation or direct numerical simulation method, so that flow field parameters of the aircraft at any point in the flow field, such as pressure, density, speed and the like, can be obtained, and further performance parameters of the aircraft, such as lift force, resistance and the like, can be obtained through simple calculation.
Referring to fig. 3-4, fig. 3 is a velocity profile verification diagram, from fig. 3, it can be seen that the velocity profile obtained by the method is almost identical to the reference verification data and theoretical value, fig. 4 is a reynolds stress profile verification diagram, from fig. 4, it can be seen that the reynolds stress profile obtained by the method is basically consistent with the reference verification data, and the frequency selection techniques in fig. 3 and fig. 4 are the methods of the present invention.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.

Claims (10)

1. A method of ambient turbulence field generation and simulation calculation for an aircraft, the method comprising:
step 1: obtaining a turbulence entrance boundary condition of an aircraft computational domain;
step 2: finishing the boundary condition setting and initial condition setting of an aircraft calculation domain based on the aircraft inflow information and the turbulence inlet boundary condition, and dividing the grids of the aircraft calculation domain;
and step 3: performing simulation calculation on an environment flow field of the aircraft based on the grid information of the aircraft calculation domain, the boundary condition setting information and the initial condition setting information of the aircraft calculation domain;
wherein, the step 1 specifically comprises:
step 1.1: obtaining a set random three-dimensional speed perturbation field;
step 1.2: obtaining a transient speed disturbance field based on the set random three-dimensional speed disturbance field;
step 1.3: and superposing the transient speed disturbance field to a preset average flow field to obtain a physical turbulence speed field, and obtaining a turbulence entrance boundary condition of an aircraft calculation domain based on the physical turbulence speed field.
2. The aircraft environmental turbulence field generation and simulation calculation method according to claim 1, wherein the step 1.2 specifically comprises:
obtaining a conversion coefficient based on the set random three-dimensional speed disturbance field;
and obtaining the transient speed disturbance field based on the conversion coefficient and the universal reference Reynolds stress.
3. The aircraft environmental turbulence field generation and simulation calculation method according to claim 2, wherein the step 1.1 specifically comprises:
defining a discrete filter function
Figure DEST_PATH_IMAGE001
N is a positive integer, and a random three-dimensional speed disturbance field is set
Figure 794155DEST_PATH_IMAGE002
Expressed as:
Figure DEST_PATH_IMAGE003
Figure 242454DEST_PATH_IMAGE004
is a random number sequence with a total number of m,
Figure DEST_PATH_IMAGE005
is and
Figure 818929DEST_PATH_IMAGE006
the corresponding random number coefficients, k and l are integers, k =1, 2, 3, … ….
4. The method of claim 3, wherein the method comprises generating and simulating an aircraft environmental turbulence fieldSequence of random numbers
Figure DEST_PATH_IMAGE007
Has a mean of 0 and a variance of 1.
5. The aircraft environmental turbulence field generation and simulation calculation method of claim 3,
Figure 745297DEST_PATH_IMAGE008
the calculation method is as follows:
Figure DEST_PATH_IMAGE009
wherein, the intermediate amount
Figure 356407DEST_PATH_IMAGE010
The calculation method is as follows:
Figure DEST_PATH_IMAGE011
wherein the content of the first and second substances,
Figure 710028DEST_PATH_IMAGE012
is composed of
Figure DEST_PATH_IMAGE013
Time of flight
Figure 773799DEST_PATH_IMAGE010
The square of the square,
Figure 238278DEST_PATH_IMAGE014
is a spatial signature parameter.
6. The aircraft environmental turbulence field generation and simulation calculation method of claim 3,
Figure DEST_PATH_IMAGE015
the conversion coefficient is calculated in the following way:
Figure 703894DEST_PATH_IMAGE016
wherein the nth time step is divided into
Figure DEST_PATH_IMAGE017
The set random three-dimensional velocity perturbation field of (2) is recorded as
Figure 228417DEST_PATH_IMAGE018
N-1 time step
Figure DEST_PATH_IMAGE019
The set random three-dimensional velocity perturbation field of (2) is recorded as
Figure 779484DEST_PATH_IMAGE020
，
Figure DEST_PATH_IMAGE021
In order to be a step of time,
Figure 47654DEST_PATH_IMAGE022
is a time stamp parameter.
7. The method of claim 6, wherein the transient velocity disturbance field is calculated by:
Figure DEST_PATH_IMAGE023
wherein the content of the first and second substances,
Figure 367777DEST_PATH_IMAGE024
、
Figure DEST_PATH_IMAGE025
and
Figure 328780DEST_PATH_IMAGE026
velocity components in three directions of coordinate axes in the transient velocity disturbance field,
Figure DEST_PATH_IMAGE027
，
Figure 101564DEST_PATH_IMAGE028
，
Figure DEST_PATH_IMAGE029
，
Figure 173425DEST_PATH_IMAGE030
，
Figure DEST_PATH_IMAGE031
is a common reference reynolds stress;
Figure 613633DEST_PATH_IMAGE032
、
Figure DEST_PATH_IMAGE033
and
Figure 479958DEST_PATH_IMAGE034
the conversion coefficients in the three directions x, y and z, respectively.
8. The method according to claim 7, wherein the calculation of the physical turbulent velocity field obtained by superimposing the transient velocity disturbance field on the preset average flow field is performed by:
Figure DEST_PATH_IMAGE035
wherein the content of the first and second substances,
Figure 740038DEST_PATH_IMAGE036
、
Figure DEST_PATH_IMAGE037
and
Figure 350011DEST_PATH_IMAGE038
velocity components in three directions of coordinate axes in the physical turbulence velocity field,
Figure DEST_PATH_IMAGE039
average velocity components in three directions of coordinate axes in the preset average flow field are obtained.
9. The method of claim 1, wherein the aircraft inflow information comprises: velocity, temperature, and pressure of the incoming environment of the aircraft.
10. The aircraft environmental turbulence field generation and simulation calculation method of claim 1, further comprising the step of 4:
and 3, calculating to obtain flow field parameters of the aircraft around any point in the flow field based on the simulation calculation result in the step 3, and calculating to obtain performance parameters of the aircraft based on the flow field parameters.
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114330035A (en) * 2022-03-09 2022-04-12 中国空气动力研究与发展中心计算空气动力研究所 High-speed aircraft aerodynamic performance evaluation method
CN116412991A (en) * 2023-06-12 2023-07-11 中国空气动力研究与发展中心高速空气动力研究所 Method for synchronously simulating flying height and flying speed in wind tunnel flow field test

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5233865A (en) * 1991-04-24 1993-08-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Probe systems for measuring static pressure and turbulence intensity in fluid streams
CN103020398A (en) * 2012-12-31 2013-04-03 中国人民解放军国防科学技术大学 Turbulent inlet generation method used for numerical simulation
CN104239640A (en) * 2014-09-18 2014-12-24 中国人民解放军国防科学技术大学 Generation method of turbulence entry condition by incompressible-flow large-eddy simulation
CN110598362A (en) * 2019-09-30 2019-12-20 西安交通大学 Method for generating boundary condition of large-vortex simulation calculation speed under condition of fully developing turbulence
CN112765736A (en) * 2021-04-12 2021-05-07 中国空气动力研究与发展中心计算空气动力研究所 Method for setting boundary of turbulent kinetic energy inlet of hypersonic-velocity blunt leading edge around flow

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5233865A (en) * 1991-04-24 1993-08-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Probe systems for measuring static pressure and turbulence intensity in fluid streams
CN103020398A (en) * 2012-12-31 2013-04-03 中国人民解放军国防科学技术大学 Turbulent inlet generation method used for numerical simulation
CN104239640A (en) * 2014-09-18 2014-12-24 中国人民解放军国防科学技术大学 Generation method of turbulence entry condition by incompressible-flow large-eddy simulation
CN110598362A (en) * 2019-09-30 2019-12-20 西安交通大学 Method for generating boundary condition of large-vortex simulation calculation speed under condition of fully developing turbulence
CN112765736A (en) * 2021-04-12 2021-05-07 中国空气动力研究与发展中心计算空气动力研究所 Method for setting boundary of turbulent kinetic energy inlet of hypersonic-velocity blunt leading edge around flow

Non-Patent Citations (5)

* Cited by examiner, † Cited by third party
Title
TU GUOHUA等: "SA and SST turbulence models for hypersonic forced boundary layer transition", 《ACTA AERODYNAUTICA ET ASTRONAUTICA SINICA》 *
沈文达等: "激光等离子体波纹临界面的共振吸收和二次谐波产生", 《物理学报》 *
蔡晓春等: "飞机尾喷流的速度场及浓度场数值模拟", 《微计算机信息》 *
逯学志等: "湍流入流条件在强迫转捩研究中的应用", 《空气动力学学报》 *
陈坚强等: "高超声速边界层转捩研究现状与发展趋势", 《空气动力学学报》 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114330035A (en) * 2022-03-09 2022-04-12 中国空气动力研究与发展中心计算空气动力研究所 High-speed aircraft aerodynamic performance evaluation method
CN114330035B (en) * 2022-03-09 2022-05-24 中国空气动力研究与发展中心计算空气动力研究所 High-speed aircraft aerodynamic performance evaluation method
CN116412991A (en) * 2023-06-12 2023-07-11 中国空气动力研究与发展中心高速空气动力研究所 Method for synchronously simulating flying height and flying speed in wind tunnel flow field test
CN116412991B (en) * 2023-06-12 2023-08-22 中国空气动力研究与发展中心高速空气动力研究所 Method for synchronously simulating flying height and flying speed in wind tunnel flow field test

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