CN108197388A - A kind of acquisition methods and system of high-speed aircraft flow transition characteristic - Google Patents
A kind of acquisition methods and system of high-speed aircraft flow transition characteristic Download PDFInfo
- Publication number
- CN108197388A CN108197388A CN201810002292.0A CN201810002292A CN108197388A CN 108197388 A CN108197388 A CN 108197388A CN 201810002292 A CN201810002292 A CN 201810002292A CN 108197388 A CN108197388 A CN 108197388A
- Authority
- CN
- China
- Prior art keywords
- speed aircraft
- parameter
- speed
- aircraft
- transition
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The present invention provides a kind of acquisition methods and system of high-speed aircraft flow transition characteristic, including：The full scale model of the high-speed aircraft is established, according to the formal parameter of the full scale model, obtains the corresponding Bestgrid of the full scale model；Obtain the incoming parameter of the high-speed aircraft and the boundary condition parameter of the high-speed aircraft；According to the Bestgrid, the incoming parameter and the boundary condition parameter, the surface boundary layer flow transition of the high-speed aircraft is simulated by the symbol king Transition model based on Reynolds average, and pass through the separation flow transition that Reynolds average large eddy simulation mixed method simulates the high-speed aircraft, obtain the high-speed aircraft turn twist starting point and the transition range length of the high-speed aircraft.The present invention can be successfully applied to the simulation of the supreme ultrasonic aircraft flow transition of subsonic speed, and numerical precision is higher, as a result reliably.
Description
Technical field
The present invention relates to high speed high-speed aircraft technical field, more particularly, to a kind of high-speed aircraft flow transition
The acquisition methods and system of characteristic.
Background technology
Laminar flow has great influence to the transition of turbulent flow for the design of high-speed aircraft.Due to the wall in transition range
Face friction can increased dramatically with the coefficient of heat conduction, and the value in even higher than complete turbulent area postpones high-speed aircraft surface-boundary
Laminar flow turn, which is twisted, to substantially reduce fuel consumption, and the selection for also making thermally protective materials is more flexible.
And to promote to turn to twist generation in the design of high-speed aircraft engine, if at engine inlets entrance flowing
In laminar condition, then easily generate separate bubble and influence gas entrapment, engine is resulted even in when serious to be started, air
In combustion chamber, residence time is only millisecond magnitude, and the efficiency of combustion under turbulence state greatly improves when will be with respect to laminar flow.
In recent years, direct Numerical (DNS), large eddy simulation (LES) and perturbation equation throw physico-chemical process (PSE), in height
The role of performer's ever more important in the numerical simulation of fast boundary layer transition.Nevertheless, from engineering reality, based on Reynolds
Average (RANS) turn to twist-turbulent model method appoint it is so most effective.
The firm hair is grown up based on Turbulence Modeling Theory, wherein adding the transition letter by modelling
Breath.Transition model calculating cycle is short, has become research hotspot in recent years.Particularly, it can describe to turn to twist the later stage well
Nonlinear processes.The symbol proposed at present-king's Transition model has been successfully applied to subsonic speed to hypersonic boundary layer transition mould
Formula.
Traditional RANS methods can relatively accurately predict the high-speed aircraft surface-boundary laminar flow of no separation.So
And rudder clearance, heat-proof tile gap and the positions such as engine inlets and combustion chamber of true high-speed aircraft will appear tool
The separation for having apparent unsteady characteristic is flowed, and RANS simulations cannot be guaranteed enough precision.Detach the error of flow transition prediction
Also the precision of prediction that boundary layer flow turn is twisted can be influenced.
It is limited by development of computer is horizontal, the LES methods with degree of precision can not be applied to high speed high-speed flight
The simulation of device Complex Flows.In fact, RANS is particularly suited for the simulation of near-wall region, because only needing at this time vertical to wall surface
The network in direction is encrypted and keeps very thick network in wall surface parallel direction, so as to greatly reduce total network number
Amount.In order to which the advantages of RANS and LES is combined, Reynolds average-large eddy simulation (RANS-LES) mixed method is suggested simultaneously
It is successfully used for various complicated low speeds flows.
Nevertheless, mixed method is confined to complete turbulent flow calculating at present, flow at high speed transition can not be applied to
Simulation.
Invention content
The present invention provides a kind of a kind of high-speed aircraft for overcoming the above problem or solving the above problems at least partly
The acquisition methods and system of flow transition characteristic.
According to an aspect of the present invention, a kind of acquisition methods of high-speed aircraft flow transition characteristic are provided, including：
The full scale model of the high-speed aircraft is established, according to the formal parameter of the full scale model, described in acquisition
The corresponding Bestgrid of full scale model；
Obtain the incoming parameter of the high-speed aircraft and the boundary condition parameter of the high-speed aircraft；
According to the Bestgrid, the incoming parameter and the boundary condition parameter, by the symbol based on Reynolds average-
King's Transition model simulates the surface boundary layer flow transition of the high-speed aircraft, and passes through Reynolds average-large eddy simulation mixing
Method simulates the separation flow transition of the high-speed aircraft, obtain the high-speed aircraft turn twist starting point and the high speed
The transition range length of aircraft.
Preferably, the formal parameter according to the full scale model, it is corresponding optimal to obtain the full scale model
Grid specifically includes：
According to the formal parameter of the full scale model, initial mesh is obtained；
By Reynolds average algorithm, subregion, the structure of the initial mesh and the subregion are carried out to the initial mesh
Docking；
The initial mesh is optimized, obtains the corresponding Bestgrid of the full scale model, the Bestgrid
Suitable for the calculating requirement of Reynolds average-large eddy simulation mixed method.
Preferably, the incoming parameter of the high-speed aircraft includes：The incoming parameter of spout, the free stream Mach number of spout,
The temperature of incoming flow of spout and the incoming angle of attack parameter of spout；The boundary condition parameter of the high-speed aircraft includes：The high speed
The air intake duct parameter of the wall surface temperature of aircraft, the wall roughness of the high-speed aircraft and the high-speed aircraft.
Preferably, the high-speed aircraft turns to twist starting point and be:The intermittency factor phase of the high-speed aircraft lower surface
10% position is increased for laminar region or, the friction coefficient on the high-speed aircraft surface increases by 10% relative to laminar region
Position；The transition range length of the high-speed aircraft twists starting point to complete turbulent area to turn.
According to another aspect of the present invention, a kind of acquisition system of high-speed aircraft flow transition characteristic is provided, including：
Mesh module, for establishing the full scale model of the high-speed aircraft, according to the shape of the full scale model
Parameter obtains the corresponding Bestgrid of the full scale model；
Incoming boundary module, for obtaining the perimeter strip of the incoming parameter of the high-speed aircraft and the high-speed aircraft
Part parameter；
Turn to twist module, for according to the grid, the incoming parameter and the boundary condition parameter, by being based on Reynolds
Average symbol-king's Transition model simulates the surface boundary layer flow transition of the high-speed aircraft, and passes through Reynolds average-big whirlpool
Simulate the separation flow transition that mixed method simulates the high-speed aircraft, obtain the high-speed aircraft turn to twist starting point and
The transition range length of the high-speed aircraft.
Preferably, the network module specifically includes：
Initial mesh unit for the formal parameter according to the full scale model, obtains initial mesh；
For passing through Reynolds average algorithm, subregion, the knot of the initial mesh are carried out to the initial mesh for zoning unit
Structure is docked with the subregion；
Optimize unit, for being optimized to the initial mesh, obtain the corresponding Bestgrid of the full scale model,
The Bestgrid is suitable for the calculating requirement of Reynolds average-large eddy simulation mixed method.
Preferably, the incoming parameter of the high-speed aircraft includes：The incoming parameter of spout, the free stream Mach number of spout,
The temperature of incoming flow of spout and the incoming angle of attack parameter of spout；The boundary condition parameter of the high-speed aircraft includes：The high speed
The air intake duct parameter of the wall surface temperature of aircraft, the wall roughness of the high-speed aircraft and the high-speed aircraft.
Preferably, the high-speed aircraft turns to twist starting point and be:The intermittency factor phase of the high-speed aircraft lower surface
10% position is increased for laminar region or, the friction coefficient on the high-speed aircraft surface increases by 10% relative to laminar region
Position；The transition range length of the high-speed aircraft is：Turn to twist starting point the distance between to complete turbulent area.
In accordance with a further aspect of the present invention, it is proposed that a kind of to be set for obtaining the electronics of high-speed aircraft flow transition characteristic
It is standby, including：
At least one processor；And
At least one processor being connect with the processor communication, wherein：
The memory is stored with the program instruction that can be performed by the processor, and the processor calls described program to refer to
Enable the acquisition methods for being able to carry out a kind of above-mentioned high-speed aircraft flow transition characteristic.
According to another aspect of the invention, a kind of non-transient computer readable storage medium storing program for executing, the non-transient calculating are provided
Machine readable storage medium storing program for executing stores computer instruction, and the computer instruction makes the computer perform a kind of above-mentioned high-speed aircraft
The acquisition methods of flow transition characteristic.
The present invention proposes a kind of acquisition methods and system of high-speed aircraft flow transition characteristic, according to high-speed aircraft
Formal parameter carries out grid generation and piecemeal, the flight parameter of high-speed aircraft and boundary condition parameter is obtained, using based on thunder
The average symbol of promise-king's Transition model simulation high-speed aircraft surface boundary layer flow transition, is using Reynolds average-large eddy simulation
Mixed method simulated flight device detaches flow transition, can be successfully applied to the supreme ultrasonic aircraft flow transition of subsonic speed
Simulation, numerical precision is higher, as a result reliably.
Description of the drawings
Fig. 1 is a kind of acquisition methods of high-speed aircraft flow transition characteristic of the embodiment of the present invention；
Fig. 2 is a kind of structure diagram of the acquisition system of high-speed aircraft flow transition characteristic in the embodiment of the present invention.
Specific embodiment
With reference to the accompanying drawings and examples, the specific embodiment of the present invention is described in further detail.Implement below
Example is used to illustrate the present invention, but be not limited to the scope of the present invention.
Fig. 1 is a kind of acquisition methods of high-speed aircraft flow transition characteristic of the embodiment of the present invention, including：
S1, the full scale model for establishing the high-speed aircraft according to the formal parameter of the full scale model, obtain institute
State the corresponding Bestgrid of full scale model；
Specifically, the efficiency of the levels of precision of numerical result and calculating process is influenced right and wrong by mesh quality
It is often big.When only when the generation of grid and solving the algorithm good match in flow field, it can just succeed and efficiently calculate knot
Fruit.
The boundary condition parameter of S2, the incoming parameter for obtaining the high-speed aircraft and the high-speed aircraft；
Specifically, the incoming parameter of high-speed aircraft includes：The incoming parameter of spout, the free stream Mach number of spout, spout
Temperature of incoming flow and spout incoming angle of attack parameter；The boundary condition parameter of high-speed aircraft includes：The wall surface of high-speed aircraft
The air intake duct parameter of temperature, the wall roughness of high-speed aircraft and high-speed aircraft.Certainly according to actual needs, incoming parameter
Other specific parameters are may also include, the embodiment of the present invention does not do specific restriction.
S3, according to the Bestgrid, the incoming parameter and the boundary condition parameter, by based on Reynolds average
Symbol-king's Transition model simulates the surface boundary layer flow transition of the high-speed aircraft, and passes through Reynolds average-large eddy simulation and mix
Conjunction method simulates the separation flow transition of the high-speed aircraft, obtain the high-speed aircraft turn twist starting point and the height
The transition range length of fast aircraft.
Specifically, the surface boundary layer of the high-speed aircraft is simulated by the symbol based on Reynolds average-king's Transition model
Flow transition, and pass through the separation flow transition that Reynolds average-large eddy simulation mixed method simulates the high-speed aircraft.
Numerical computations are based on Unsteady Flow Calculation software UNITS, which is based on compressible limited bulk Reynolds average
N-S equations, including folk prescription journey S-A, a variety of common turbulent models, symbol-king's Transition model and the base such as two equation k-w, k-w-SST
In Reynolds average-large eddy simulation (RANS-LES) mixed method of a variety of turbulent models.Convective term is discrete to be had based on three ranks
The Roe forms of MUSCL, five rank WENO interpolation, symmetric TVD scheme and quadravalence based on six rank centered differences and five rank WENO
Cell centered scheme, viscosity term is discrete to use Second-Order Central Difference.Time stepping method is the second order LU-SGS methods of belt iteration, is included into
A variety of boundary conditions such as outlet, far field, wall surface and period, have the characteristics of Large-scale parallel computing.
Symbol-king's Transition model is by three transport equations about intermittency factor γ, pulse energy k and its unit dissipative shock wave ω
Composition.It pulses in coefficient of virtual viscosity (eddy stress in other words) using intermittency factor γ as turbulence pulsation part and non-turbulent flow
Partial weight, to realize the simulation to transition.Further, γ starts the position increased (corresponding to for turning to twist in flow field
Beginning position) by the function F in γ equation source itemsonsetIt determines, and FonsetValue again depend on k (non-turbulent flow pulsatile portion) peace
The development degree flowed.The pattern is suitable for the simulation of the supreme ultrasonic aircraft surface boundary layer transition of subsonic speed.Its
It is mainly characterized by：
(1), the physical mechanism of boundary layer transition process is considered in detail, rationally reflects and master is risen to low speed boundary layer transition
Lead the influence of the first mode and the second mode to play a leading role to hypersonic boundary layer transition of effect.
(2), turbulent area is being gone to completely, pattern is reduced to the SST turbulent models of general prevalence.
(3), it is convenient to be applied to existing CFD software based on Reynolds average method, it, can suitable for Large-scale parallel computing
It is combined with Reynolds average-large eddy simulation mixed method, fine analog Complex Phenomena in Vertical Bell Jar.
Calculating Reynolds average-large eddy simulation mixed method is direct Numerical method, and this method is only needed original
The change of very little is done on the basis of Reynolds average turbulent model, define and is used simply, to the adaptable of complex appearance, this year
To have obtained rapid development and be widely applied.This method is filtered by mesh scale, and different zonings is using different
Model, interface is typically dynamic change, and basic thought is that small scale is simulated with Reynolds average near wall
Turbulent flow, Diverging area use similar Smagorinsky Asias Gree stress model.
Output aircraft turn twist starting point and transition range length parameter.
The numerical value that high-speed aircraft flow transition characteristic is completed using Tecplot the poster processing softs obtains.
Turn twist starting point be high-speed aircraft lower surface intermittency factor relative to laminar region increase by 10% position or
Person, the friction coefficient on high-speed aircraft surface increase by 10% position relative to laminar region, and complete turbulent area refers to high-speed flight
The intermittency factor of the lower surface of device is equal to 1 or the friction coefficient on high-speed aircraft surface reaches maximum value.Since the present invention is implemented
Example using Reynolds average-large eddy simulation mixed method parsed at lower surface turn twist flowing near the unit that sets out, so as to catch
Grasped high-speed aircraft turn twist characteristic.
On the basis of above-described embodiment, as in a preferred embodiment, according to the formal parameter of full scale model, obtain
The corresponding Bestgrid of the full scale model, specifically includes：
According to the formal parameter of the full scale model, initial mesh is obtained；
By Reynolds average algorithm, subregion, the structure of the initial mesh and the subregion are carried out to the initial mesh
Docking；
The initial mesh is optimized, obtains the corresponding Bestgrid of the full scale model, the Bestgrid
Suitable for the calculating requirement of Reynolds average-large eddy simulation mixed method.
It is suitable for the subregion docking structure grid of Reynolds average calculating according to the generation of the formal parameter of high-speed aircraft first,
Namely the structure of initial mesh will be docked with subregion, and initial mesh also has following characteristic：Wall surface grid is in fit premise
Under ensure orthogonality as possible, precursor compressing surface, inlet lip, in boundary layer and region that local flow changes greatly carry out
Mesh refinement simultaneously smoothly transits.
The grid of local calculation is optimized later, Bestgrid is obtained after optimization, Bestgrid disclosure satisfy that Reynolds
The calculating requirement of average-large eddy simulation mixed method.
An embodiment of the present invention provides the specific acquisition methods of Bestgrid, by carrying out subregion, optimization to initial mesh,
So that the Bestgrid finally obtained meets the calculating requirement of Reynolds average-large eddy simulation mixed method, to utilize base below
In the symbol-king's Transition model simulation high-speed aircraft of Reynolds average surface boundary layer flow transition and utilize Reynolds average-big
The separation flow transition that whirlpool simulation mixed method simulates the high-speed aircraft provides guarantee.
Fig. 2 is a kind of structure diagram of the acquisition system of high-speed aircraft flow transition characteristic in the embodiment of the present invention,
As shown in Fig. 2, the system includes mesh module, incoming boundary module and turns to twist module.Wherein：
Mesh module is used to establish the full scale model of the high-speed aircraft, according to the outer parameter of the full scale model
Number, obtains the corresponding Bestgrid of the full scale model；
Incoming boundary module is used to obtain the incoming parameter of the high-speed aircraft and the perimeter strip of the high-speed aircraft
Part parameter；
Turn to twist module for according to the grid, the incoming parameter and the boundary condition parameter, by being based on Reynolds
Average symbol-king's Transition model simulates the surface boundary layer flow transition of the high-speed aircraft, and passes through Reynolds average-big whirlpool
Simulate the separation flow transition that mixed method simulates the high-speed aircraft, obtain the high-speed aircraft turn to twist starting point and
The transition range length of the high-speed aircraft.
The specific implementation procedure of this system embodiment is identical with the implementation procedure of above method embodiment, and detailed process please join
The implementation procedure for stating embodiment of the method is admitted to, details are not described herein.
On the basis of above-described embodiment, it is preferable that the network module specifically includes：
Initial mesh unit for the formal parameter according to the full scale model, obtains initial mesh；
For passing through Reynolds average algorithm, subregion, the knot of the initial mesh are carried out to the initial mesh for zoning unit
Structure is docked with the subregion；
Optimize unit, for being optimized to the initial mesh, obtain the corresponding Bestgrid of the full scale model,
The Bestgrid is suitable for the calculating requirement of Reynolds average-large eddy simulation mixed method.
On the basis of above-described embodiment, it is preferable that the incoming parameter of the high-speed aircraft includes：The incoming ginseng of spout
The incoming angle of attack parameter of number, the free stream Mach number of spout, the temperature of incoming flow of spout and spout；The perimeter strip of the high-speed aircraft
Part parameter includes：The wall surface temperature of the high-speed aircraft, the wall roughness of the high-speed aircraft and the high-speed flight
The air intake duct parameter of device.
On the basis of above-described embodiment, it is preferable that the high-speed aircraft turns to twist starting point and be:The high-speed flight
The intermittency factor of device lower surface increases by 10% position or, the friction coefficient on the high-speed aircraft surface relative to laminar region
Increase by 10% position relative to laminar region；The transition range length of the high-speed aircraft is：Turn to twist starting point to complete turbulent flow
The distance between area.
The present invention proposes a kind of acquisition system of high-speed aircraft flow transition characteristic, according to the outer parameter of high-speed aircraft
Number carries out grid generation and piecemeal, the flight parameter of high-speed aircraft and boundary condition parameter is obtained, using based on Reynolds average
Symbol-king's Transition model simulation high-speed aircraft surface boundary layer flow transition, using Reynolds average-large eddy simulation mixing side
Method simulated flight device detaches flow transition, can be successfully applied to the mould of the supreme ultrasonic aircraft flow transition of subsonic speed
Intend, numerical precision is higher, as a result reliably.
The embodiment of the present invention discloses a kind of computer program product, and the computer program product includes being stored in non-transient
Computer program on computer readable storage medium, the computer program include program instruction, when described program instructs quilt
When computer performs, computer is able to carry out the method that above-mentioned each method embodiment is provided, such as including：Establish the high speed
According to the formal parameter of the full scale model, it is corresponding optimal to obtain the full scale model for the full scale model of aircraft
Grid；Obtain the incoming parameter of the high-speed aircraft and the boundary condition parameter of the high-speed aircraft；According to described optimal
Grid, the incoming parameter and the boundary condition parameter simulate the height by the symbol based on Reynolds average-king's Transition model
The surface boundary layer flow transition of fast aircraft, and pass through Reynolds average-large eddy simulation mixed method and simulate the high-speed flight
The separation flow transition of device, obtain the high-speed aircraft turn twist starting point and the transition range length of the high-speed aircraft.
The embodiment of the present invention provides a kind of non-transient computer readable storage medium storing program for executing, the non-transient computer readable storage
Medium storing computer instructs, and the computer instruction makes the computer perform the side that above-mentioned each method embodiment is provided
Method, such as including：The full scale model of the high-speed aircraft is established, according to the formal parameter of the full scale model, is obtained
The corresponding Bestgrid of the full scale model；Obtain the incoming parameter of the high-speed aircraft and the side of the high-speed aircraft
Boundary's conditional parameter；According to the Bestgrid, the incoming parameter and the boundary condition parameter, by based on Reynolds average
Symbol-king's Transition model simulates the surface boundary layer flow transition of the high-speed aircraft, and passes through Reynolds average-large eddy simulation and mix
Conjunction method simulates the separation flow transition of the high-speed aircraft, obtain the high-speed aircraft turn twist starting point and the height
The transition range length of fast aircraft.
One of ordinary skill in the art will appreciate that：Realizing all or part of step of above method embodiment can pass through
The relevant hardware of program instruction is completed, and aforementioned program can be stored in a computer read/write memory medium, the program
When being executed, step including the steps of the foregoing method embodiments is performed；And aforementioned storage medium includes：ROM, RAM, magnetic disc or light
The various media that can store program code such as disk.
Finally, method of the invention is only preferable embodiment, is not intended to limit the scope of the present invention.It is all
Within the spirit and principles in the present invention, any modification, equivalent replacement, improvement and so on should be included in the protection of the present invention
Within the scope of.
Claims (10)
1. a kind of acquisition methods of high-speed aircraft flow transition characteristic, which is characterized in that including：
The full scale model of the high-speed aircraft is established, according to the formal parameter of the full scale model, obtains the full ruler
The corresponding Bestgrid of very little model；
Obtain the incoming parameter of the high-speed aircraft and the boundary condition parameter of the high-speed aircraft；
According to the Bestgrid, the incoming parameter and the boundary condition parameter, turned by symbol-king based on Reynolds average
The surface boundary layer flow transition of high-speed aircraft described in pattern simulation is twisted, and passes through Reynolds average-large eddy simulation mixed method
Simulate the separation flow transition of the high-speed aircraft, obtain the high-speed aircraft turn twist starting point and the high-speed flight
The transition range length of device.
2. method according to claim 1, which is characterized in that the formal parameter according to the full scale model obtains
The corresponding Bestgrid of the full scale model, specifically includes：
According to the formal parameter of the full scale model, initial mesh is obtained；
By Reynolds average algorithm, subregion is carried out to the initial mesh, the structure of the initial mesh is docked with the subregion；
The initial mesh is optimized, obtains the corresponding Bestgrid of the full scale model, the Bestgrid is applicable in
In the calculating requirement of Reynolds average-large eddy simulation mixed method.
3. method according to claim 1, which is characterized in that the incoming parameter of the high-speed aircraft includes：Spout comes
Flow the incoming angle of attack parameter of parameter, the free stream Mach number of spout, the temperature of incoming flow of spout and spout；The side of the high-speed aircraft
Boundary's conditional parameter includes：The wall surface temperature of the high-speed aircraft, the wall roughness of the high-speed aircraft and the high speed
The air intake duct parameter of aircraft.
4. method according to claim 1, which is characterized in that the high-speed aircraft turns to twist starting point and be:The high speed
The intermittency factor of aircraft lower surface increases the friction of 10% position or, the high-speed aircraft surface relative to laminar region
Coefficient increases by 10% position relative to laminar region；The transition range length of the high-speed aircraft twists starting point to complete rapids to turn
Flow area.
5. a kind of acquisition system of high-speed aircraft flow transition characteristic, which is characterized in that including：
Mesh module, for establishing the full scale model of the high-speed aircraft, according to the formal parameter of the full scale model,
Obtain the corresponding Bestgrid of the full scale model；
Incoming boundary module, for obtaining the boundary condition of the incoming parameter of the high-speed aircraft and high-speed aircraft ginseng
Number；
Turn to twist module, for according to the grid, the incoming parameter and the boundary condition parameter, by being based on Reynolds average
Symbol-king's Transition model simulate the surface boundary layer flow transition of the high-speed aircraft, and pass through Reynolds average-large eddy simulation
Mixed method simulates the separation flow transition of the high-speed aircraft, and obtain the high-speed aircraft turns to twist starting point and described
The transition range length of high-speed aircraft.
6. system according to claim 5, which is characterized in that the network module specifically includes：
Initial mesh unit for the formal parameter according to the full scale model, obtains initial mesh；
Zoning unit, for passing through Reynolds average algorithm, to the initial mesh carry out subregion, the structure of the initial mesh with
The subregion docking；
Optimize unit, for being optimized to the initial mesh, obtain the corresponding Bestgrid of the full scale model, it is described
Bestgrid is suitable for the calculating requirement of Reynolds average-large eddy simulation mixed method.
7. system according to claim 5, which is characterized in that the incoming parameter of the high-speed aircraft includes：Spout comes
Flow the incoming angle of attack parameter of parameter, the free stream Mach number of spout, the temperature of incoming flow of spout and spout；The side of the high-speed aircraft
Boundary's conditional parameter includes：The wall surface temperature of the high-speed aircraft, the wall roughness of the high-speed aircraft and the high speed
The air intake duct parameter of aircraft.
8. system according to claim 5, which is characterized in that the high-speed aircraft turns to twist starting point and be:The high speed
The intermittency factor of aircraft lower surface increases the friction of 10% position or, the high-speed aircraft surface relative to laminar region
Coefficient increases by 10% position relative to laminar region；The transition range length of the high-speed aircraft is：Turn to twist starting point to complete
The distance between turbulent area.
9. a kind of electronic equipment for being used to obtain high-speed aircraft flow transition characteristic, which is characterized in that including：
At least one processor；And
At least one processor being connect with the processor communication, wherein：
The memory is stored with the program instruction that can be performed by the processor, and the processor calls described program instruction energy
It is enough to perform such as any the method for Claims 1-4.
10. a kind of non-transient computer readable storage medium storing program for executing, which is characterized in that the non-transient computer readable storage medium storing program for executing is deposited
Computer instruction is stored up, the computer instruction makes the computer perform such as any the method for Claims 1-4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810002292.0A CN108197388B (en) | 2018-01-02 | 2018-01-02 | A kind of acquisition methods and system of high-speed aircraft flow transition characteristic |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810002292.0A CN108197388B (en) | 2018-01-02 | 2018-01-02 | A kind of acquisition methods and system of high-speed aircraft flow transition characteristic |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108197388A true CN108197388A (en) | 2018-06-22 |
| CN108197388B CN108197388B (en) | 2019-04-05 |
Family
ID=62588193
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810002292.0A Active CN108197388B (en) | 2018-01-02 | 2018-01-02 | A kind of acquisition methods and system of high-speed aircraft flow transition characteristic |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108197388B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109033525A (en) * | 2018-06-27 | 2018-12-18 | 浙江大学 | A kind of hypersonic transition prediction method based on simplified three equation transition models |
| CN109583067A (en) * | 2018-11-22 | 2019-04-05 | 北京空天技术研究所 | High-speed aircraft based on equalized temperature turns to twist position measurement sensor design method |
| CN110702356A (en) * | 2019-10-12 | 2020-01-17 | 空气动力学国家重点实验室 | Hypersonic velocity transition prediction method considering surface roughness effect |
| CN112052632A (en) * | 2020-07-27 | 2020-12-08 | 空气动力学国家重点实验室 | Hypersonic flow direction transition prediction method |
| CN113127976A (en) * | 2021-04-23 | 2021-07-16 | 中南大学 | Wide-speed-domain boundary layer separation induced transition prediction method, device, equipment and medium |
| CN113505542A (en) * | 2021-06-11 | 2021-10-15 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for constructing turbulence transition model of backswept wing of hypersonic aircraft |
| CN115879231A (en) * | 2023-02-24 | 2023-03-31 | 北京卓鸷科技有限责任公司 | Method and device for acquiring flow transition information of micro aircraft |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9275645B2 (en) * | 2014-04-22 | 2016-03-01 | Droneshield, Llc | Drone detection and classification methods and apparatus |
| CN107103117A (en) * | 2017-03-27 | 2017-08-29 | 北京临近空间飞行器系统工程研究所 | A kind of thermal environment design method in hypersonic aircraft control flaps gap |
-
2018
- 2018-01-02 CN CN201810002292.0A patent/CN108197388B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9275645B2 (en) * | 2014-04-22 | 2016-03-01 | Droneshield, Llc | Drone detection and classification methods and apparatus |
| CN107103117A (en) * | 2017-03-27 | 2017-08-29 | 北京临近空间飞行器系统工程研究所 | A kind of thermal environment design method in hypersonic aircraft control flaps gap |
Non-Patent Citations (2)
| Title |
|---|
| SONG FU 等: "RANS modeling of high-speed aerodynamic flow transition with consideration of stability theory", 《PROGRESS IN AEROSPACE SCIENCES》 * |
| 符松 等: "基于雷诺平均方法的高超音速边界层转扳模拟", 《中国科学》 * |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109033525A (en) * | 2018-06-27 | 2018-12-18 | 浙江大学 | A kind of hypersonic transition prediction method based on simplified three equation transition models |
| CN109033525B (en) * | 2018-06-27 | 2022-08-30 | 浙江大学 | Hypersonic transition prediction method based on simplified three-equation transition model |
| CN109583067A (en) * | 2018-11-22 | 2019-04-05 | 北京空天技术研究所 | High-speed aircraft based on equalized temperature turns to twist position measurement sensor design method |
| CN109583067B (en) * | 2018-11-22 | 2020-04-07 | 北京空天技术研究所 | Design method of high-speed aircraft transition position measurement sensor based on temperature balance |
| CN110702356B (en) * | 2019-10-12 | 2021-06-08 | 空气动力学国家重点实验室 | Hypersonic velocity transition prediction method considering surface roughness effect |
| CN110702356A (en) * | 2019-10-12 | 2020-01-17 | 空气动力学国家重点实验室 | Hypersonic velocity transition prediction method considering surface roughness effect |
| CN112052632B (en) * | 2020-07-27 | 2021-05-11 | 空气动力学国家重点实验室 | Hypersonic flow direction transition prediction method |
| CN112052632A (en) * | 2020-07-27 | 2020-12-08 | 空气动力学国家重点实验室 | Hypersonic flow direction transition prediction method |
| CN113127976A (en) * | 2021-04-23 | 2021-07-16 | 中南大学 | Wide-speed-domain boundary layer separation induced transition prediction method, device, equipment and medium |
| CN113127976B (en) * | 2021-04-23 | 2022-06-21 | 中南大学 | Boundary layer separation induction transition prediction method, device, equipment and medium |
| CN113505542A (en) * | 2021-06-11 | 2021-10-15 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for constructing turbulence transition model of backswept wing of hypersonic aircraft |
| CN113505542B (en) * | 2021-06-11 | 2023-03-21 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for constructing turbulence transition model of backswept wing of hypersonic aircraft |
| CN115879231A (en) * | 2023-02-24 | 2023-03-31 | 北京卓鸷科技有限责任公司 | Method and device for acquiring flow transition information of micro aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108197388B (en) | 2019-04-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108197388B (en) | A kind of acquisition methods and system of high-speed aircraft flow transition characteristic | |
| Kawai et al. | Wall-modeling in large eddy simulation: Length scales, grid resolution, and accuracy | |
| Wang et al. | Dynamics of attached turbulent cavitating flows | |
| Jameson et al. | Some recent developments in numerical methods for transonic flows | |
| Wang et al. | Numerical investigation of unsteady cloud cavitating flow around the Clark-Y hydrofoil with adaptive mesh refinement using OpenFOAM | |
| CN112069689B (en) | Simulation method and system for fuel atomization characteristic of aircraft engine | |
| CN108009383A (en) | A kind of definite method and system of Natural Laminar Flow nacelle shape | |
| CN111859529B (en) | Multi-grid disturbance domain updating acceleration method for aircraft streaming numerical simulation | |
| Vieira et al. | CFD hover predictions including boundary-layer transition | |
| CN113609598A (en) | RANS/LES disturbance domain updating method for aircraft aerodynamic characteristic simulation | |
| Huang et al. | Simulation of cavitating flow around a 2-D hydrofoil | |
| Péron et al. | An immersed boundary method for preliminary design aerodynamic studies of complex configurations | |
| Solntsev et al. | CABARET on rotating meshes | |
| CN115879231B (en) | Method and device for acquiring flow transition information of micro aircraft | |
| Rodriguez et al. | Formulation and implementation of inflow/outflow boundary conditions to simulate propulsive effects | |
| Wen et al. | Optimal design of an autonomous underwater helicopter's shape based on combinatorial optimization strategy | |
| Wang et al. | Dynamics analysis of underwater glider based on fluid-multibody coupling model | |
| Knapke et al. | Detailed unsteady simulation of a counterrotating aspirated compressor with a focus on the aspiration slot and plenum | |
| Kawai et al. | A dynamic wall model for large-eddy simulation of high Reynolds number compressible flows | |
| Veldman | Quasi-simultaneous viscous-inviscid interaction for transonic airfoil flow | |
| Noelting et al. | The lattice-Boltzmann method: An alternative to LES for complex aerodynamic and aeroacoustic simulations in the aerospace industry | |
| Arif et al. | Design and optimization of bump (compression surface) for diverterless supersonic inlet | |
| Arnone | Viscous analysis of three-dimensional rotor flows using a multigrid method | |
| Prabhakar et al. | Application of CFD Simulation in the Design of a Parabolic Winglet on NACA 2412 | |
| Shah et al. | CFD Analysis and Experimental Validation of an Unmanned Aerial Vehicle. |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |