CN109871586A - Aerodynamic interference numerical value suitable for co-axial rotor ground effect determines method and system - Google Patents
Aerodynamic interference numerical value suitable for co-axial rotor ground effect determines method and system Download PDFInfo
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Abstract
The present invention discloses a kind of aerodynamic interference numerical value suitable for co-axial rotor ground effect and determines method and system.Method includes: to obtain rotor parameter；Coaxial double-rotary wing geometrical model is established according to rotor parameter；Select area of space as computational domain according to geometrical model, area of space includes geometrical model；Discrete to the computational domain progress comprising coaxial double-rotary wing, division obtains calculating grid；With the true information of flow for the grid position that the information of flow in the grid of division replaces dividing；Determine boundary condition；Determine the initial value in the coaxial double-rotary wing flow field of ground proximity；It is calculated according to the initial value in the coaxial double-rotary wing flow field of the calculating grid, boundary condition and ground proximity of division, determines that information of flow, the information of flow include speed, density, pressure and the interior energy of air-flow.The flow field characteristic under coaxial double-rotary wing ground effect can be accurately analyzed through the invention.
Description
Technical field
The present invention relates to helicopter fields, more particularly to a kind of aerodynamic interference number suitable for co-axial rotor ground effect
It is worth and determines method and system.
Background technique
Helicopter has the function of that other aircraft such as steadily hovering, VTOL and nap of the earth flight are difficult to realize, because
This all has broad application prospects in terms of civil and military.In helicopter VTOL and nap of the earth flight, ground faces rotor
Performance generation significantly affect very much, keep power it is constant under conditions of, rotor generate pulling force with far from ground compared to obviously
Increase, this phenomenon is referred to as " ground effect " (IGE).Since the upper and lower rotor of coaxial double-rotary wing is there are spacing, lower rotor is big
Partial region is in the purling and tail whirlpool of upper rotor, and there are Complex Flows interference phenomenons in flow field.With conventional single rotor
It compares, the aerodynamic interference under the ground effect of DCB Specimen is more complicated, it is therefore desirable to further investigate.
Currently, less for the research of coaxial double-rotary wing ground effect both at home and abroad.2000, Kang etc. was with momentum source method
Simulate rotor stream field effect, by solve average Navier-Stokes equation obtain preceding winged cross-arranging type in ground effect, lap siding and
The flow location form of coaxial double-rotary wing.2015, Dreier was simulated the ground effect of coaxial double-rotary wing and is lured using Wake Model
Lead VELOCITY DISTRIBUTION.The same year, Qin Yanhua etc. calculate coaxial double-rotary wing flow field and induction under ground effect with free wake method
Speed.2017, Lu Taoye, which further studies the ground effect of coaxial double-rotary wing and parametrization, to be influenced.The above is about altogether
The research of axis DCB Specimen ground effect has great significance, but still not deep enough.About coaxial double-rotary wing ground effect
Research mostly uses momentum source method and free wake method etc., these methods can not consider the geometrical property of blade, and be unable to mould
Draw up the Flow details of rotor and Near Ground.
Summary of the invention
The object of the present invention is to provide a kind of aerodynamic interference numerical value suitable for co-axial rotor ground effect determine method and
System can accurately analyze the flow field characteristic under coaxial double-rotary wing ground effect.
To achieve the above object, the present invention provides following schemes:
A kind of aerodynamic interference numerical value suitable for co-axial rotor ground effect determines method, comprising:
Obtain rotor parameter；
Coaxial double-rotary wing geometrical model is established according to the rotor parameter；
Select area of space as computational domain according to the geometrical model, the area of space includes the geometrical model；
Discrete to the computational domain progress comprising the coaxial double-rotary wing, division obtains calculating grid；
The true information of flow of the grid position of the division is replaced with the information of flow in the calculating grid；
Determine boundary condition；
Determine the initial value in the coaxial double-rotary wing flow field of ground proximity；
It is carried out according to the initial value in the coaxial double-rotary wing flow field of the grid of the division, boundary condition and the ground proximity
It calculates, determines that information of flow, the information of flow include speed, density, pressure and the interior energy of air-flow.
Optionally, the described pair of computational domain comprising coaxial double-rotary wing carries out discrete, and division obtains calculating grid, specific to wrap
It includes:
It is discrete to the computational domain progress comprising coaxial double-rotary wing, obtain background grid；
Exercise testing is obtained to the return motion of background grid simulation DCB Specimen；
Local mesh reflnement is carried out to background grid rotor wake region and Near Ground using multiple grid method,
Obtain encrypted grid；
Judge whether the encrypted grid meets setting mesh quality requirement；
If so, carrying out flow field calculation calculating；
Select area of space as computational domain according to the geometrical model if it is not, returning, the area of space includes described
Geometrical model.
Optionally, the determining boundary condition, specifically includes:
When determining boundary condition, the ground below coaxial double-rotary wing determines boundary information using no slip boundary condition；
Far field boundary information is determined using one-dimensional Riemann invariant in addition to the ground below coaxial double-rotary wing.
Optionally, the coaxial double-rotary wing flow field according to the grid of the division, boundary condition and the ground proximity
Initial value calculated, determine aerodynamic interference numerical value, specifically include:
It is used according to the initial value in the coaxial double-rotary wing flow field of the grid of the division, boundary condition and the ground proximity
FormulaIt calculates, determines aerodynamic interference numerical value；
Wherein,W is conservation variable, FcFor without viscous flux, FvRespectively
For sticky flux, ρ is fluid density, and p is fluid pressure, and u, v, w is fluid velocity component, and E is energy, V in unit fluidrIt is phase
To speed；For the normal vector of control plane；qn,qbRespectively fluid velocity and mesh motion speed is along grid surface
The component of normal direction, τ, Φ are physical quantitys relevant to viscosity.
A kind of aerodynamic interference numerical value suitable for co-axial rotor ground effect determines method, comprising:
Module is obtained, for obtaining rotor parameter；
Model building module, for establishing coaxial double-rotary wing geometrical model according to the rotor parameter；
Area of space selecting module, for selecting area of space as computational domain, the space according to the geometrical model
Region includes the geometrical model；
Grid dividing module, discrete for carrying out to the computational domain comprising the coaxial double-rotary wing, division obtains calculating net
Lattice；
Flow field alternative module, for it is described calculating grid in information of flow replace the division grid position it is true
Real information of flow；
Boundary determining module, for determining boundary condition；
Initial value determining module, the initial value in the coaxial double-rotary wing flow field for determining ground proximity；
Aerodynamic interference numerical value determining module, for according to the grid of the division, boundary condition and the ground proximity
The initial value in coaxial double-rotary wing flow field is calculated, and determines information of flow, the information of flow include the speed of air-flow, density,
Pressure and interior energy.
Optionally, the grid dividing module, specifically includes:
Discrete unit, it is discrete for being carried out to the computational domain comprising coaxial double-rotary wing, obtain background grid；
Return motion unit obtains exercise testing for the return motion to background grid simulation DCB Specimen；
Encryption unit, for being carried out using multiple grid method to background grid rotor wake region and Near Ground
Local mesh reflnement obtains encrypted grid；
Judging unit, for judging whether the encrypted grid meets setting mesh quality requirement；
If so, carrying out flow field calculation calculating；
Select area of space as computational domain according to the geometrical model if it is not, returning, the area of space includes described
Geometrical model.
Optionally, the boundary determining module, specifically includes:
Boundary determination unit, for determining boundary condition, the ground below coaxial double-rotary wing is using no slip boundary condition
To determine boundary information；Determine that far field boundary is believed using one-dimensional Riemann invariant in addition to the ground below coaxial double-rotary wing
Breath.
Optionally, the aerodynamic interference numerical value determining module, specifically includes:
Aerodynamic interference numerical value determination unit, for according to the grid of the division, boundary condition and the ground proximity
The initial value in coaxial double-rotary wing flow field uses formulaIt calculates, determines aerodynamic interference number
Value；
Wherein,W is conservation variable, FcFor without viscous flux, FvPoint
Not Wei sticky flux, ρ is fluid density, and p is fluid pressure, u, v, and w is fluid velocity component, E be in unit fluid can, VrIt is
Relative velocity；For the normal vector of control plane；qn,qbRespectively fluid velocity and mesh motion speed is along grid
The component of face normal direction, τ, Φ are physical quantitys relevant to viscosity.
The specific embodiment provided according to the present invention, the invention discloses following technical effects: the present invention provides a kind of suitable
Aerodynamic interference numerical value for co-axial rotor ground effect determines method, comprising: obtains rotor parameter；It is established according to rotor parameter
Coaxial double-rotary wing geometrical model；Area of space is selected according to geometrical model, area of space includes geometrical model；To in area of space
Computational domain progress comprising coaxial double-rotary wing is discrete, obtains calculating grid；It is divided to grid is calculated, the net divided
Lattice, with the true information of flow for the grid position that the information of flow in the grid of division replaces dividing；Determine boundary condition；It determines
The initial value in the coaxial double-rotary wing flow field of ground proximity；According to the coaxial double-rotary of the grid of division, boundary condition and ground proximity
The initial value in wing flow field is calculated, and determines information of flow, and the information of flow includes the speed of air-flow, density, pressure and interior
Energy.The flow field characteristic under coaxial double-rotary wing ground effect can be accurately analyzed through the invention.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without any creative labor, can also be according to these attached drawings
Obtain other attached drawings.
Fig. 1 determines method flow diagram for the aerodynamic interference numerical value that the embodiment of the present invention is suitable for co-axial rotor ground effect；
Fig. 2 determines system construction drawing for the aerodynamic interference numerical value that the embodiment of the present invention is suitable for co-axial rotor ground effect；
Fig. 3 is coaxial double-rotary wing blade surface geometry model schematic；
Fig. 4 is coaxial double-rotary wing geometrical model schematic diagram；
Fig. 5 is the multi grid schematic diagram under coaxial double-rotary wing ground effect；
Fig. 6 is that the blade tip scrollwork under coaxial double-rotary wing ground effect plays schematic diagram；
Fig. 7 is the motion pattern under coaxial double-rotary wing ground effect.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The object of the present invention is to provide a kind of aerodynamic interference numerical value suitable for co-axial rotor ground effect determine method and
System can accurately analyze the flow field characteristic under coaxial double-rotary wing ground effect.
In order to make the foregoing objectives, features and advantages of the present invention clearer and more comprehensible, with reference to the accompanying drawing and specific real
Applying mode, the present invention is described in further detail.
Fig. 1 determines method flow diagram for the aerodynamic interference numerical value that the embodiment of the present invention is suitable for co-axial rotor ground effect.
As shown in Figure 1, a kind of aerodynamic interference numerical value suitable for co-axial rotor ground effect determines method, comprising:
Step 101: obtaining rotor parameter；
Step 102: coaxial double-rotary wing geometrical model is established according to the rotor parameter；
Step 103: selecting area of space as computational domain according to the geometrical model, the area of space includes described several
What model；
Step 104: discrete to the computational domain progress comprising the coaxial double-rotary wing, division obtains calculating grid；
Step 105: the true flow field letter of the grid position of the division is replaced with the information of flow in the calculating grid
Breath；
Step 106: determining boundary condition；
Step 107: determining the initial value in the coaxial double-rotary wing flow field of ground proximity；
Step 108: according to the first of the coaxial double-rotary wing flow field of the grid of the division, boundary condition and the ground proximity
Initial value is calculated, and determines that information of flow, the information of flow include speed, density, pressure and the interior energy of air-flow.
Step 104, it specifically includes:
It is discrete to the computational domain progress comprising coaxial double-rotary wing, obtain background grid；
Exercise testing is obtained to the return motion of background grid simulation DCB Specimen；
Local mesh reflnement is carried out to background grid rotor wake region and Near Ground using multiple grid method,
Obtain encrypted grid；
Judge whether the encrypted grid meets setting mesh quality requirement；
If so, carrying out flow field calculation calculating；
Select area of space as computational domain according to the geometrical model if it is not, returning, the area of space includes described
Geometrical model.
Step 106, it specifically includes:
When determining boundary condition, the ground below coaxial double-rotary wing determines boundary information using no slip boundary condition；
Far field boundary information is determined using one-dimensional Riemann invariant in addition to the ground below coaxial double-rotary wing.
Step 108, it specifically includes:
It is used according to the initial value in the coaxial double-rotary wing flow field of the grid of the division, boundary condition and the ground proximity
FormulaIt calculates, determines aerodynamic interference numerical value；
Wherein,W is conservation variable, FcFor without viscous flux, FvRespectively
For sticky flux, ρ is fluid density, and p is fluid pressure, and u, v, w is fluid velocity component, and E is energy, V in unit fluidrIt is phase
To speed；For the normal vector of control plane；qn,qbRespectively fluid velocity and mesh motion speed is along grid surface
The component of normal direction, τ, Φ are physical quantitys relevant to viscosity.
Fig. 2 determines system construction drawing one for the aerodynamic interference numerical value that the embodiment of the present invention is suitable for co-axial rotor ground effect
The aerodynamic interference numerical value that kind is suitable for co-axial rotor ground effect determines method, comprising:
Module 201 is obtained, for obtaining rotor parameter；
Model building module 202, for establishing coaxial double-rotary wing geometrical model according to the rotor parameter；
Area of space selecting module 203, for selecting area of space as computational domain, the sky according to the geometrical model
Between region include the geometrical model；
Grid dividing module 204, discrete for carrying out to the computational domain comprising the coaxial double-rotary wing, division is calculated
Grid；
Flow field alternative module 205, for replacing the grid position of the division with the information of flow in the calculating grid
True information of flow；
Boundary determining module 206, for determining boundary condition；
Initial value determining module 207, the initial value in the coaxial double-rotary wing flow field for determining ground proximity；
Aerodynamic interference numerical value determining module 208, for according to the grid of the division, boundary condition and the ground proximity
The initial value in coaxial double-rotary wing flow field calculated, determine information of flow, the information of flow includes the speed, close of air-flow
Degree, pressure and interior energy.
The grid dividing module 204, specifically includes:
Discrete unit, it is discrete for being carried out to the computational domain comprising coaxial double-rotary wing, obtain background grid；
Return motion unit obtains exercise testing for the return motion to background grid simulation DCB Specimen；
Encryption unit, for being carried out using multiple grid method to background grid rotor wake region and Near Ground
Local mesh reflnement obtains encrypted grid；
Judging unit, for judging whether the encrypted grid meets setting mesh quality requirement；
If so, carrying out flow field calculation calculating；
Select area of space as computational domain according to the geometrical model if it is not, returning, the area of space includes described
Geometrical model.
The boundary determining module 206, specifically includes:
Boundary determination unit, for determining boundary condition, the ground below coaxial double-rotary wing is using no slip boundary condition
To determine boundary information；Determine that far field boundary is believed using one-dimensional Riemann invariant in addition to the ground below coaxial double-rotary wing
Breath.
The aerodynamic interference numerical value determining module 208, specifically includes:
Aerodynamic interference numerical value determination unit, for according to the grid of the division, boundary condition and the ground proximity
The initial value in coaxial double-rotary wing flow field uses formulaIt calculates, determines aerodynamic interference number
Value；
Wherein,W is conservation variable, FcFor without viscous flux, FvPoint
Not Wei sticky flux, ρ is fluid density, and p is fluid pressure, u, v, and w is fluid velocity component, E be in unit fluid can, VrIt is
Relative velocity；For the normal vector of control plane；qn,qbRespectively fluid velocity and mesh motion speed is along grid
The component of face normal direction, τ, Φ are physical quantitys relevant to viscosity.
Fig. 3 is coaxial double-rotary wing blade surface geometry model schematic.Fig. 4 is that (1 is upper to coaxial double-rotary wing geometrical model schematic diagram
Rotor, 2 be lower rotor).Fig. 5 is the multi grid schematic diagram under coaxial double-rotary wing ground effect.Fig. 6 is coaxial double-rotary wing ground
Blade tip scrollwork under effect plays schematic diagram.Fig. 7 is the motion pattern under coaxial double-rotary wing ground effect.Fig. 4 is that coaxial double-rotary wing is several
What model schematic, wherein 1 is upper rotor, 2 be lower rotor.
As shown in figs. 3-7, below by taking Harrington-1 coaxial double-rotary wing as an example, the present invention is made further detailed
Explanation.
Aerodynamic interference numerical value suitable for co-axial rotor ground effect of the invention determines method in the actual operation process
Including the following steps:
1) according to rotor parameter, Harrington-1 coaxial double-rotary wing Geometric Modeling is completed.
2) self-compiling program is used, grid dividing is carried out to Harrington-1 coaxial double-rotary wing, using exercise testing
The return motion for simulating co-axial rotor, to around rotor and the grid of Near Ground encrypts.
3) mesh quality is checked, the tail whirlpool under coaxial double-rotary wing ground effect can be rolled on ground, rotor wake region
Higher quality is needed with the grid of Near Ground to capture the Flow details under ground effect.
4) need the exercise testing to rotor in background grid before Harrington-1 coaxial double-rotary wing Flow Field Calculation
In dug a hole and contributed unit searches, the nest relation both established is convenient for carrying out data exchange in calculating.
5) it carries out flow field initialization: using final steady flow condition data as initial value is calculated, the convergence calculated speed can be accelerated
Degree.It, can be using forward flight speed as flow field such as when calculating the ground effect aerodynamic interference of coaxial double-rotary wing low speed forward flight state
Initial value.
6) aerodynamic interference Flow Field Calculation of the Harrington-1 rotor under ground effect is carried out, using N-S equation conduct
Control equation:
Wherein,W is conservation variable, FcFor without viscous flux, FvIt is viscous
Property flux, ρ is fluid density, and p is fluid pressure, u, v, w be fluid velocity component, E be unit fluid in can, VrIt is relatively fast
Degree；For the normal vector of control plane；qn,qbRespectively fluid velocity and mesh motion speed is along grid surface normal direction
Component, τ, Φ are and the relevant physical quantity of viscosity.
For the influence for reducing non-physical dissipation, Flow Field Calculation precision is improved, using second order MUSCL format to unit flow field
It is reconstructed, and the convective flux on grid interface is calculated using Upwind Difference Scheme (Roe format).Due to DCB Specimen interference flowing field
Be it is unsteady, need to carry out time stepping method using dual time method, be used up implicit LU-SGS format in pseudo-time side and carry out
Time stepping method is to improve the computational efficiency in flow field.Turbulence model uses Spalart-Allmaras one-equation model.
7) boundary condition is arranged: when carrying out Flow Field Calculation, the ground below coaxial double-rotary wing is using no slip boundary condition
To simulate.Other boundaries use far field boundary, and the information of flow of far field boundary is determined using one-dimensional Riemann invariant.
8) in order to accurately capture nonstationary flow field characteristic, this numerical method carries out time stepping method using dual time stepping, and
Flow field is accelerated to restrain by using local time step-length, residual error fairing.It is as follows to embody form:
V represents control unit body volume,For conservation variable, t indicates physical time, and n is the iterative steps on t, and dt refers to
Be time difference form.Iterative steps are more than to carry out next step after pseudo-time walks.
9) coaxial double-rotary wing exercise testing coordinate is updated, and calculates blade grid surface method arrow, the net of current position
The information such as lattice movement velocity.
10) nest relation between coaxial double-rotary wing exercise testing and background grid is updated, that is, digs a hole and contributes and is single
Meta Search Engine.
11) after the physical time of calculating is met the requirements, terminate to calculate and export rotary wing performance and information of flow.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.For system disclosed in embodiment
For, since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is said referring to method part
It is bright.
Used herein a specific example illustrates the principle and implementation of the invention, and above embodiments are said
It is bright to be merely used to help understand method and its core concept of the invention；At the same time, for those skilled in the art, foundation
Thought of the invention, there will be changes in the specific implementation manner and application range.In conclusion the content of the present specification is not
It is interpreted as limitation of the present invention.
Claims (8)
1. a kind of aerodynamic interference numerical value suitable for co-axial rotor ground effect determines method characterized by comprising
Obtain rotor parameter；
Coaxial double-rotary wing geometrical model is established according to the rotor parameter；
Select area of space as computational domain according to the geometrical model, the area of space includes the geometrical model；
Discrete to the computational domain progress comprising the coaxial double-rotary wing, division obtains calculating grid；
The true information of flow of the grid position of the division is replaced with the information of flow in the calculating grid；
Determine boundary condition；
Determine the initial value in the coaxial double-rotary wing flow field of ground proximity；
It is counted according to the initial value in the coaxial double-rotary wing flow field of the grid of the division, boundary condition and the ground proximity
It calculates, determines that information of flow, the information of flow include speed, density, pressure and the interior energy of air-flow.
2. the aerodynamic interference numerical value according to claim 1 suitable for co-axial rotor ground effect determines method, feature
It is, the described pair of computational domain progress comprising coaxial double-rotary wing is discrete, and division obtains calculating grid, it specifically includes:
It is discrete to the computational domain progress comprising coaxial double-rotary wing, obtain background grid；
Exercise testing is obtained to the return motion of background grid simulation DCB Specimen；
Local mesh reflnement is carried out to background grid rotor wake region and Near Ground using multiple grid method, is obtained
Encrypted grid；
Judge whether the encrypted grid meets setting mesh quality requirement；
If so, carrying out flow field calculation calculating；
Select area of space as computational domain according to the geometrical model if it is not, returning, the area of space includes the geometry
Model.
3. the aerodynamic interference numerical value according to claim 1 suitable for co-axial rotor ground effect determines method, feature
It is, the determining boundary condition specifically includes:
When determining boundary condition, the ground below coaxial double-rotary wing determines boundary information using no slip boundary condition；Except altogether
Far field boundary information is determined using one-dimensional Riemann invariant outside ground below axis DCB Specimen.
4. the aerodynamic interference numerical value according to claim 1 suitable for co-axial rotor ground effect determines method, feature
Be, the initial value in the coaxial double-rotary wing flow field according to the grid of the division, boundary condition and the ground proximity into
Row calculates, and determines aerodynamic interference numerical value, specifically includes:
Formula is used according to the initial value in the coaxial double-rotary wing flow field of the grid of the division, boundary condition and the ground proximityIt calculates, determines aerodynamic interference numerical value；
Wherein,W is conservation variable, FcFor without viscous flux, FvIt is respectively viscous
Property flux, ρ is fluid density, and p is fluid pressure,u,v,wFor fluid velocity component, E is energy, V in unit fluidrIt is relatively fast
Degree；For the normal vector of control plane；qn,qbRespectively fluid velocity and mesh motion speed is along grid surface normal direction
Component, τ, Φ are and the relevant physical quantity of viscosity.
5. a kind of aerodynamic interference numerical value suitable for co-axial rotor ground effect determines method characterized by comprising
Module is obtained, for obtaining rotor parameter；
Model building module, for establishing coaxial double-rotary wing geometrical model according to the rotor parameter；
Area of space selecting module, for selecting area of space as computational domain, the area of space according to the geometrical model
Include the geometrical model；
Grid dividing module, discrete for carrying out to the computational domain comprising the coaxial double-rotary wing, division obtains calculating grid；
Flow field alternative module, the true stream of the grid position for replacing the division with the information of flow in the calculating grid
Field information；
Boundary determining module, for determining boundary condition；
Initial value determining module, the initial value in the coaxial double-rotary wing flow field for determining ground proximity；
Aerodynamic interference numerical value determining module, for according to the coaxial of the grid of the division, boundary condition and the ground proximity
The initial value of coaxial rotor flowfield is calculated, and determines that information of flow, the information of flow include the speed, density, pressure of air-flow
With interior energy.
6. the aerodynamic interference numerical value according to claim 5 suitable for co-axial rotor ground effect determines system, feature
It is, the grid dividing module specifically includes:
Discrete unit, it is discrete for being carried out to the computational domain comprising coaxial double-rotary wing, obtain background grid；
Return motion unit obtains exercise testing for the return motion to background grid simulation DCB Specimen；
Encryption unit, for carrying out part to background grid rotor wake region and Near Ground using multiple grid method
Mesh refinement obtains encrypted grid；
Judging unit, for judging whether the encrypted grid meets setting mesh quality requirement；
If so, carrying out flow field calculation calculating；
Select area of space as computational domain according to the geometrical model if it is not, returning, the area of space includes the geometry
Model.
7. the aerodynamic interference numerical value according to claim 5 suitable for co-axial rotor ground effect determines system, feature
It is, the boundary determining module specifically includes:
Boundary determination unit, for determining boundary condition, the ground below coaxial double-rotary wing is using no slip boundary condition come really
Determine boundary information；Far field boundary information is determined using one-dimensional Riemann invariant in addition to the ground below coaxial double-rotary wing.
8. the aerodynamic interference numerical value according to claim 5 suitable for co-axial rotor ground effect determines system, feature
It is, the aerodynamic interference numerical value determining module specifically includes:
Aerodynamic interference numerical value determination unit, for according to the coaxial of the grid of the division, boundary condition and the ground proximity
The initial value of coaxial rotor flowfield uses formulaIt calculates, determines aerodynamic interference numerical value；
Wherein,W is conservation variable, FcFor without viscous flux, FvIt is respectively viscous
Property flux, ρ is fluid density, and p is fluid pressure, u, v, w be fluid velocity component, E be unit fluid in can, VrIt is relatively fast
Degree；For the normal vector of control plane；qn,qbRespectively fluid velocity and mesh motion speed is along grid surface normal direction
Component, τ, Φ are and the relevant physical quantity of viscosity.
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| CN113221478A (en) * | 2021-05-07 | 2021-08-06 | 南京航空航天大学 | Numerical analysis method and system for actively controlling rotor wing |
| CN113312728A (en) * | 2021-06-24 | 2021-08-27 | 南京航空航天大学 | Flow field simulation method and system in oil loss process of double-row tapered roller bearing |
| CN113515900A (en) * | 2021-04-07 | 2021-10-19 | 南京航空航天大学 | Numerical simulation method for simulating wake flow of continuous rotation detonation engine |
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2019
- 2019-01-21 CN CN201910053907.7A patent/CN109871586A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111563299A (en) * | 2020-04-30 | 2020-08-21 | 南京航空航天大学 | Rotor noise determination method and system |
| CN111563299B (en) * | 2020-04-30 | 2024-01-30 | 南京航空航天大学 | Rotor noise determination method and system |
| CN113515900A (en) * | 2021-04-07 | 2021-10-19 | 南京航空航天大学 | Numerical simulation method for simulating wake flow of continuous rotation detonation engine |
| CN113221478A (en) * | 2021-05-07 | 2021-08-06 | 南京航空航天大学 | Numerical analysis method and system for actively controlling rotor wing |
| CN113221478B (en) * | 2021-05-07 | 2024-02-02 | 南京航空航天大学 | Numerical analysis method and system for actively controlling rotor wing |
| CN113312728A (en) * | 2021-06-24 | 2021-08-27 | 南京航空航天大学 | Flow field simulation method and system in oil loss process of double-row tapered roller bearing |
| CN113312728B (en) * | 2021-06-24 | 2024-06-11 | 南京航空航天大学 | Flow field simulation method and system in oil loss process of double-row tapered roller bearing |
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