CN108536922A - The internal and external flow field integration method for numerical simulation of aircraft and engine - Google Patents
The internal and external flow field integration method for numerical simulation of aircraft and engine Download PDFInfo
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Abstract
Present disclose provides a kind of aircraft and the internal and external flow field integration method for numerical simulation of engine, include the following steps：S1 carries out mesh generation to model aircraft, and individually divides engine portion and be divided into particular fluid region；S2 builds the compressor part that engine is replaced along streamline body force model in particular fluid region；S3 extracts the body force of compressor, obtains the expression formula of body force and the coefficient of body force, obtains body force source item according to the coefficient of body force, the body force source item field in particular fluid region, i.e. engine interior flow field are solved according to body force source item；S4 carries out wind tunnel test to model aircraft, obtains the far field boundary condition of model aircraft；And the three-dimensional computations hydrodinamical model of S5 structure model aircrafts, with reference to the design conditions of the Detailed Numerical Simulation of External Flow Field of far field boundary condition setting three-dimensional computations hydrodinamical model, and the coefficient along streamline body force model is calculated according to air flow rate, realize the integrated numerical simulation of flow field and Flow Field outside.
Description
Technical field
This disclosure relates to the internal and external flow field integration method for numerical simulation of a kind of aircraft and engine.
Background technology
With the development of aeronautical technology, researcher has found that influencing each other for aircraft and engine is increasingly closer, not only body
The internal and external flow field of fuselage and air intake duct, fuselage and jet pipe is interfered under present high-speed flight state, at the same caused by fuselage into
Gas distortion can also have an important influence on engine performance.In order to solve the compatible matching of aircraft, engine, aircraft is promoted
The integrated design of overall performance, aircraft/engine already becomes new trend.Therefore, aircraft/engine integration is calculated
Demand emerge, but the huge increasing of its calculation amount will be made us imagining.Have scholar only to single-stage compressor and air intake duct into
Combined calculation is gone, grid has been approached 6000W, and carries out Reynolds average simulation (RANS) to aircraft/engine whole flow field and be even more
It can not be found from open source literature.
Currently, in order to avoid the huge calculation amount of direct Numerical (DNS), common method is in outer Flow Field Calculation
Given uniform back-pressure export boundary condition substitutes the import section of engine, and given flow inlet boundary condition substitutes engine
Outlet.This method ignores the inner geometry of engine, saves computing resource, can comparatively fast understand overall performance, but by
It is not necessarily equally distributed in the import sectional pressure of the coupling of fuselage and engine, engine, therefore this side
Method can not really reflect the inside and outside coupling influence flowed completely.In order to seek more accurate analogy method, some scholars needle
To the body force model computational methods of the N+3 project developments of NASA based on Gong model refinements, to being embedded in 16 compressors
Blended wing-body carried out the numerical simulation of degree of precision.Body force model method has ignored blade complicated inside compressor
Configuration converts the active force of blade in the power source for being applied to corresponding region, can accurately simulate compressor inside stream
It is dynamic, but since it still remains the geometry of wheel hub and casing, and apply the body with circumferential direction axially, radially under rotating coordinate system
Product power, complicated geometric configuration so that grid number is more than 2000W, and mesh generation and solution procedure are all by calculating instrument, meter
The limitation of resource is calculated, the integrated Fast numerical simulation of aircraft/engine is difficult to realize.
Invention content
In order to solve at least one above-mentioned technical problem, present disclose provides a kind of aircraft and the internal and external flow fields one of engine
Body method for numerical simulation.
According to one aspect of the disclosure, the internal and external flow field integration method for numerical simulation of aircraft and engine, including with
Lower step：
S1 carries out mesh generation to model aircraft, and individually divides engine portion and be divided into particular fluid region；
S2 builds the compressor part that engine is replaced along streamline body force model in particular fluid region；
S3 extracts the body force of compressor, obtains the expression formula of body force and the coefficient of body force, what it is according to body force is
Number obtains body force source item, and the body force source item field in particular fluid region, i.e. engine interior stream are solved according to body force source item
；
S4 carries out wind tunnel test to model aircraft, obtains the far field boundary condition of model aircraft；And
S5 builds the three-dimensional computations hydrodinamical model of model aircraft, and three-dimensional computations stream is arranged with reference to far field boundary condition
The design conditions of the Detailed Numerical Simulation of External Flow Field of body dynamics model, and calculated along streamline body force model according to air flow rate and be
Number realizes the integrated numerical simulation of flow field and Flow Field outside.
According at least one embodiment of the disclosure, in step S2, the construction method along streamline body force model includes
Following steps：
S21 setting compressors are parallel to the active force of air-flow the flow direction of gas, active force of the compressor to air-flow
For body force in an axial direction, concurrently sets compressor region and be formed by stacking by multiple flow tubes, each flow tube is cut into an axial direction
Multiple identical flow tube units, the whole pressure ratio and adiabatic efficiency after each flow tube unit series connection are consistent with compressor, that is, calm the anger
Machine has been broken down into multiple flow tubes for including body force, and compressor is with distributed one-dimensional along streamline body force source item field, i.e. edge
Streamline body force model substitutes；
S22 derives the overall pressure tatio and adiabatic efficiency of each flow tube unit according to the overall pressure tatio and adiabatic efficiency of compressor；
And
S23 sets each flow tube unit by two body forces, lists the equation of momentum and the energy side of each flow tube unit
Journey sets each flow tube unit and is exchanged with extraneous empty calory, meet it is permanent and without viscous condition, by the equation of momentum and energy equation
In the unknown expressed with body force coefficient, body force source item is obtained according to volume force coefficient, and further solves the equation of momentum
And energy equation, it obtains along streamline body force model.
According at least one embodiment of the disclosure, in step S23, each flow tube unit is set by two volumes
Power, two body forces are respectively：It is parallel to streamline tangent line and body force identical with gas flow direction So that gas
Pressure rise；And it is parallel to streamline tangent line but the body force opposite with flow direction Hinder gas flowing；Each flow tube
The resultant force that unit is subject toStill along grain direction, and meet the relationship of following formula 1：
According at least one embodiment of the disclosure, the internal and external flow field integration method for numerical simulation of aircraft and engine
Further comprise the steps：
S6 is by the stagnation pressure liter along streamline body force modeling calculating compressor, by gained numerical simulation result and experiment
The stagnation pressure liter of the compressor of acquisition is compared, reliability of the verification method for numerical simulation in flow field；And
S7 will be put into along streamline body force model in model aircraft, simulation calculate aircraft lift coefficient and resistance coefficient with
The numerical simulation result of acquisition is compared by the change curve of the angle of attack with the results of wind tunnel of model aircraft, verifies numerical value
Including analogy method, the reliability of Flow Field outside.
According at least one embodiment of the disclosure, in step S6, the stagnation pressure liter of the compressor as obtained by numerical simulation
It is compared verification under two conditions with the stagnation pressure liter of the compressor as obtained by experiment, two kinds of conditions are respectively：Uniform air inlet
Condition and inlet distortion condition.
According at least one embodiment of the disclosure, the propulsion system of model aircraft is replaced with aspirating rake, and suction rake is attached
The fuselage back in model aircraft, the boundary layer of suction rake simulation propulsion system sucks effect.
According at least one embodiment of the disclosure, the far field boundary condition of model aircraft is：Cruise Mach number
0.85Ma, height 0m, pressure 101.325Pa, temperature 288.15K, density 1.2249kg/m3, flow 0.223kg/s.
According at least one embodiment of the disclosure, wind tunnel test replaces conventional tail using abdominal support formula brackets
Support formula brackets.
Description of the drawings
Attached drawing shows the illustrative embodiments of the disclosure, and it is bright together for explaining the principles of this disclosure,
Which includes these attached drawings to provide further understanding of the disclosure, and attached drawing is included in the description and constitutes this
Part of specification.
Fig. 1 be according to the pressure term volume force coefficient of the low speed axial flow compressor of at least one embodiment of the disclosure with
The relation schematic diagram of Mach number.
Fig. 2 is the schematic diagram with changes in flow rate according to the stagnation pressure liter of the compressor of at least one embodiment of the disclosure.
Fig. 3 is the lift coefficient along streamline body force model according at least one embodiment of the disclosure with the angle of attack
Change curve (a figures) and resistance coefficient with the angle of attack change curve (b figures).
Specific implementation mode
The disclosure is described in further detail with embodiment below in conjunction with the accompanying drawings.It is understood that this place
The specific implementation mode of description is only used for explaining related content, rather than the restriction to the disclosure.It also should be noted that being
Convenient for description, illustrated only and the relevant part of the disclosure in attached drawing.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the disclosure can
To be combined with each other.The disclosure is described in detail below with reference to the accompanying drawings and in conjunction with embodiment.
In order to save computing resource, shorten aircraft/engine integration design period, really reflect aircraft/engine
Coupling influence, the present disclosure proposes a kind of aircraft and the internal and external flow field integration method for numerical simulation of engine, including following step
Suddenly：
S1 carries out mesh generation to model aircraft, and individually divides engine portion and be divided into particular fluid region；
S2 builds the compressor part that engine is replaced along streamline body force model in particular fluid region；
S3 extracts the body force of compressor, obtains the expression formula of body force and the coefficient of body force, what it is according to body force is
Number obtains body force source item, and the body force source item field in particular fluid region, i.e. engine interior stream are solved according to body force source item
；
S4 carries out wind tunnel test to model aircraft, obtains the far field boundary condition of model aircraft；And
S5 builds the three-dimensional computations hydrodinamical model of model aircraft, and three-dimensional computations stream is arranged with reference to far field boundary condition
The design conditions of the Detailed Numerical Simulation of External Flow Field of body dynamics model, and calculated along streamline body force model according to air flow rate and be
Number realizes the integrated numerical simulation of flow field and Flow Field outside.
In an optional embodiment of the disclosure, it can be built by the following method along streamline body force model：
S21 basic assumptions：
Compressor is the critical piece to the air work flowed through in engine, it is assumed that air-flow along engine axially into
The rotation of compressor, compressor rotor makes air-flow deflect, and generates circumferential component, but stator makes air-flow deflect back to, and counteracts this
A circumferential component, then the direction of final air-flow is still kept axially into it may therefore be assumed that compressor is parallel to airflow acting force
In the flow direction of gas.If choosing the inlet and outlet section of entire compressor and the control volume of casing inner wall formation, can will calm the anger
Machine is reduced to body force in an axial direction to the effect of air-flow, and makes further assumption：
1) assume that the region that entire compressor is substituted in pipeline is formed by stacking by numerous flow tube, and the characteristic of each flow tube
It can be consistent with the characteristic of former compressor；
2) assume that each flow tube is split in an axial direction as infinite multiple flow tube units, each flow tube unit is identical,
And the overall permanence being connected in series still meets the overall pressure tatio and adiabatic efficiency characteristic of former compressor, then it is believed that whole pipeline
Model remains to the characteristic for reflecting former compressor.
Since compressor is broken down into the numerous flow tube for being added to body force, with distributed one-dimensional along streamline
Body force source item field is constituted substitutes compressor along streamline body force model, so that it may with by numerical simulation engine to flowing through gas
The active force of body.
The performance characteristics of S22 micro units：
In S21 basic assumptions, former compressor has been divided into infinite multiple flow tube units, i.e., infinite multiple micro units.
Assuming that each micro unit performance having the same, then when gas flows through each micro unit, being all equivalent to an overall pressure tatio is
Adiabatic efficiency isSmall compressor do work to it.Since the entirety of infinite multiple micro unit compositions will remain to reflect former compressor
Overall performance, it can thus be derived that the relationship of the overall performance of the performance and compressor of each micro unit.
Assuming that the overall pressure tatio of compressor isAdiabatic efficiencyEach flow tube is divided into N number of micro unit,
Then：
The overall pressure tatio of each micro unit is as shown in following formula 2：
The adiabatic efficiency of each micro unit is as shown in following formula 3：
(wherein, k indicates the adiabatic exponent of gas.)
The body force of S23 micro units is analyzed：
Assuming that the micro unit of unit mass is by two powerWith Be parallel to streamline tangent line and with gas flowing side
To identical,So that the pressure rise of gas；Be parallel to streamline tangent line but with gas flow direction on the contrary,Hinder gas stream
Dynamic and generation frictional force；The resultant force that micro unit is subject toStill along grain direction, and meet relational expression 1：
Micro unit is expressed as following formula 4 in the equation of momentum of X-direction:：
(wherein, ρ indicates that gas density, p indicate gas-static, ΦxIndicate body force resultant force in the component of X-direction, τxxTable
Show the stress of the X-direction on the face vertical with X-direction, τxyThe stress of the Y-direction on the face vertical with X-direction is indicated, when t is indicated
Between, VxIndicate speed in the component of X-direction, VyIndicate the component of speed in the Y direction.)
Assuming that body force model meets, permanent, nothing is viscous, axial admission condition, while streamline is not sent out in body force region
Raw big deflection, then it is assumed that the speed of micro unit in the Y direction can be ignored, then micro unit the equation of momentum of X-direction can
It is reduced to following formula 5：
Dissipative termIt is expressed as following formula 6：
Then：
(wherein, ρ indicates gas density,Indicate the heat output of unit mass gas,Indicate the acting of body force resultant force
Amount, τxxIndicate the stress of the X-direction on the face vertical with X-direction, τyyThe stress of table Y-direction on the face vertical with Y-direction, e
Indicate the interior energy of gas, h*Indicate the adiabatic enthalpy of gas, VxIndicate speed in the component of X-direction, VyIndicate speed in the Y direction
Component.)
Assuming that micro unit is exchanged with extraneous empty calory, meets condition permanent, that nothing is viscous, finally obtain resultant force and do workIt can
It is expressed as following formula 8:
(wherein, ρ indicates gas density, VxComponent of the expression speed in X-direction.)
BecauseIt is the unknown, and thinks that it is only related to local Mach number, is respectively defined as volume
Force coefficient fp,fv,By the way that body force to be expressed as to the function of local amount, the unknown in governing equation is then by along streamline
Body force source item field substitutes, and the equation of momentum of X-direction is solved, it can be achieved that with body force source item modelling in conjunction with the characteristic line of compressor
Air-flow flows through the growth of mechanical energy and pressure that compressor is obtained.
More specifically, expression formula is established to micro unit：
1)fpExpression formula such as following formula 9：
(wherein, Δ p indicates that static pressure liter, Δ x indicate the increment of coordinate along streamline, p1Indicate micro unit import static pressure, p2Table
Show micro unit exit static pressure,Indicate micro unit import stagnation pressure,Indicate that micro unit exports stagnation pressure,Indicate each micro unit
Overall pressure tatio.)
Wherein,
By flow formula
(wherein,Indicate that mass flow, k indicate that gas adiabatic exponent, R indicate gas constant, T*Indicate that total temperature, A indicate
Area, q (Ma) indicate the flow function of Mach number.)
And flow conservation principle, the flow function expression formula of Mach number, i.e. following formula 10 can be obtained：
2)fvExpression formula such as following formula 11：
(wherein, V1xIndicate micro unit inlet velocity, V2xIndicate that micro unit muzzle velocity, Δ x indicate the coordinate along streamline
Increment, k indicate that gas adiabatic exponent, R indicate gas constant, T1Indicate micro unit import static temperature, T2Indicate that micro unit outlet is quiet
Temperature.)
Wherein
3)Expression formula such as following formula 12：
(wherein, cpIndicate specific heat capacity at constant pressure, Δ T*Indicate total temperature increment.)
So far, along the body force f of streamlinep,fv,The function measured for locality is completely represented, if total property of known compressor
Can, then it can be substituted by distributed along streamline body force source item field.
In an optional embodiment of the disclosure, in step S23, each flow tube unit is set by two individuals
Product power, two body forces are respectively：It is parallel to streamline tangent line and body force identical with gas flow direction Make gas
Pressure rise；And it is parallel to streamline tangent line but the body force opposite with flow direction Hinder gas flowing；Each stream
The resultant force that pipe unit is subject toStill along grain direction, and meet relational expression：
In an optional embodiment of the disclosure, the internal and external flow field integration method for numerical simulation of aircraft and engine
It may further include following steps：
S6 is by the stagnation pressure liter along streamline body force modeling calculating compressor, by gained numerical simulation result and experiment
The stagnation pressure liter of the compressor of acquisition is compared, reliability of the verification method for numerical simulation in flow field；And
S7 will be put into along streamline body force model in model aircraft, simulation calculate aircraft lift coefficient and resistance coefficient with
The numerical simulation result of acquisition is compared by the change curve of the angle of attack with the results of wind tunnel of model aircraft, verifies numerical value
Including analogy method, the reliability of Flow Field outside.
In an optional embodiment of the disclosure, in step s 6, the stagnation pressure of the compressor as obtained by numerical simulation
It rises and is compared verification under two conditions with the stagnation pressure liter of the compressor as obtained by experiment, two kinds of conditions are respectively：Uniformly into
Gas bar part and inlet distortion condition.
In an optional embodiment of the disclosure, the propulsion system of model aircraft can aspirate rake and replace, suction rake
It is attached to the fuselage back of model aircraft, suction rake can simulate the boundary layer sucking effect of propulsion system.
In an optional embodiment of the disclosure, the far field boundary condition of model aircraft could be provided as：Cruise horse
Conspicuous several 0.85Ma, height 0m, pressure 101.325Pa, temperature 288.15K, density 1.2249kg/m3, flow 0.223kg/s.
In an optional embodiment of the disclosure, wind tunnel test may be used abdominal support formula brackets and replace often
Advise shoe formula brackets.
In an optional embodiment of the disclosure, the analog result as obtained by above-mentioned integrated method for numerical simulation
Verification is compared with experimental result：
1) flow field is verified：
Under the conditions of uniform inlet air conditions and inlet distortion, with along streamline body force model substitute low speed axial flow compressor into
Row Simulation.
The extraction that first performance characteristics of the compressor obtained by experiment are carried out with body force, obtains corresponding body force table
It is pressure term volume force coefficient f as shown in Figure 1 up to formula and volume force coefficientp(Ma) with the changing rule of Ma.
Using commercial numerical software FLUENT, corresponding compressor geometry draws 3D pipeline models.The incoming that distorts is by 30% face
The plate flow spoiler of product blockage ratio realizes that the fluid domain that original wheel hub, blade are added to body force source item field substitutes.Source item
It is to solve to being compiled along streamline volume force coefficient by User-Defined Functions function (UDF) and obtain flow field.Point
It is corresponding along performance characteristics such as the stagnation pressure liters of streamline body force model to obtain compressor for the total parameter for analysing flow field inlet and outlet.
As shown in Fig. 2, under uniform inlet air conditions, rises characteristic along the stagnation pressure of streamline body force model and coincide with experimental result
Degree is higher.Under conditions of inlet distortion, the compressor stagnation pressure liter that method for numerical simulation obtains is tied with the variation of flow with experiment
Fruit is consistent in general trend.Stagnation pressure liter under most of flow rate working conditions is more slightly lower than experiment value, this is because plate flow-disturbing
The perturbation action of device is more strong in numerical simulation, and the fluid to distort in area is not exclusively to enter axially into body force region
, there is smaller speed deflection, or even have slight flow separation near wall, it means that intake velocity is flowed than practical
It is less than normal, therefore the body force of corresponding addition is also less than normal, finally obtained stagnation pressure, which rises, is less than experiment value.Worst error 3.4% occurs
In nearly stall point, still in acceptable error range, therefore, it is considered that under the conditions of inlet distortion, still along streamline body force model
The performance characteristics of compressor can be simulated in certain precision.
2) Flow Field outside is verified：
It will be put into along streamline body force model in certain blended wing-body model aircraft, the model is to be attached to the pumping of fuselage back
It inhales rake and replaces simulation of engine boundary layer sucking effect (BLI effects), experiment is blowed in certain transonic wind tunnel.
In the corresponding three-dimensional computations hydrodinamical model (CFD model) of wind tunnel experiment, dynamical system part can simplify
For the box-like runner of connection, the region folded by internal two faces is body force Adding Area.Since the disclosure only flies to simulating
Symmetrical flow behavior when machine is without sliding is studied, and calculates time and resource to save, numerical computations are in half model CFD nets
It is carried out on lattice.Since the structure of CFD model is complex, in conjunction with considering for computing resource and Numerical accuracy, finally adopt
With the grid configuration of the unstructured combination of structuring-.The partial geometry structure of vertical fin, dynamical system outside and afterbody composition
Type is complicated, selects unstructured grid, and encrypt in wall surface, grid number is about 110W.Dynamical system internal structure is simple, selects
Structured grid, about 15W.Fuselage main body part uses C-H type structured grids, and boundary and lateral boundaries choose 40 before and after far field
The region of times fuselage length.The surface mesh of each wall surface is encrypted along normal direction, to ensure the accurate of numerical computations
Property, grid number is about 110W.It is as shown in table 1 to calculate the far field boundary condition used：
1 CFD far field boundary conditions of table
Alloy making may be used in the model aircraft for carrying out wind tunnel experiment, and the suction rake for being installed on fuselage passes through suction airstream
The BLI effects of simulated engine, pipeline thereafter are connected to induction apparatus, control and suck flow.Due to blended wing-body layout
Fuselage is relatively thin, and dynamical system is arranged in afterbody, therefore abdominal support formula brackets is selected to replace conventional shoe formula branch
Frame is laid out to reduce interference of the holder to fuselage afterbody flow field.
The import of suction rake corresponds to the import of dynamical system air intake duct, and constant pumping quality is maintained by induction apparatus
Flow Min=0.223kg/s completes more angle of attack blowing tests of constant cruise Mach number Ma=0.85.With reference to experimental setup number
It is worth the design conditions of simulation, and according to corresponding liter, the resistance coefficient along streamline body force model of flow rate calculation dynamical system.It will
Corresponding liter, the resistance coefficient along streamline body force model of dynamical system is obtained with the changing rule of the angle of attack with wind tunnel test
It rises, resistance coefficient is compared with the changing rule of the angle of attack.As shown in Fig. 3 (a), when Aircraft Angle of Attack α≤8 °, lift coefficient
CLIt is almost changed linearly with the angle of attack.Subsequent CLReduce with the slope of angle of attack variation, numerical simulation captures the oblique of lift coefficient
Rate changes.After 10 ° of α ＞, CLIt is linearly increasing with α, the more previous linear reduction of slope.When α=10 °, numerical simulation result is found
Have there is separation in aircraft surfaces.Simultaneously after 10 ° of α ＞, the difference of numerical simulation result and experimental result becomes larger, numerical simulation knot
Fruit is generally less than experimental result.The reason of leading to this result, may be there are two aspect：After 10 ° of α ＞, aircraft merges section surface
Separation takes place in air-flow, and slight jitter occurs in model, and the elastic error of model increases, and also results in balance measurement data fluctuations
Increase, experiment value is made to deviate actual value；On the other hand, due to 10 ° of later segregation phenomenons of α ＞, the grid of CFD and used
Turbulence model can not accurately simulate the flow field after air-flow separation, so that simulation value deviates its actual value.
As shown in Fig. 3 (b), when Aircraft Angle of Attack α≤6 °, resistance coefficient CDTwo curves it is preferable.And 6 ° of α ＞
When, there is difference in numerical simulation and experiment result, and the resistance coefficient that CFD is calculated is less than resistance coefficient obtained by wind tunnel test.
The reason of causing difference may have two aspects：First, being caused by the support interferences of wind tunnel model, with the increase of the angle of attack, holder is dry
It disturbs to CDInfluence gradually increase；Second is that after separation occurs in flow field, CFD model is not accurate enough for the flowing capture of Disengagement zone,
Lead to CDAccuracy be deteriorated.
Although there are deviations for the result and results of wind tunnel of numerical simulation, overall variation tendency is consistent, especially
Numerical simulation result and the registration of results of wind tunnel are higher under Low Angle Of Attack, it can be considered that the aircraft of the disclosure and its
The internal and external flow field integration method for numerical simulation of engine is feasible.
In the disclosure, by the compressor along streamline body force model alternative structure complexity, and by engine to flowing through
The form of the source item body force of the active force of gas in a distributed manner is added to along the governing equation of streamline body force model, realizes
The internal and external flow field integration numerical simulation of aircraft and engine.
In the disclosure, the internal and external flow field integration method for numerical simulation of aircraft and engine can relatively accurately reflect
Coupling between aircraft and engine, and a large amount of computing resources can be saved, it on a personal computer can be quickly complete
It is calculated at internal and external flow field integration, substantially reduces the construction period of aircraft/engine integration design.
It will be understood by those of skill in the art that the above embodiment is used for the purpose of clearly demonstrating the disclosure, and simultaneously
Non- be defined to the scope of the present disclosure.For those skilled in the art, may be used also on the basis of disclosed above
To make other variations or modification, and these variations or modification are still in the scope of the present disclosure.
Claims (8)
1. the internal and external flow field integration method for numerical simulation of a kind of aircraft and engine, which is characterized in that include the following steps：
S1 carries out mesh generation to model aircraft, and individually divides engine portion and be divided into particular fluid region；
S2 builds the compressor part that engine is replaced along streamline body force model in the particular fluid region；
S3 extracts the body force of the compressor, the coefficient of the expression formula and the body force of the body force is obtained, according to institute
The coefficient for stating body force obtains body force source item, and the body force source in the particular fluid region is solved according to the body force source item
Item field, i.e. engine interior flow field；
S4 carries out wind tunnel test to model aircraft, obtains the far field boundary condition of model aircraft；And
S5 builds the three-dimensional computations hydrodinamical model of model aircraft, with reference to the far field boundary condition setting three-dimensional meter
The design conditions of the Detailed Numerical Simulation of External Flow Field of fluid operator kinetic model, and it is described along streamline body force according to air flow rate calculating
The coefficient of model realizes the integrated numerical simulation of flow field and Flow Field outside.
2. method for numerical simulation according to claim 1, which is characterized in that described along streamline body force mould in step S2
The construction method of type includes the following steps：
S21 setting compressors are parallel to the active force of air-flow the flow direction of gas, and compressor is edge to the active force of air-flow
Axial body force, concurrently sets compressor region and is formed by stacking by multiple flow tubes, each flow tube is cut into multiple in an axial direction
Identical flow tube unit, the whole pressure ratio and adiabatic efficiency after each flow tube unit series connection are consistent with compressor, i.e. compressor quilt
Multiple flow tubes for including body force are resolved into, compressor is with distributed one-dimensional along streamline body force source item field, i.e., along streamline
Body force model substitutes；
S22 derives the overall pressure tatio and adiabatic efficiency of each flow tube unit according to the overall pressure tatio and adiabatic efficiency of compressor；
And
S23 sets each flow tube unit by two body forces, lists the equation of momentum and energy of each flow tube unit
Measure equation, set each flow tube unit and exchanged with external world's empty calory, meet it is permanent and without viscous condition, by the momentum side
The unknown in journey and the energy equation is expressed with body force coefficient, and body force source item is obtained according to the volume force coefficient,
And the equation of momentum and the energy equation are further solved, it obtains described along streamline body force model.
3. method for numerical simulation according to claim 2, which is characterized in that in step S23, set each flow tube list
By two body forces, described two body forces are respectively member：It is parallel to streamline tangent line and identical with gas flow direction
Body force So that the pressure rise of gas；And it is parallel to streamline tangent line but the body force opposite with flow direction
Hinder gas flowing；The resultant force that each flow tube unit is subject toStill along grain direction, and meet the relationship of following formula 1：
4. method for numerical simulation according to claim 1, which is characterized in that the method further includes following steps：
S6 by the stagnation pressure liter for calculating the compressor along streamline body force modeling, by gained numerical simulation result with
The stagnation pressure liter of the compressor obtained is tested to be compared, verify the method for numerical simulation flow field reliability；With
And
S7 is put into described along streamline body force model in model aircraft, simulation calculate aircraft lift coefficient and resistance coefficient with
The numerical simulation result of acquisition is compared, described in verification by the change curve of the angle of attack with the results of wind tunnel of model aircraft
Including method for numerical simulation, the reliability of Flow Field outside.
5. method for numerical simulation according to claim 4, which is characterized in that in step S6, pressed as obtained by numerical simulation
The stagnation pressure of mechanism of qi rises is compared verification, two kinds of condition difference under two conditions with the stagnation pressure liter of the compressor as obtained by experiment
For：Uniform inlet air conditions and inlet distortion condition.
6. method for numerical simulation according to claim 4, which is characterized in that the propulsion system of the model aircraft is to aspirate
Rake replaces, and the suction rake is attached to the fuselage back of the model aircraft, the boundary layer of the suction rake simulation propulsion system
Suck effect.
7. method for numerical simulation according to claim 1 or 2, which is characterized in that the far field boundary condition is：Cruise horse
Conspicuous several 0.85Ma, height 0m, pressure 101.325Pa, temperature 288.15K, density 1.2249kg/m3, flow 0.223kg/s.
8. method for numerical simulation according to claim 1 or 4, which is characterized in that the wind tunnel test uses abdominal support
Formula brackets replace conventional shoe formula brackets.
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