课程设计---翼身组合体气动力计算

1、课程设计一-翼身组合体气动力 计算FLUENT课程设计说明书翼身组合体气动力计算2. 2 Gambit网格划分17院系航空宇航工程学院 专业一飞行器设计与工程专业_XXXXXXX学号 XXXXXXXXXXXXX姓名_XXXXXX指导教师XXXXXX2011/7/6目录第一章软件介绍.41. 1 Gambit软件介绍.412 Fluent软件介绍 .4第二章前处理 .521 Gambit建立模型 .523 Gambit设置边界条件.19第三章求解.203. 1 Fluent求解器设置 .2032 Fluent求解过程 .32第四章后处理.3441 Fluent后处理 .3542 Tecplot后

2、处理.40第五章总结.47第六章附录.48第一章软件介绍1. 1 Gambit软件介绍Gambit软件的主要功能是网格划分，当然也有实体建模的功能，并可导入 大多数三维建模软件的模型文件，其次是设置边界条件，最后导出网格。1. 2 Fluent软件介绍Fluent软件的主要功能是求解和后处理，读入来自Gambit的网格数据后， 设置相应参数后，迭代计算求解，最后进行结果的显示和输出。6第二章前处理2. 1 Gambit建立模型(1)导入机身母线数据File/ImportAertex Data (数据格式请査看数据文件)7(2)选择 vertex DataSolverNewRun Journal

3、View RleOpenSavePrint Graphics .Clean Journal d unlGympor: Vertex Data F le图2.289图2.3机身母线点组图2.4机身线段组GeometiyEdgefY|W J Convert Edges (Nonreal to Real)Edges PickIE却 piy IGoseReset |图2 6(3)通过 Operation/Geometiy/Edge/Convert Edges 将机身母线转化成实线Operation1011(5)连接母线首尾两点成直线OperationGeometry I厲|厲|而戯IVolume叫鷺1

4、闽1卫1 &Revolve FacesFaces11 1AngleAxisDefinG|Draft:Type(0,0,0)-(0,0,1)ExtendedRound纳脚With meshLabelApply| Reset | Qose图 2.10(7)生成旋转机身图2 11(8)隐藏旋转成的机身，导入翼型上表面数据(翼型为NACA0016翼型)12Gy yiiili*lii川仙卄呼 FIIHIIIIIIIIIIII 川川 |图2.12翼型上表面数据点组(9)连点成线，合并线段，转化成实线，生成上翼面实线。图2.14翼型下翼面实线13Cdorclinate Sys. |：c_$y3.1TypeJ

5、jCartesian J IGlobal=0J Connected geometryLocal图 2.16(10)分别为按比例20, 40放大翼面ffl 2.17(11)小翼面移动( (12.5,0,25)大翼面移动( ( 45,0,0)OperationGeometryFace塑曰旦111 莎少日I闽II矽|MOYE / Copy FacesMoveOporation:v Translate7 Rotate7 Reflect ScaleFactor 函图 2.1814Face创日旦ill對V V/_/ Parallelogran I PolyQDHV-*Circle夕 * EllipseiR

6、otateScaleNet SjrFccet_sys.1*1| -| Succp Edgs芒r1r(12)通过Skin Surface连接大翼型和小翼型上表面生成机翼上表面OperationGeometryo| 0|g 01Skin SurfaceCartesian Comected geometry图 2.19图 2.20) )y Faces； i WireframeRevolve EdgesLocalGy15( (14)通过四个机翼表面生成机翼实体(15)以xoy面对称机翼实体OperationOperationGeometryueumeuy _Geometry 11序|耳jg| 11洌厅

7、液VolumeVolumep旦旦回對回旦色回扈 严I鬼I園纠門鬼I園VStitch FacesMove / Copy VolumesFaces face.6Number: Single volumey Multiple volumes Realy Virtualy Av；Type:%ToleranceAuto -J*1Volumes Pick I |polume.2y Move Copy ifOperation:y Translate7 Rotate Reflect7 ScaleReflection PlaneDefineApply |Reset |Close |Label(0,0,0)-(0

8、,0,1)Active Coord Sys. Vector图2 22图 2.231617OperationGeometryVolumeVolumesResetQose图 2.25(17)生成圆柱 高800半径250 CenterX 一_r(18)圆柱减去翼身组合体19纽华卫轴0001X0001爭帀丁旦耻库丑(61)srzffl9S0D| lasaa |X|ddvurejea rIIsaiuniOAurejaa rlOEijqns1*1IIaiuniOAsaiuniOA leay loegns夕|國|园西叵回直euin|OAXauioag顾W再创uor) )Biado(20)用生成的面去剪切求解

9、域，并删除z轴负向的一半OperationGeomotry盘11引厅I莎翹Itolume爾|压画II矽I2122(22)用生成的圆柱分割求解域(connected)MeshEdge I I |H|图 2.34图23523242. 2 Gambit网格划分(1)对机身表面线段网格划分(interval size=l等间距)图 2.36(2)对中间半圆柱表面线段网格划分( (interval size=5等间距)(3)对外面半圆柱表面线段网格划分(interval slze=10等间距)25(4)对中间半圆柱体网格划分(默认设置)OperationMesh罔血创 jgVolume曹蹙團列创 I2J

10、4RQSOt |C10S9|图 2.39Elements:Tet/Hybrid IOptions:F MeshJ Remove old meshJr：c$hJ Ignore size functions26图 2.40272. 3 Gambit设置边界条件隐藏网格，设定边界条件(1)wall类型 翼身组合体表面1) wall_body机身表面2) wall_wing_top机翼上表面3) wall.wing.bottom 机翼下表面4) wing_side机翼侧边缘(2)pressure_far_field (远场边界条件)大半圆柱表面(3)symmetry (对称面)大半圆柱和小半圆柱矩形面

11、导出网格数据，并在 fluent中检査28第三章求解3.1 Fluent求解器设置(1)打开Fluent,选择三维单精度类型(2)导入网格数据旦 FLUENT 3d, pbns, lamI File | Grid Define Solve Adapt Surface Display PioReadCase. WriteData.ImportExport.Interpol a te Case & Data.PDF”.DTR.M Rays.View Factors. Hardcopy.Batch Options.Profile.ISAT Table.Save LayoutScheme.Run.Jo

12、urnal.RSF.expendExit129DonPolyh edraGriMerge.Separa t 巳DoFuse.ZoneUoSurface Mesh.ReorderScale.FaTranslate.Rotate 4Smooth/Swap.79fi392851maxmaxmax(3)检査网格3 FLUENT 3d. pbns, lamFile | Grid Define Solve Adapt SuCheckInfo(4)最小体积大于零 FLUENT 3d, pbns, lam. 一 G 回File Grid Define Solve Adapt Surface Display P

13、lot Report Parallel HelpGrid CheckDomain Extents:x-coordinate: min y-coordinate: min z-coordinate: min Uolume statistics:(n) = -4.000009e+002,5) = -2.500080e+002,5) = -1.530758e-014,(ID) = 4.000000e+002(m) = 2.500080e+902(m) = 2.500080e+902minimum maximum total Face areauolume (m3): uolume (m3): uol

14、ume (m3): statistics:2.796100e-0825.392468e+0927.851229e+097minimum Face area (m2): 1.588932e-001maximum Face area (m2): 1.391012e+802Checking Checking Checking Checking Checking Checkingnumber of nodes per cell, number of Faces per cell, thread pointers.number of cells per face- Face cells.bridge F

15、aces.3031(6)定义基本求解器3 FLUENT 3d, pbns, lamGrid CheModelsSolver.Domainx-coo y-coo z-coo Uolumeminim maxim tot Face ar minim maxin Checkin Checkin Checkin Chpckin Checkin CheckinMateria s.Phases.Operating Con ditions.Boundary Conditions. Periodic Conditions.Grid Interfaces.Dynamic MeshMixing Planes.Tur

16、bo Topology-Injections. DTRM Rays.Custom Field Functions.Multiphase-Energy.Viscous.Radiation.SpeciesDiscrete Phase.Solidification & Melting.Acoustcs.(5)网格重命名(加快求解速度)File Grid Define Solve Adapt Surface Display Plot Report Parallel HelpProfiles.相应设置如图(Pressure Based压力基 适用于低速不可压流,Density Based 密度基 适用于

17、高速可压流；求梯度的方法选择Green-Gauss Node Based,非常 适合于非结构网格o Implicit隐式消耗内存，收敛快；Explicit显式节省内存, 收敛慢，如果觉得自己的电脑内存不够用，可选用显示求解，隐式大约需要1G 32内存)33(7)定义湍流模型相应设置如图(Inviscid模型适用于无粘层流，Laminar模型适用于有粘层 流，后五项适用于湍流，Spalart-Allmaras适用于具有壁面限制的飞行器、翼型 等绕流流场分析；选择 StrainAzortlcity-Based Production)34ModelModel Constants广 Inviscid:

18、Laminare Spalart-Allmaras (1 eqn) k-epsilon 2 eqn k-omega (2 eqn)厂 Reynolds Stress (7 eqn Detached Eddy Simulation厂 Large Eddy Simulation LESSpalart-Allmaras OptionsVorticity-Based Production Strain/Vorticity-Based ProductionUser-Defined FunctionsTurbulent ViscositynoneCancel I Help I(8)设置流体属性S FLUE

19、NT3d, dbns imp, S-A File Grid| Define Solve Adapt Surface Display Plot Report Parallel HelpCh&ckinModelsCheckin CheckinMaterials.CheckinPhases.CheckinOperating Conditions. CheckinCheckinBoundary Conditions.CheckinPeriodic Conditions.CheckinCheckinGrid Interfaces.CheckinDynamic MeshCheckinCheckinMixi

20、ng Planes.CheckinTurbo Topology.CheckinDone.Inject) onsDTRM Rays.Note: EnCustom Field Funciionsuired bp material density method.4Profiles.35相应设置如图( (Density中选择理想气体ideal-gas； Viscosity中选择 Sutherland,弹出窗口，保持默认设置；注意，一定要Change/Create后在关闭 窗口)(9)设置环境属性36相应设置如图(压力0,无重力)(10)设置边界条件FLUENT 3d. dbns imp, S-A：相应

21、设置如图37Boundary ConditionsZoneTypedefault-interiorexhaust-fanfluidinlctvcntpressure far field.dintake-fansymmetry. 6interfacewall bodymaos-flow-inletwall sideoutflowJwall wing bottomoutlebvenl二1wall winq toppreseu re-fa r-fieldhpressure-inlet pressure-outlet symmetry velocity-inletDr4|Set.Copy.Close

22、| Help1 f(大气压力101325,马赫数0.8,迎角10度，计算岀相应方向上的单位速 度分量;湍流指定方法 Turbulence Specification Method 选择 Turbulent Viscosity Ratio,粘性比10不变)口 Pressure Far-FieldZone Name|pressure_tf:ar_f:ield. 5Momentum j Thermal | Radiation | Species | UDS | DPMGauge Pressure (pascal) 101325|Mach NumberI constantjI constantJX-C

23、omponent of Flow Direction p.981*8I constantY-Component of Flow Direction p.1736constantjZ-Component of Flow Direction gTurbulenceI constantJSpecification Method Turbulent Viscosity Ratio二|Turbulent Viscosity Ratio|constantOK Cancel | Help7温应3乔变，热力学温度）38(11)求解参数设置旦 FLUENT 3d, dbns; imp S-AFile Grid

24、Define Solve Adapt Surface Display Plot Report Parallel HelpChecking Checking Checking Checking Checking Checking Checking Checking Checking Checking Checking Checking Checking Checking Checking Done.faceControlsSolution.bride righlInitializeMultigrid.facpMonitorsLimits.faceAnimateMulti-Stage.eleinc

25、bouncMesh Motion.faceParticle History卜peril nodeExecute Commands.nosoCase ChecknosolfaceIterate.cell stor;Acoustic Signals.Note: Enabling energy equation as required by material density method 相应设置如图3940(12)初始化相应设置如图(从远场边界初始化，Init后Apply,在关闭)(13)设置残差监视器41相应设置如图(14)设置阻力，升力，力矩系数监视器3 FLUENT 13d. dbm imp

26、rT1!File Grid DefineSolve Adapt Surface DisplayPlot Report ParallelHelpFace bride righlControlsInitialize厶Checking Checking Checking CheckingFaceMonitorsResidual.AnimateStatistic.Face elem bouiuMesh Motion.Force.Face perlc nodePartide HistoryExecute Commands.Surface.Volume.nosoJ nosolCase Check.Chec

27、king Checking Checking Checking Checking Checking Checking Checking Checking Checking CheckingFace cell storiIterate.Acoustic SignalsDone =Mote: Enabling energy equation as required by material density nethod 相应设置如图42Apply之后在Coefficient中选择Lift,设置升力系数监视器如图Apply之后在Coefficient中选择Moment,设置力矩系数监视器如图(15)设

28、置升力.阻力.力矩参考值43OK I Cancel IHelpNote: Enabling energy equation as required by naterial density nettwd 相应设置如图（从远场初始化参考值，参考面积为机翼面积二（根弦长+梢弦长）x半个展长，参考长度二平均弦长二（根弦长+梢弦长）/2.0） ）口 Reference ValuesCompulE Frompressure_tar_field.5Reference ValuesArea (m2) |isonDensity (kg/m3) |i.176676Entha,py G/M 340480.4Leng

29、th (叫3Pressure (pascal) 132 .8Temperature (k |299.9993Velocity (m/s) |277.6fj98 scosity (kgfm-s) |i.789e-05 Ratio of Sprdfic Heats p .4Reference Zone3. 2 Fluent求解过程（ （1） ）迭代计算H FLUENT 34 dbr.s imp, S-AFie Grid D福ne 5Q!VG Ada 口Checking face cells.Chrcking bridge Fdcrs.Checking right-handed cells Chec

30、king face handedness.Checking face node order.Chocking vlvnvnt typo consictonc.Checking boundary types:CheckingCheckingChockingCheckingCheckingCheckingCheckingCheckingDone.Summary.face pairs periodic boundaries nadp count.nosolue cell count nosolve face count face children, cell children storage Flu

31、xes.Force.Projected Areas.Surface Integrals. Volume Integrals. Discrete Phase S2S Irrfcmvrtion.Reference Values.44IterationNumber of IterationsReporting Inter/alUDF Profile Update Interval佃q11厶-;-1-Iterate I Apply 1 CloseHelpIS3 Iterate45点击Iterate后开始迭代，在迭代过程中会显示四个窗口，残塞 阻力、升力、 力矩，通过判断四个图，判断收敛情况，本例大约需

32、迭代100步，用时40分钟。(2)生成的残差图46rgr们次(3)生成的阻力图3 FLUENT FT 庄3C7ewyratt*Y(4)生成的升力图(5)生成的力矩图MBT07i FLUENT 0： Fberr TncnerattonsuxsifUCXTC) )N5rw * FLUENT 2 Fluent rQ FLUENT 3 Fluent IncIterations47第四章后处理484. 1 Fluent后处理(1)翼身里合体半吏面等压线图旦 FLUENT 2d, dbns imp, S-AFileGridDefineSolveAdaptSurface | Dispby PlotRepor

33、tParallelHelp冉6triangularwallFaces,Zl110triangularuallfaces.Zl107$triangularuallaces,NQ1077triangularvailfaces.Zt1381M97triangularinterior132234nodes, binary.132234node flagsbinary Building. grid, materials, interface, donains, mixturezones, default-interior ujallringtop vxill_wing_bottoin wall_slde

34、 vwll_body pressure_Far_field.5 synnetrp 6 Fluidshpll conduction ZOHPS. Done.Reading C:U5ersGXQDocunientsG.Partide Tracks.DTRM Graphics.Sweep Surface.Zone Motion.Options.Scene.Scene Animation.Views.Lights.Colormaps.Mouse Buttons.Annotate.PDF Tables/Curves.hnnoH Con toursOptionsF FilledP Node ValuesP

35、 Global Range Auto Range 厂 Clip to Range 厂 Draw Profiles r Draw GridContours ofI Pressure.Min (pascaljMax (pascal130762.6Il46880.6Surface Name PatternSurfaces11 =I symmetry.64wallbodywallsidePW3ll_wing_ bottomwall wing iopMatchSurface Types11 =axis clip-surf exhaust-fan fanDisplay ICloseH 巳 Ip |49Co

36、ntours or 曲匕 Pressure (pascal)501.47e+O5 142e+O5 139e+O5 135e+O5 1326+05 123e+O5 125e+O5 I2ie+S 伯 86+05 1.14e+O5 1-Iie+O5 1.07e+05 1.CHe+05 10)6+05 969e+H 9346+04 899e+H 864e+H 829e+H 74e+Oi 759e+O4 725e+H 6e+H 655e+H 620e+H 585e+H 5.5Oe+O4 5.15e+H 4 33e+H 445eKH 4.1le+H 376e+H 3.4le+H 3O6e+HCorcour

37、soTSGtte Pressure (pascal)JUI06.2011FLUEfsTT 63 (3d. dDn& bp. &A)选中Filled, Display显示压力云图1.47e+O5 1.42e+O5 1.39e+O5 135e+O5 132e+O5 123e+O5 1256+05 12le+O5 1-18e+O5 1.14e+O5 i.ne+05 1.07e+05 1.04e+05 i.a) )e+a5 969e+O4 954e+O4 899e+O4 864e+O4 829e+O4 754e+O4 7.59e+O4 725e+O4 693e+O4 6 55e+O4 620e+04

38、535e+O4 550e+04 5.156+04 4 33e+O4 4 45e+O4 4.11*4 376e+O4 3.41e+O4 3 06e+04Jul 06.2011FLUEfsTT 63 (3d. Ons mp. &A)Contours or 曲匕 Pressure (pascal)5152Save Name luiew-0Camera. IClose(2)设置显示整个翼身组合体File Grid Definw Solve Adapt Surface |JDi;spby | Plot Report Parallel Help5446 triangular wall faces, z(

39、(Grid.110 triangular wall faces, ztCc n+m ire.1875 triangular wall faces, zt1877 triangular wall faces, zVectors.1381897 triangular interior face!Pathlines.132234 nodes, binary.132234 node Flags, binary.Particle Tracks.DTR.M Graphics.Building grid,Sweep Surface.materials,Zone Merface,domain

40、s,Opti ms,.mixtureScene.zones,default-interiorScene Animation.wall_wing_topViews.wall uing bottomwall_sideLights.wall_bodyColormaps.pressure_Far_Field.5Mouse Buttons.symmetry.6fluidAnno tate.ViewsActionsMirror Planes =Define Plane-Define.symme-fry.6Periodic Repeats53shell conduction zones,Done PDF T

41、ables/Curves.Do irtn nrfi P - IIPVfl nnoBimrin-t-r- PE3 Views选中对称面后，Apply,然后在Contour窗口点击Display即可541.47e+O5 142e+O5 139e+O5 1.35e+O5 1.32e+O5 123e+O5 1256+05 12le+O5 1.18e+O5 1.14e+C5 1-He+O5 1.07e+05 1.CHe+O5 10)6+05 969e+O4 9346+04 899e+O4 864e+O4 829e+O4759e+O4 725e+O4 6e+O4 655e+O4 620e+H 585e+O

42、4 5.5Oe+O4 5.15e+O4 4 33e+O4 445e+O4 4.11e+O4 376+O4 341e+04 3 06+04(3)査看速度矢量图E FLUENT 3d,dbnsimpf S-AFile Grid Define Solve Adapt Surface | Display Plot Report Parallel 卜Ail 06.2011544611010751077 1381097 132234 132234triangular triangular triangular triangular triangularwall wall wall wallFaces, F

43、aces, Faces, Faces,Grid.Contours.Verior Face?nodes, binary node Flags, binary.Building_grid,materials,interface, domains, mixturezones, deFault-interior vMll_vjiing_top wa ll_vjiing_bottom wall_side vwll_bodi/ pressure_Far_Field.5 symmetry.6 fluidshell conduction zones.Done.PQ ar1*i nn P -

44、 llcaG- CVflS rineiimcint-G QPathlines.Particle Tracks.DTRM Gra phics.Sweep Surface-Zone Motion.Options.Scene.Scene AnimationViews.Lights.Colormaps.Mouse Buttons.Annotate.PDF Tables/Curves.5556JUI06.2011FLUENT 63 (3d. dDns g &A)4 96e+02 4.77e+02 4.628+02420e+02 4.06e+02 39le+02 3.77e+02 363e+02 349e

45、+O2 3e+C2 320e+02 3.06e+02 292e+02 278e+02 263e+02 249e+O2 2356+02 221e+ 2066+02 1$2e+C2 178*2 16te+02 150e+G2 135e+02 12le+C2 1.07e+02 927e+01 7.85e+O1 6 42e+01 5a) )e+oivetooiy vectors Cotored 场 Vetooiy Magnfijoe (m*s)总结：可以得到阻力系数Cd=0.035、升力系数Cl=0.200.力矩系数Cm=0.06。阻力D = 2 X Cd X -pv2s 升力L = 2 X Cl X

46、 Zpvs力矩2 2M = 2 X Cm X | pv2s X bA574. 2 Tecplot 后处理Tecplot后处理主要是通过平行于翼身组合体的平面截取组合体，获得所截 平面上下两条曲线的数据分布(如压力分布)。(1)从Fluent中导出需要处理的数据58(2)导入数据到Tecplot中59TecpIotDaG Lod刨Text Spreadsheet LoaderNew Layout Open Layout Save Layout Save Layout as.Ctrl+OCtrl+SCtrl+WLoad Data File(s).Write Data File.Print Prev

47、iew.Print.Paper Setup.Ctrl+PPublish.Export.Ctrl 十 UPreferencesExitCtrl+QSelect Import FormatANSYS Results (FEA)CGNS LoaderDEM Loader DXF LoaderESI/PAM-CRASH DAISY (FEA EnSight LoaderExcel LoaderFL0W-3D LoaderFLUENT/FIDAP Neutral (FEA) Fluent Data LoaderGeneral T ext LoaderHDF LoaderHDF5 LoaderKiva L

48、oaderLSTC/DYNA Input (FEALSTC/DYNA Taurus State Database (FEA) MSC2NASTRAN Bulk Data (FEA) MSC/NASTRAM Output2 (FEA)MSC/PaUan Neutral (FEA)PL0T3D LoaderPLY Polygon File Loader PTC/Mechanica Design Study (FEA)SDRC/IDEAS Universal (FEA)StarCCM (FEA1OK CancelHelp| File Edit View Plot Insert Animate Data Frame Options $60Tecplot Data Loaderg Tecpbt 360 2010i File Edit View PlotD *日呂氐3D Cariian Zone SuifdC6$Layers:Mesh0 Ccrtour QVectorSctei回E Effects:171 LigHhgTronsluccrcyZone Stye.Derived