FLUENT翼型算例_-_Flow_over_an_Airfoil-_Problem_Specification教程.pdf

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1、FLUENT-FlowoveranAirfoil-ProblemSpecificationAuthor:RajeshBhaskaran,CornellUniversityProblemSpecification1.CreateGeometryinGAMBIT2.MeshGeometryinGAMBIT3.SpecifyBoundaryTypesinGAMBIT4.SetUpProbleminFLUENT5.Solve!6.AnalyzeResults7.RefineMeshProblem1Problem2ProblemSpecificationConsidera

2、irflowingoverNACA4412airfoil.Thefreestreamvelocityis50m/sandtheangleofattackis2°.Assumestandardsea-levelvaluesforthefreestreamproperties:Pressure=101,325PaDensity=1.2250kg/m3Temperature=288.16KKinematicviscosityv=1.4607e-5m2/sWewilldeterminetheliftanddragcoefficientsundertheseconditi

3、onsusingFLUENT.Step1:CreateGeometryinGAMBITIfyouwishtoskipthestepsforgridcreation,youcandownloadthemeshfilehere(right-clickandselectSaveAs...)andgotoStep4.HigherResolutionImageThistutorialleadsyouthroughthestepsforgeneratingameshinGAMBITforanairfoilgeometry.ThismeshcanthenbereadintoF

4、LUENTforfluidflowsimulation.Inanexternalflowsuchasthatoveranairfoil,wehavetodefineafarfieldboundaryandmeshtheregionbetweentheairfoilgeometryandthefarfieldboundary.Itisagoodideatoplacethefarfieldboundarywellawayfromtheairfoilsincewe'llusetheambientconditionstodefinetheboundaryconditio

5、nsatthefarfield.Thefartherwearefromtheairfoil,thelesseffectithasontheflowandsomoreaccurateisthefarfieldboundarycondition.Thefarfieldboundarywe'lluseisthelineABCDEFAinthefigureabove.cisthechordlength.StartGAMBITCreateanewdirectorycalledairfoilandstartGAMBITfromthatdirectorybytypinggam

6、bit-idairfoilatthecommandprompt.UnderMainMenu,selectSolver>FLUENT5/6sincethemeshtobecreatedistobeusedinFLUENT6.0.ImportEdgeTospecifytheairfoilgeometry,we'llimportafilecontainingalistofverticesalongthesurfaceandhaveGAMBITjointheseverticestocreatetwoedges,correspondingtotheupperandlowe

7、rsurfacesoftheairfoil.We'llthensplittheseedgesinto4distinctedgestohelpuscontrolthemeshsizeatthesurface.Thefilecontainingtheverticesfortheairfoilcanbedownloadedhere:naca4412.dat(rightclickandselectSaveAs...)Let'stakealookatthenaca4412.datfile:2552000-0.000196280.0012414740-0.000247836

8、0.0017593970