m6 机翼模型

m6机翼模型ONERAM6WingFigure1.ONERAM6wing(Fig.B1-2fromreference1.).IntroductionThiscaseinvolvestheflowovertheONERAM6wing.ItwastestedinawindtunnelattransonicMachnumbers(0.7,0.84,0.88,0.92)andvariousangles-of-attackupto6degrees.TheReynoldsnumberswereabout12millionbasedonthemeanaerodynamicchord.ThewindtunneltestsaredocumentedbySchmittandCharpinintheAGARDReportAR-138publishedin1979(Reference1).SomepagesofthereportbySchmittandCharpin(mostlygeometryinformation)areavailableasPDFfiles.Thefollowingpageshavebeenscanned,Page:1,2,3,4,5&6,7,20,38.TheOneraM6wingisaclassicCFDvalidationcaseforexternalflowsbecauseofitssimplegeometrycombinedwithcomplexitiesoftransonicflow(i.e.localsupersonicflow,shocks,andturbulentboundarylayersseparation).IthasalmostbecomeastandardforCFDcodesbecauseofitsinclusionasavalidationcaseinnumerousCFDpapersovertheyears.Intheproceedingsofasingleconference,the14thAIAACFDConference(1999),theOneraM6wingwasincludedin10oftheapproximately130papers!SomeofthepapersusingtheONERAM6wingarelistedasreferencesbelow(Contactmeifyouwishtohaveyourpaperreferenced).FlowDescriptionCurrently,theCFDsimulationsusetheflowfieldconditionsofTest2308ofReference1.Table1liststheseflowconditions.ThesecorrespondtoaReynoldsnumberof11.72millionbasedonthemeanaerodynamicchordof0.64607meters.GeometryTheONERAM6wingisaswept,semi-spanwingwithnotwist.ItusesasymmetricairfoilusingtheONERADsection.Thecoordinatesoftheairfoilsectionatthe(y/b)=0.0planearelistedonPage7andalsoinapictureof[TableB1-1](DownloadAccessiblePDFPlug-in)oftheSchmittandCharpinreport.Thefileairfoil.txtisanASCIItextfilecontainingthesecoordinates.Thecoordinatesindicatethatthereisafinitethicknesstothetrailingedge.ForCFDsimulations,anapproximationisusuallymadeofazerotrailingedgethickness.TheFortranprogramfoilmod.f90waswrittentolinearlyscalethe(z/l)coordinatesnearthetrailingedgesothatthetrailingedgethicknessiszero.ThemodifiedcoordinatesareintheASCIItextfilefoilmod.txt.Figure2showsthegeometriclayoutofthewing.Thisfigureisalsoon[Page38](DownloadAccessiblePDFPlug-in)oftheSchmittandCharpinreport.Table2belowlistssomeofthegeometricproperties.Figure2.GeometriclayoutoftheONERAM6wing(Fig.B1-1fromreference1.).ComparisonDataComparisondataconsistsofpressurecoefficientsatsectionsalongthespanofthewingobtainedintheexperimentperformedbySchmittandCharpinasreportedintheAGARDreportreferencedbelow.Table3listslinkstotextdatafilescontainingthesepressurecoefficientsalongtheloweranduppersurfacesofthewingateachofthesevensections.Thespanwiselocationofthesectionsarespecifiedwithrespecttothewingspan,b.TheaccuracyofthepressurecoefficientmeasurementsatMach0.84wasdeterminedtobe+/-0.02.TheexperimentalpressurecoefficientsarealsoavailableinaTECPLOTdatafile,ONERAb114.tec.ComputationalStudiesTheAIAAPaper97-2010referencedbelowbyManietal.presentscomputationalresultsforthiscaseobtainedusingNASTD(predecessortoWIND)aspartofanassessmentoftheSpalart-AllmarasandSSTturbulencemodels.References1.Schmitt,V.andF.Charpin,"PressureDistributionsontheONERA-M6-WingatTransonicMachNumbers,"ExperimentalDataBaseforComputerProgramAssessment.ReportoftheFluidDynamicsPanelWorkingGroup04,AGARDAR138,May1979.2.Mani,M.,J.A.Ladd,A.B.Cain,andR.H.Bush,"AnAssessmentofOne-andTwo-EquationTurbulenceModelsforInternalandExternalFlows",AIAA97-2010,June1997.