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1、614J.AIRCRAFT,VOL.36,NO.3:ENGINEERINGNOTES5Launder,B.E.,andSharma,B.I.,“ApplicationoftheEnergy-Dissipationcofthewingrootchordofthemodel.Thefull-scalelengthofModelofTurbulencetotheCalculationofFlownearaSpinningDisk,”therootchordis240in.Allconditionsweresel
2、ectedbasedonLettersinHeatandMassTransfer,Vol.1,1974,pp.131–138.theavailabilityofexperimentaldata.1Theexperimentconsistedof6Nagano,Y.,andKim,C.,“ATwo-EquationModelforHeatTransportawind-tunneltestofa0.10-scalemodelwithoutstores.FortheinWallTurbulentShearFlo
3、ws,”JournalofHeatTransfer,Vol.110,No.3,purposeofvalidation,thesurfacepressurecoefcientmeasuredby1988,pp.583–589.7theexperimentwasused.Yap,C.R.,“TurbulentHeatandMomentumTransferinRecirculatingandImpingingFlows,”Ph.D.Dissertation,FacultyofTechnology,Univ.of
4、ThegridsweregeneratedfromaCADsourceoftheoriginalge-ometryusingtheGRIDGENsoftware.5ThecomputationdepartedManchester,Manchester,England,UK,1987.8Piccin,O.,andCassoudensalle,D.,“EtudeDansLaSouferieF1DesfromtheoriginalgeometryonlywithrespecttotheengineinletPr
5、olesAS329etA240,”ONERA,PV73/1685AYG,Toulouse,France,andoutlet.Inthecomputation,afreestreaminowconditionwas1987.speciedattheinletfacewiththeoutowcapped.Overlapping9Cook,P.H.,McDonald,M.A.,andFirmin,M.C.P.,“AirfoilRAE2822—gridswereconstructedforthevariousco
6、mponentsoftheF-22air-PressureDistributions,andBoundaryLayerandWakeMeasurements,”craft,viz.nose,fuselage,inlet,wing,andhorizontalandverticalAGARD-AR138,1979.tails.AllgridsexceptthenoseandinletgridswereofHtopology,thenosewasC-Otopology,andtheinletgridswerer
7、ectangular.Theentiremeshsystemwasembeddedwithinabackgroundmeshextendingverootchordlengthsawayfromthebodyinalldi-ComputationalSimulationrections,exceptthespanwisedirection,whichextendedtworootoftheF-22Aircraftchordlengths.Aminimumdistance,1y=cD4:6£10¡5,was
8、usedinthebodynormaldirection,resultinginyCD10atthersty-meshpointabovethesurface.Here,c,isthereferencelengthofthewingEswarJosyula¤andRaymondE.Gordnier†rootchordreferredtoearlier.Solutionconvergencewasassumedforthehig
