FLUENT软件在飞机进气道内流的应用

FLUENTFLUENTFLUENT/FLUENT,,FLUENT1CFDFLUENTNSFLUENTFLUENT2patch1/2/110,-1996YF22/120[1]345177FLUENTFLUENT3NSκ-ε64PCCPU733MHZ5560CPUM=2.0α=078M=2.091011121415[2]CFD517824[1]Tornado[3]CFDFLUENTFLUENTFLUENTM=2.0M=2.00.009[1][4][5][6]16-18190.0096FLUENT,,2000600F/A-18CIBMSP232CPU10G5[7][1]BrianD.Goble,ScottKing,JimTerry,andMikeSchoop,InletHammershockAnalysisUsinga3-DUnsteadyEuler/Navier-StokesCode,AIAA96-2547[2]L.H.Bangert,C.E.Johnston,M.J.Schoop,CFDApplicationinF-22Design,AIAA93-3055[3]E.L.Goldsmith,J.Seddon,PracticalIntakeAerodynamicDesign,1993[4]IsmailO.Hindash,RobertH.Bush,andRaymondR.Cosner,ComputationalModelingofInletHammershockWaveGeneration,AIAA90-2005[5]JoongkeeChung,ComparisonofCompressorFaceBoundaryConditionsforUnsteadyCFDSimulationsofSupersonicInlets,AIAA95-2627[6]DonaldFreund,MiklosSajben,ExperimentalInvestigationofOutflowBoundaryConditionsUsedinUnsteadyInletFlowComputations,AIAA97-0610[7]RobertF.Tomaro,FrankC.Witzeman,andWilliamZ.Strang,SimulationofStoreSeparationfortheF/A-18CUsingCobalt60,JournalofAircraft,Vol.37,No.3,May-June2000179FLUENTFLUENT1/2180FLUENTFLUENT3450.00100.00200.00300.00130000140000150000160000170000180000M=2.04Curve1Curve2Curve3Curve4Curve56M=2.072M=2.0181FLUENTFLUENT810M=2.09M=2.0182FLUENTFLUENT11M=2.0183a(b)12M=2.010(a)(b)13M=2.0FLUENTFLUENT(a)(b)14M=2.013(a)(b)0.600.700.800.900.700.800.90(1998)(2000)15M=2.016184FLUENTFLUENT171819185