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1、固体火箭技术第33卷第1期JournalofSolidRocketTechnologyVo.l33No.12010¹AfastCFDsimulationschemeforsupersonicinletCAIFe-ichao,CHENFeng-ming,XUDong-la,iYANGMao(CollegeofAstronautics,NorthwesternPolytechnicalUniversity,Xia'n710072,China)Abstract:Basedoninternalflowcharacteristicsofinlet,andcombinedwithexis
2、tingengineeringdesignexperiencesandexper-imentconclusions,afastcomputationalfluiddynamics(CFD)modelingandcomputationschemeispresented.ItnotonlysimplifiesCFDsimulationscale,butalsoimprovesnumericalconvergencebyconstructingacomputationaldomainwithsupersonicflow,whichisformedbyunifyingsuperson
3、icdiffuserandexternalflowfieldofthroat.Theresultsshowthatcomputationspeedandefficiencyaregreatlyimproved.Ittakeslessthan20mintosolveasinglecase.Andallthemajorperformanceparameters,includingcapturedmassflowandmaximaltotalpressurerecoverycoefficientoftheinlet,canbeeasilyextractedfromcomputati
4、onresults.Itisespe-ciallysuitableforfastperformanceevaluationandschemeselectionindesignstage,resultinginhigherefficiencyandfasterdesigncycle.Keywords:supersonicinlet;computationalfluiddynamics(CFD);numericalsimulationCLCNumber:V438Documentcode:AArticleID:1006-2793(2010)01-0041-04超声速进气道快速CFD
5、数值模拟计算方案蔡飞超,陈凤明,徐东来,杨茂(西北工业大学航天学院,西安710072)摘要:根据进气道内部流动特征,并结合现有工程设计经验和试验结论,提出从进气道喉道段出口截面截断,简化取其超声速扩压段和喉道段与其外部流场统一构造出具有单一性态超声速流动的流场计算域,既缩减了CFD数值模拟的计算规模,又提高数值计算的收敛性。经实例计算分析表明,解算速度和效率大大提高,单个计算工况仅需时不到20min即可快速完成求解,并可基于数值计算模型提取出进气道捕获流量和最大总压恢复系数等全部主要性能参数,特别适合于在超声速进气道方案设计阶段用来快速进行性能评估和方案选型,有利于提高设计效
6、率,缩短研制开发周期。关键词:超声速进气道;计算流体力学(CFD);数值模拟[1]1Introductionnough.Essentially,CFDtechniqueisananalytictoolFixedgeometrysupersonicinle,twhichisacompro-insteadofadesigntoolbecauseitcanonlybeusedine-miseddesign,iscommonlyusedinexistingductedrocketvaluatingexistingdesigns.Additionally,itisnotaneff-if
7、ormissiles.Itsinnerflowfieldnotonlycoverssubsonic,cientwaytoperformdesignevaluationsolelyonCFDca-ltransonicandsupersonicregimes,butsubjectstostrongculationsduetolargecomputationcostsandtime.shockwaveandboundarylayerinteractions,whichareEspecially,enginee
