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1、固體火箭技術(shù)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超聲速進(jìn)氣道快速CFD
5、數(shù)值模擬計(jì)算方案蔡飛超,陳鳳明,徐東來,楊茂(西北工業(yè)大學(xué)航天學(xué)院,西安710072)摘要:根據(jù)進(jìn)氣道內(nèi)部流動特征,并結(jié)合現(xiàn)有工程設(shè)計(jì)經(jīng)驗(yàn)和試驗(yàn)結(jié)論,提出從進(jìn)氣道喉道段出口截面截?cái)?簡化取其超聲速擴(kuò)壓段和喉道段與其外部流場統(tǒng)一構(gòu)造出具有單一性態(tài)超聲速流動的流場計(jì)算域,既縮減了CFD數(shù)值模擬的計(jì)算規(guī)模,又提高數(shù)值計(jì)算的收斂性。經(jīng)實(shí)例計(jì)算分析表明,解算速度和效率大大提高,單個計(jì)算工況僅需時不到20min即可快速完成求解,并可基于數(shù)值計(jì)算模型提取出進(jìn)氣道捕獲流量和最大總壓恢復(fù)系數(shù)等全部主要性能參數(shù),特別適合于在超聲速進(jìn)氣道方案設(shè)計(jì)階段用來快速進(jìn)行性能評估和方案選型,有利于提高設(shè)計(jì)效
6、率,縮短研制開發(fā)周期。關(guān)鍵詞:超聲速進(jìn)氣道;計(jì)算流體力學(xué)(CFD);數(shù)值模擬[1]1Introductionnough.Essentially,CFDtechniqueisananalytictoolFixedgeometrysupersonicinle,twhichisacompro-insteadofadesigntoolbecauseitcanonlybeusedine-miseddesign,iscommonlyusedinexistingductedrocketvaluatingexistingdesigns.Additionally,itisnotaneff-if
7、ormissiles.Itsinnerflowfieldnotonlycoverssubsonic,cientwaytoperformdesignevaluationsolelyonCFDca-ltransonicandsupersonicregimes,butsubjectstostrongculationsduetolargecomputationcostsandtime.shockwaveandboundarylayerinteractions,whichareEspecially,enginee
