直升机旋翼翼型的气动设计方法研究

南京航空航天大学硕士学位论文直升机旋翼翼型的气动设计方法研究姓名：尚克明申请学位级别：硕士专业：飞行器设计指导教师：招启军20090301ICFDPoissonJamesonMGMCFDEulerIIAbstractTherotorairfoilsplayakeyroleintheflowfieldandtheaerodynamiccharacteristicsofthehelicopterrotor.Theadvanceddesignaerodynamicmethodforrotorairfoilshasbecomeanimportantpartofhelicopteraerodynamics.Consideringtheaerodynamiccharacteristicsofhelicopterrotor,aninversedesignmethodforhelicopterrotorairfoilshasbeenestablishedbasedontheiterativeresidualcorrectionprinciple,andthemethodofidentifyingthetargetpressuredistributionisalsoinvestigatedpreliminarily.Themajorresearchworkinthethesisareasfollows:Asthebackgroundofthecurrentwork,theclassicalairfoildesignmethodsandtheircharacteristicareanalyzed,andthedomesticandoverseasresearchresultsareintroducedbriefly.Atlast,itispointedoutthattheinversedesignbasedonCFDmethodisimportantforresearchoftheairfoildesignforhelicopterrotor.InChapter2,throughanalyzingthecharacteristicsoftherotorflowfield,andconsideringtherequirementsofinversedesignmethodonthegrids,astructuregridgenerationmethodaroundrotorbladeshasbeenestablished,whichisbasedonsolvingPoissonequations,andemployingtwotypesofmethodstocalculatethecontrolsourcetermswiththeirmodifications.ThegridsaroundrotorbladegeneratedbythismethodaregivenattheendofthisChapter.InChapter3,basedonthefinitevolumemethodpresentedbyJameson,andanembeddedgridmethodology,acalculationmethodbyEulerequationsforflowfieldofhelicopterrotorinhoverisestablished.Bythepresentmethod,theflowfieldofairfoils,wingsandrotorsarecalculated,andtheeffectivenessofthisflowfieldsolutionisverified.InChapter4,thedifferentdiscretizationmethodsofMGMequationwhichisthegoverningequationintheinversedesignmethodhasbeendeducted,thentheinfluenceofdiscretizationmethodsonthecalculationefficiencyhasbeendiscussed.Toimprovethepracticabilityoftheinversedesignmethod,themethodforconfirmingthetargetpressuredistributionisinvestigatedpreliminarily.CombiningtheCFDandthegridgenerationmethod,aninversedesignmethodforhelicopterrotorinhoverhasbeenestablished.InChapter5,inversedesigncalculationsfor2-Dairfoils,3-Dwing,androtorbladesareperformedrespectivelybyusingthepresentinversedesignmethod.Thentheinversedesignanalysishasbeencarriedoutontherotorbladewithdifferentairfoilscollocationalongitsspanwiseemphaticallytoprovetheeffectivenessoftheinversedesignmethodforthehelicopterrotor.Keywords:airfoil,inversedesign,rotor,Eulerequation,embeddedgrid,finitevolumemethodV1.1..................................................................................................21.2..................................................................................................32.1..........................................................................................................................72.2..................................................................................................................82.3.....................................................................................................112.4....................................................................................................142.5........................................................................................................152.6........................................................................................................................152.7........................................................................................................................162.8................................................................................................................162.9................................................................................................................172.10..............................................................................................................173.1....................................................................................243.2HoleMap......................................................................................................................253.3InverseMap.......................................................................................263.4........................................................................273.5................................................................................................................273.6........................................................283.7........................................................293.8M60.44R..........................................................293.9M60.65R..........................................................303.10M60.90R........................................................303.11M60.95R........................................................303.120.5R........................................313.130.89R......................................313.140.96R..................................323.150.5R....................................323.160.89R......................................323.170.96R......................................33VI4.1...............