NASA NACA-TN-1468-1947 Low-speed static stability and damping-in-roll characteristics of some swept and unswept low-aspect-ratio wings《一些扫掠和非扫掠且低展弦比机翼低速静态稳定性和滚转阻尼特性》.pdf

《NASA NACA-TN-1468-1947 Low-speed static stability and damping-in-roll characteristics of some swept and unswept low-aspect-ratio wings《一些扫掠和非扫掠且低展弦比机翼低速静态稳定性和滚转阻尼特性》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TN-1468-1947 Low-speed static stability and damping-in-roll characteristics of some swept and unswept low-aspect-ratio wings《一些扫掠和非扫掠且低展弦比机翼低速静态稳定性和滚转阻尼特性》.pdf（25页珍藏版）》请在麦多课文档分享上搜索。

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2、calLaboratory.- LangleyField,Va.WashingtonOctober1947. ,._,= . _. .=,w-. -.- -=. _- ._, ._.- - . .,-+.-.+“+-.- -5, - .-.LANGLEYMEMORIALAQONAUTICtia71 LAWXMT(3EYProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-/i -.-:. IW.TIONALAmIsmYCcm4mTmFORAERONAUT

3、ICSTK2WCW”ioii!liO.c1468 -.L., .LOW-SPEEDSTATICSTABXHTYANDDAMPING-IN-ROLLCHPJUCTERISTIC!SOFSOMESWEPTAND, UNSWEPTLOW-ASPECT-TLATXOWINGS r-ByLotisP.Tosti .,SUMMARYAninvestigationatlowspeedtodeterminethestaticstabilityanddamping-in-rollcharacterietisofnuatmroflow-as-pect-ratio. wingsticlwMngsweptwingso

4、fqprox5mat63whereasthetriangularandpt t8red-S h nerdshowedareductionofdampinginpollwithincreasingU,ftcoefficientandfilsou casesbecameunstablebeforemsximmliftwasreached.Thedampinginrolldecreasedaexpectedwithaspectratio.3Xperi-mmte,lvaluesofthem%Iricl.udedforcomparison.Ml.forceHandnomentswhicharedefl-

5、nedi.nfigureWOi6ref erridtO1. !L1X3rollfn!g,thestabilityaxas- “yawti,andpttchinaerodynamic.chord.hcorrooi.ons”forthepffectsoftheJetbounfeetchord,feetmeanaerodynamicchord,feet,W=)rmt chord,feettipchord,feetM Of SWOEICliofquarter-chordMne ofwing,degreestaperratio (+J.-,.angleof.attack,deglxmsangl.9. o

6、f., y-ax, degree a ,.-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-IVACA-TNNOc1468baspectratio()-5-()Id.ftlliftcoefficient0Dragdragcoefficient_Cpitchti.rymontcoefi%ciertrolling-momentcoefficient(-Roll)molllent(?+:3yawing-momntcoefficient-.rolltnga

7、ngularvelocity,radianspersecondrolling-anlar-velocityfactorofhelixanEJegemrated%ywingttpinroll,radiansrateofchangeofrolling-momentcoefficientwithrofii-a71acl.0angular-vqlocityfactorgrateofchangesideslipinrateofchangesideslipinofrolling-momentcoefficientwithangleofP) tdegreesofyawing-mortmxbooef*fici

8、en*withangleofde-es r)$“()*lift -curveslopeaiL -.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 .Foroeanddamping-in-rolltowttiwere”madeoneachcfthe18w-describedintable1. InordertofailttatotheW3.Wcons”bruc+d.on,mostofthelow-aspect-ratiowiri,gswereof

9、flat-plateairfoilsoction,foryastexperiencehasshownthata%lowasstYatiostapproximak”o1?orless)thechoioeofairfoilshaslittleeffectontheaerodynamiccharacteristicsof.=wtig.Theometricdihedralofthomoanthiclmeaslinewaszeroforallofthewingsexceptwings4and6,.-whichhad-0.6end-19dihedral,”m electively.Theforcetest

10、sweremadeonthesix-componentTala.nceoftheLangleyfree-flittunnel,Foracomplbtebmn?iptlonof*hobalanceandtunnelseereferences2and3,respective.y.) Thetestsconsistidofmeasurementsthroughar- ofazieofattackfromsmallnoativeanglesthrough“theangleofmaxiru.igMftwithemglmsofyawof0,“,L3.M-”.:JTm.valuesoftheIatel%l.

11、stabilityderivatims-Clp U Cq weredetorm1A.ect ., -, .,.” r.,.-,- -I- .-.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATNNO.1468RElmuLNms1.Zimmerman,C.II.:CharacteristicsofClarkYAirfoilsofSmallAspectRatfcm.NACARep.No.431,1932.2,3.4*5*6,.8.9910.S

12、hortal.,JosephA.,endIlrapeP,JohnW.: Free-Flight-TunnelInvestigationoftheEffeetoftheFuselageLengthandtheAsyectRatioendd3zeoftheVerttc”alTailonLateralStabilityandControl.NACAARRNo,3D17,2943.Shortal.,JosephA.,andOsterhout,ClaytonJ.: PreliminaryStahilltyandControlTeeteintheNACAFree-FlightWindTunnelandCo

13、rrelationwithFull.-ScaleFlightTests.NACAINNo.810,1941a71Zitierman,C,H+: PreliminaryTestsintheN.A.CCA,Free-SpinningWindTunnel.NACARep.No.557,1936.Bennett,Ch-arlesV.,andJohnson,JoeephL,: ExperimentalDeterminationoftheDampinginRollendAiLeronl?oX1.ingEffectiveness.ofTheeWingsEaving2,42,and62Sweepback.NA

14、CATNNo.1.278,1947.LangeandWacke:PrllfberichtUber3-und6-KomponentenmessungenenderZuspitzungoreihevonFlllgelnkleinerSt.recg.Teilberi.cht:llreleckflel.UMNr.1023/5,DeutscheLuftfahrtforschung(B6rlin-Al,dershof),1943.(AvailableagNACA No.u76.)Swanson,RobertS*andCrandall,Stews D 300 .5 Q9 Q 1.00.K o/0 o .50

15、5 0II A ,.3.00 0 449/? A go o 56.313 A /.00 o 7L6-/4 A- .50 0 Hzgl.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.,-,.; -.6II I i)n I+”/J/eImgure12.-Vs.riationofdamphg-in-rollparameterwitiaspectratioatCL O forwjngs8to18andatmaximumvaluesofdampinginroll forwings1to7.(Wings1to18ofTable1.)sProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-