NASA NACA-TN-1759-1948 Effect of compressibility on normal-force pressure and load characteristics of a tapered wing of NACA 66-series airfoil sections with split flaps《压缩性对带有分裂式襟翼.pdf

1、)1!IIIIO-Jmc-l-lNATIONALADVISORYCOMMITTEEFORAERONAUTICSTECHNICALNOTENo. 1759EFFECTSOFCOMPRESSIBILITYLOADCHARACTETICS OFAONNORMAL-FORCE,PRESSURE,ANDTAPEREDWINGOFNACA66-SERUMAIRFOILSECTIONSWITHSPLIT FLAPSByF. E.West,Jr., andJ.M. Hallissy,Jr.LangleyAeronauticalLaboratoryLangleyField,Va.=qiJttjij7Washin

2、gtonDecember1948_. . . -. .-.,- , . -. - .- . . . . . . . . . -.I1,:III-)I.II!(,1!IIJ.-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-RACAImTmIwG,ADVISORYCOIWITTEEFORAERONACS_TECHLIBRARYKAFB,NMTECBMICAIINm No.1759 llllllllllll!llllluoob5015EFFECTSOF

3、COMPRESSIBILITYONlWRMAhowever,thisdoesnothaveach effectonthewingnarmsl-forcecoefficientbecausetheoutloardsectionsofthewingcontributea smallerpsrtofthetotalwingnarmalforcethantheinboardsections.Atthehighanglesofattackthenarmsl-farcecoefficientsforthewingwithflapsincreaserapidlyatthehigherMachnmibersi

4、namannersimilmtothatnotedforthewingwithoutflaps.Illfigure7 itcanbeseenthatforMachnnmbersabove0.k85largesupersonicregionsefienciingoverthefarwsrdpartoftheuppersurfaceoccurfcmthewingwithflaps. ThisfigureshowsthatastheMachmniberiEIticreasedfromO.k8to0.535,awell-establishedshockbecomesevidentalongwitha

5、largeincreaseintheareaofthepressuredistribution%AstheMachnumberisfurtherincreasedto0.550,theshockshiftstdwardthetrailingedgeandtheerbentofthesupersonicregionalongthechcmdchangesfromappradmately25to33percentofthechord.Thus,itisappsrentthattheticreasesh thenorml-forcecoefficientsathighMch numbersandhi

6、ghanglesofattackareduetotheformationoflargesupersonicregionswhichcauselargeareaincreasesinthepressuredistributions.Jkximumnormal-fwcecoefficient.TheeffectofMachnumleronmaximumnormal-forcecoefficientforallthreewingconfigurationsandonmsximumliftcoefficientforthewingwithoutflapsisshownhfigure8. Thevalu

7、eofmaximumliftcoefficientforthewingtithout.flapsincreaseswithlwhereasairfoilshavhgbluntlesdingedges,suchastheNACA230series,donotexhibittherise.TheresultsofthepresenttestsoftheNACA66-serieswingwithflapsindicatethessmetypeofvariationofmsximumliftcoefficientwithMachnuniberaswasobtained.withoutflaps.Thu

8、s,itisfurthersubstantiatedthatthephenomenonisessentiaHya leading-edgeeffectascauiber,caliberlocation,and.%aildge. aLe appeartohavelittleornoeffectonthetypeofvariationofmaximumnormal-forcecoefficientwithMch number.Typicalsectionstallingcharacteristics.-Anexaminationofthellcarpet”plotsoffigure5 showst

9、hatthetypesofstallingcanbedividedintothreerepresentativegroups:low-speedstall (M= 0.200),mcderatpeedsta31 (M=0.390),endhigh-speedst (M= 0.535).Inordertogivea clearerunderstandingofthesethreetes ofstalling,pressuredistributionsthatshowtypicalsectiondxiUingcharacteristicsforthefull-spanflapconfigurati

10、onarepresentedinfigures9 to11.Asthetypicalsectionstallingcharacteristicsareshdlarforallthreeconfigurations,awithoutflapsanddimmssionoffigures9 to11alsoappliestothewingtothewingwithpartialpanflaps. . . . - - . . _._ . . . , . .- . .,Provided by IHSNot for ResaleNo reproduction or networking permitted

11、 without license from IHS-,-,-II-2 . NACATNIio.17590 ,ThOlpeed sectionstallischaracterizedbylaminarseparationoftheflowfromtheleadingedge(seereference12)withemabruptstall *andarapidflowbreakdown.tifigure9 thepressureeakscembeobservedtoincreaserapidlywithincreasesinangleofattackuntillargeadversepressu

12、readientsfinallyinduceseparationthatcausesa shaTpflowbredalownattheleadingedge.Itcanalsobeseenthatlittlechangeintradge separationoccursbeforethestall.Themoderatpeedsectionstallwasverydifferentfromthat.observedatluwspeed.Figure10showsthatthemoderatpeedsectionstall0CCW6slowlywithincreasingangleofattac

13、kandisduetotrail-ge sepa-rationgraduallymomlngforward.Thehigthendecreasedtoavalueof,l.53ata Machtier of0.295;andthenremained“constanttoaMachntierof0.4-85af%erwhichitincreasedrapidlytoavalueof1.79ataMachnuuiberof0.585(limitofmaximmnormal-farcetests). 3.Forthewingwithfull-spansplitflapsthe narmal-forc

14、ecoefficientincreasedfromavalueof1.92ataWch numberof0.145toa low-speedpe valueof2. atamch -er of0.2;thendecreasedrapidlytoavalueof1.87ataMachnuniberof0.300;andthenincreasedslowlytoavalueof1.92atakch numberof0.4-85afterwhichitroserapidlytoavslueof2.22ataMachnumberof0.550(limitofmaximumnormal-forcetes

15、ts).4. Thereisfurtherevidencethattherapidriseinmax- liftcoefficientathigherMachnumbersisduetothesharpleadingedgeofthewingascamber,cmiberlocation,andtrailin. .*,., ,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATNNo.1759lm?ERENms.1. Mime,ThomasC

16、.: Some EffectsofReynoldsandWch Nunibersonthe,I&E%ofsnNACA0012RectemgularWingintheNACAl$Xl?ootPressure!hznnd.NACA NO.m, 1943.2. Cleary,H&oldE.: EffectsofCompressibilityonMaximumLiftCoef-ficientsforSixPropHer Airfoils.NACAACRNo.Lk121a,1945.3.Nissen,JamesM.,andGadebwg,BurnettL.: EffectofMachandReynold

17、sNuersonthePower-offlkrlmumLiftCoefficientObtainatileona&39N-1Airme asDeterminedinFlight.NACAACRNO.4F28,1944.4.Rhode,RichardQ.: CorrelationofFlightDataonLhit PressureCoefficientssmdThetiRelationto12SpeedBurblingandCriticalTailLoads.NACAACRNO.L47,1944.5. Pearson,E.O.,Jr.,Evans,A.J., West,F.E.,Jr.:Eff

18、ectsofCompressibilityontheM3ximumLiftCharacteristicsandSpanWiseloadDistributionofal=oopanl?ightee W- ofNACA23(ASeriesAirfoilSectiops.NACAACRNO.L5G10,1945.6. Pesrson,E.O.,Jr.:EffectofCompressibilityontheDistributionofPressuresovera IeredWingofNACA23SeriesAirfoilSections.NACATNNO.1390,1947.7. Furlong,

19、G.Chester,andFitzpatrick,Jua E.: EffectsofI&chIhuiberandReynoldsNumberonthe&ximumLiftCoefficientofaWingofNACA23&SeriesAirfoilSections.NACATNNO.1299,1947.8. Cooper,Morton,andKorychski,PeterI.:TheEffectsofCompressibilityontheLift,Rressure,andLoadCharacteristicsofa TayeredWingofNACA6&%riesA&foilSection

20、s.NACATNNo.1697,1948.9. walI-,NsncYE.: ChordwisePressureDistributionsona 12-Foot-SpanWingofNACA66-%riesAirfoilSectionsuptoaMachNumberof0.60.NACATNNO.1696,1948.10.VonDoenhoff,AlbertE.,andTetervin,Neal:Investigationofthe%riationofLiftCoefficientwithReyaoli!sNuniberataWderateAngleofAttackonaLowDragAirf

21、oil.NACACB,Nov.1942.IlG&hert,B.: PlaneandThre&OWnsionalFluwatHighSubsonicSpeeds.NACATMNO.11, 1946.12.Jacobs,EastmanN.,andSherman,Albert:AirfoilSectionCharacteristicsasAffectedbyVariationsoftheReynoldsNum%er.NACARep.No.586,1937. .- . . . . - -. . . - . . _- - _ . ,Provided by IHSNot for ResaleNo repr

22、oduction or networking permitted without license from IHS-,-,-16 NACATNNO.175913.Stack,John,Fedziuk,HenryA.,m Cleay,old E.: WelmmryInvestigationoftheEffectofCompressibilityontheMaximumLiftCoefficient.NACAACR,Feb.1943.,14.Anon.:SpamwiseAi&kad Distribution.AN&l(l),ArmTavyFigure 2.- Rear view of test w

23、ing with full-span flaps. L?Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.,.,.-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Reswm-a#Jt9 d#bu . “. . . . . . .,. ,:Provided by IHSNot for ResaleNo

24、reproduction or networking permitted without license from IHS-,-,-NACATNRO.1759 29.Ia71.232221201.91.81.7z1.6.+.-.8 v f I I I I I t 1 I I I I I I.7 ,WA1111111-8 -6 -4 -2 0 2 4 6 8 10 2 14 16 18 (MO=0.200)Angleofattack,a,dego .1 2 .5 .6 (cc=09f?ach nuber,MO(c)Wing with full-spanflaps.Figure5 .Concluded., ._ _ . . . . .- - .-. ._-_ .-.-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-