NASA NACA-RM-L52K19-1952 Aerodynamic characteristics of two delta wings at Mach number 4 04 and correlations of lift and minimum-drag data for delta wings at Mach numbers from 1 62.pdf

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1、aRESEARCHMEMORANDUM=AERODYNAMICCHARACTERISTICSOF TWODELTA WINGSATMACHNUMBER4.04AND CORRELATIONSOF LIFTAND MINIMUM-DRAGDATA FOR DELTA WINGSAT MACHNUMBERSFROM 1.62TO 6.9By EdwardF. UhnannandRobert W. DunningLangleyAeronauticalLaboratoryLangleyField, Va. a71,.RECEIPTSIGNkTURZREQUIREDCD DoCUMENTNAFOR AE

2、RONAUTICSWASHINGTONDecember23, 1952.sProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECHLIBRARYKAFB,NM IN NACARM L5QK19Iilllllllllllllllllllllllllln1443tia:-:. . .NATIONALADVISORYCOMMITTEEFORAERONAUTICSRESEARCHMEMORANDUM.AERODYNAMICCHARACTERISTICSOF

3、TWODELTAWINGSATMACHNUMBER4.04ANDCORRELATIONSOFLIFTANDMINIMUM-DRAGDATAFORDELTAW3iiGS.ATMACHNUMBERSFROM1.62TO 6.9ByEdwardF. UlmannandRobertW. DunningTestsweremadetodeterminetheaerodynamiccharacteristicsatMachnumber4.04oftwodeltawingsof.aspectratio2.31with 8-p=nt-thickdouble-wedgeairfoilsectionshavingt

4、heirmaximynthicknessesat18and60percentchord.ThesetestswereconductedintheLangley9- by” “9-inchMachnumberhblowdownjetata Reynoldsnumberof 6.o X 106,basedonthemodelmeanaeroamic chord.TheresultswereanalyzedtogetherwithresultsobtainedatlowerMachnumbersintheLangleyg-inchsupersonictunnelandatMachnumber6.9

5、intheLangleyn-inchhypersonictunnelfor-thesameandsimilarwings. Theanalystsindi-catedthattheconclusioninNACARML7, whichstatedthat,onthebasisofthedataatlowerMachnumbers,forwingsofthesamefamilytheratiooftheexperimentallift-curveslopetothetheoreticaltwo-dimensionallift-curveslopewasrelativelyindependento

6、fMachntiber”foranygivenvalueoftheratio tan6/tanm (where6 isthewingsemiapexanglegnd m “isthefree-streamMachangle),wasalsovalidatMachnumber4.04. Itwasalsofoundthat,fordouble-wedgedeltawingshavingthessrnemaximum-thiclmess.location,theproductofthe.-, 4.M2- I. (whereMexperimentallyderivedpssuredragaiii i

7、sthe(t/c)2 .-. .-. free-streamMachnumbernd t/c istheairfoilthicknessratio)wasrelativelyindependentofMachnumberfor givenvalueof,t6/t.m -:_.to”establishtheperformanceatMachnumber4.04ofa numberofrelatedwingsof.particularinterestinthisspedrangesgd,qe”co.nd,todeveloyifpossible,meansofcorrelationwith.the”

8、availableresultsforothersupersonicMachnumbers.Inthisprogramtheeffectsofplanform, thicknessratio,maximum-thicknesslocation,andleading-andtrailing-edgeprofilesonwingforce.characteristicsarebeinginvestigated.Thisreportpresentstheresultsobtainedfortwo8-percent-thickwingsofthisprograqwhichdifferedonlyint

9、hepositionofmaxi?nuul.“thickness.Oneofthesewingswasidentical.toawingpreviouslyinvestigatedatMachnumbersof 1.62, 1.92,and2.40intheLangleyg-inchsupersonictunnel(ref.1). Also”presentedforIEomparisonararecentlyobtainedpreliminaryresultsfortheseandsimlarwingsfromtheLangleyg-inchsupersonictunnelandfromthe

10、Langleyn-inchhyper-sonictunnel(Machnumber6.9). Thesenewdata,togetherwith.thepub-lishedresultsinreferences1 and2,areanalyzedand-discussedbrieflywitha viewtowardestablishingcorrelationcriteria.-SYMBOLSCLCmCDCbLiftliftcoefficient, ,=.qspitching-momentcoefficient,Pitchingmomentaboutwingcenterofarea qscr

11、 dragcoefficient, . .=wing-rootbending-moment.coefficientl Bendingmomentaboutwingnot duetolift.q$ angleofattack . -.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACARM L52.K19 3.”free-streamdynamicpressure.semispanwingarchwingspanwing-rootchord2cr

12、 ,-wingmeanaerodynamicchord,7ratioofwinglifttowingdrag lift-curveslopeatzeroangleofattack -wingsemiapexanglefree-streamMachangle .free-streamMachnumberReynoldsnumberbasedon Gairfoilthickness-ratiodragcoefficientat zerolift:- -.C%i,CDP pressure-dragcoefficient,cDmin-Theoreticalskin-friction-dragcoeff

13、icientAPPARATUSAND”TESTS .ThetestswereconductedintheLangley9-by 9-inchMachnumber4blowdownJet;thisfacilityisdescribedanditstest-sectionflowcali- .brationispresentedinreference3. Thesettling-chsmberpressure,which -.washeldconstantby a pressure-regulatingvalve,andthecorrespondingairtemperaturewereconti

14、nuouslyrecordedonfilmduringeachrun.An . .-.externalside-wall-mountedstrain-gagebalancewasusedtomeasurethe “- ._normalforce,chordforce,pitchingmoment,andwing-rootbendingmomentofthemodels.Themodelsweremountedthroughabourkkqy-layerbypass -:.-plate(seefig.1)whichwasfarenoughoutinthestreamtobypassthe .Pr

15、ovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4-. .NACARM L5=19tunnel-wallboundarylayer.Thedimensionsofthes“emi6anmodelsaregiveninfigure2. Themodelsweremadeofsteelandhadsharpleading“andtrailingedgesandridgelines. .-Balancedeflections.underloadnecessi

16、tatedaboutO.10-inchclear-anceallaroundthemodelsattherootchord.Forcete=tsofa rectan-gularwingequippdw.ithpressureorificesonjtssurfacejustoutboard=andinboardof-thegapatthewingrootshowedthatairflowinandoutofthisO.10-inchgapcausedlargechang”esin.thewing-surfacepressuretiataiglesofattack,whichcausederron

17、eousfandmomentsand .computingtheaerodynamiccoefficientsandthece”nter-o-pressureloca-tionshavebeenevaluated.Theprobableuncertaintiesb thedataare -listedbelow.Thecenter-of-pressureuncertaintiesrefertothecentersofpressureobtainedby theslopemethod. -a,deg. . . . . . . . . . . . . . . . . C. . . . .+o.oC

18、L. . . .: . . . . . . . G a71 . , . . . , . . . . . *0:005CD. . . . . . . . . . . . . . :. . . . . . . . . . . . . -*0.001Cm. . . . . . . . . . . . . . . . . . . . . . . . . . . . . , *0.001Cb. . . . . . . . . . . . . . . . . . . . . . . . . . . . o.oo15Chordwisecenterofpresstie,percent? . .=. . . .

19、 a71 . . . il.Spanwisecenterofpressure,percentb/2 . . . . ,:;theratiowasrelativelyindependentofMach:thusitisindicatedthatthefirstconclu- -sionofreference1 appliesatMachnumbersashigh_as.=4,0.Thepre- . .-”=liminarydatafromtheLsiey9-inchsupersonictunnel-on8-percent- .lathickdeltawing5withtheirmmimumthi

20、cknesses.at50Percentchord -thedataobtainedatMachnumber4.04onthedetawiwith itsmaximum .-thicknessat60percentchordalsofa11ofia singlecej sothatthis, “= :=correlationprovidesanotherex:.at60percent.-chordisonly5 percentgreaterthanthelift-curve.slopeofthewing .1”.:.“-:withmaximumthicknessat 18.percentcho

21、rd?Movingthe-maximg.g”t.hick;.:.-E-nesstowd thereardid,however,hate-a ltieeffect.Mtheminimumdragcoefficient,decreasingitby 50percent”(fig.6)Liftdatawe .:- availablefromreference-2 atMachnuniber“6.9.fora 5-pcent-thick -*-deltawingofaspectratio2.31”with.double-wedgeairfoilsectionhavi_ , : itsmaximumth

22、icknessat50percentchord.Theflbwovibiswing.s”_. :.;largelytwo-dimensionalandthevalueoftheiift-curveyiiopeisalmostequaltothelinear-theorytwo-dimensional”value“( tanE F see”fig.10at = 3.9 a71tanm_.Figme6shows“that”the”linear-theorypredictionof.mimumdrag .“ “.”“-1+.,coefficient,”wi”thits-unrealisti”c.dr

23、agpeaksskin-friction-dragc.oefficie”ntandthequ:tosome,extent.ID30,1951. .4.Chapman,DeanR.,andRubes,MorrisW.: Temperateand.VelocityProfilesintheCompressibleLaminarBmindaryLayFrWithArbitra”Distribution.ofSurfaceTemperature.JourAero.SCi.,vol.16,no.9, Sept. 1949,-pp.547-565.” “:”: “” “” :“-”. +- -.-. .,

24、. .- i=,_ .: =,:-5.Rubesin,MorrisW.,Maydew,Randall.C.,”andVarga,-StevenA.: AnAnalyticalandExperimentalInvestigationoftheSkinFrictiono .1,1 IIAir flow :IIi9 I 11i I+ 4.04coefficientsandlift-dragratios.coefficientsfor8-percent-thckdeltawingsi10 basedonmeanandReynolds.nuniber6.o1x-. ., -at ._.,.-U-. .

25、. . . - -=.?r. .=-:-T-. .: -.- -;-.-.-. - -.,.=r -. .-,.-. . . . .- ,-e ,. . *7.aerodynamicchord.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACARML52JS19 13.,-1=16 -12 -8 .-4 0 4 8 12 16Angieofattack,a,deg(c) Wing-robending-momentcoefficient.509

26、)-16 -12 -6 -4 a 4 8 U?! 16(d) Chordwise.-.,“:._hgleofattack,u,d+ .-centerofpressure. .“.=(e) Spanwisecenterofpressure. mFigure4.-Concluded. -. -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.wing t/c (WJmx01II: Lineartheoryref.B.Ref.1 . -1- -. -2

27、3 4 5Machnumbertan cltana+ Figure5.-Lift-curveslopesat zero angleof attackdeltawings with double-wedgeairfoilsectlormatto 6.9. ,: , =s=,1R =6.OX 106Linear theory Lineartheoryformi.ng Ref.2W- II ofref.2. R = 0.58x 106.3 4 5 6 7MachnumberL , I 1 1 I I 1 I .5 1.0 1*5 2.0 2.5 3.0 3.5 4*Otan cltanmgure 6

28、.-Drag coefficients at zero angle of attack for aspect-ratio-2.31delta wings with double-wedge airfoil sections at Mach numbers from 1.62to6.9.I , ,1E!IiU3GProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .81, I Iuction IWb.lg t/c(co .18Ii : .60: ,.

29、05 .50.Ref. “2fi“6R =6x10Machnumber,L , , 1 , , 4 Io .5 1.0 1.5 2.0 2.5 3.0 3.5 h.0tan c/tanEFigure 7.- Maximumlift-drag ratiosfor aspect-ratio-2.31deltawith double-wed airfoilsectionsat Mach numbersfrom 1.62,tingsto6.9.Provided by IHSNot for ResaleNo reproduction or networking permitted without lic

30、ense from IHS-,-,-,. , #Loz,7C8 I I I I I I -/ &.-i-4-/ . . =is=/() Machnumberc amax1.62 1.92 2.40 L Q 6.9 Smrcaq .: A v D Refereace10 lhia paper.09 :50 p .q Prelim. data frm I&ngle.($ .609-inch supersonictunnelyEl This paper. .50 0 Re.ferense2I 1“ten c/tanuFigure 10.- Ratio of the measuredlift-curv

31、etwo-dimensionallift-curveslopesat zerowings with double-wedgeairfoileections.slopesto the theoreticalangle of attackfor deltaProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-U_k & Mmhmmbera a .62 1.922.Ilo4.dl6.9 &urce.C8 .X3 A v Da71OB .18 Rafemumx

32、1016. ?hlspsper.Ca .la PreUn.datafl%mIallg11-inohper80nlctumel.Oa .50 v w Preklm.datefrcaIanglela71C9 .&) 9-* Qereoniotuulela75.05 so o Ref.2YfisFrh. date1208 vDL Elco 1 2tm c/tin mFigure 11. - Correletionof the experimentalWIUgEwith double-wedgeairfoilGectionsto 6.9.sProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-