NASA NACA-RM-A51H02-1951 Lift drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds - plane triangular wing of aspect ratio 3 with NACA 0003-63 secti.pdf

1、._mcdmtz- COPY$f3,RM A51H02,-_ j . . ,:- “z!/k-RESLIFT,EARCHMEMORANDUIV(-DRAG, ANDPITCHINGMOMENTOF LOW-ASPECT-RATIWINGSAT SUBSONICAND SUPERSONICSPEEDS-PLANE TRIANGULARWINGOFASPECTRATIO 3WITHNACA 0003-63 SECTIONBy JohnC. HeitmeyerAmes Aeronautical_.-,. LaboratoryCmf.NATIONAL ADVISORY COMMITTEEFOR AER

2、ONAUTICS fWASHINGTON “September 13,1951 - - f Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-WA RMA51H02* mmmAL AIJvIsaRYcoMmTmEImAERoNmTIcsdRE3EARCHMEmRmmMLIFT,DRAG,ANDFITCHIiYGMOMENTOFLOW4SHECT+A.TIOWrmsm SI%6SONICANDSm!ERsomcSPEEDS-EL/WETRIANGULA

3、RWINGCIEASEWCTRATIO3WITHI?ACA000343 SECTIONByJohnC.HeitmeyerSUMM4RYAwinodycombinationhavinga plane. trianguls!rwingof8SCtratio3 andNACA000M3 sectionsinstreamwiseplaneshasbeeninvesti-gatedatbothsfisonicandsursonicMachnunibers.Thelift,drag,anda71 pitchingmo=ntofthemodelarepresentedforMch nunibersfrom0

4、.60to().92andfrom1.20to1.70ataReynoldsnturiberof4.80minim. ThevariationsoftheCharacteristicswithRepoldsnuniberareelsoshownforseveralMachnmibers.INTRODUCTIONA researchprogramisinprogressattheAms AeronauticalLabora-torytoascertainexperizmntallyatsubsonicandsupersonicMachnuuibersthecharacteristisofwing

5、sofinterestinthedes:gnofhigh-peedfighterairplanes.Theeffectsofvsriationsinplanfmm, twist,c-her,sadthicknessarebeinginvestigated.This rea iS one ofaseriespertainingtothisprogramandpresentsresultsoftestsofaWinmdycombinationhavingaplanetriangularwingofaspectratio3andHACA0003-63sectionsinstreamuiseplane

6、s.Resultsofotherinves-tigationsinthisprogramarepresentedinreferences1to10.Asinthssereferences,thedatahereinm?epresentedwithoutanalysistoeqeditepublication.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2NOTATIONNACARMA51H02bc2LD(LLDMqRrosxYawingspan

7、()b/2meanaerodynamicchord zolocalwingchordlengthofbodyincluding“portionremovedtoaccommodatestinglift+.rag ratio a71maximumlift-drag ratioWch numberfree-stream dynamicpressurea71Reynoldsnumberbasedonthemeanaerodynamicchordradiusofbody *maximumbodyradiustotalwingarea,includingareafarmedbyextendinglead

8、ingandtrailingedgestoplaneofsymmetrylongitudinaldistancefromnoseofbodydistanceperpendiculartoplaneofsymmtryangleofattackofbodyaxis,degreesdragcoefficient()p()liftcoefficientpitchinllomentcoefficientreferredtoaerodynamicchord(pit Ching momentqsE )quarterpointofmean .Provided by IHSNot for ResaleNo re

9、production or networking permitted without license from IHS-,-,-cA RMA51H02 3a71 d slopeoftheliftcurvemasuredatzerolift,perdegree .# dCL slopeofthepitchpnomntcurveasuredatzeroliftAPMRATUSWindTunnel andEquipmntTheerimntalinvestigationwasconductedintheAnEx!6-byfig.1) 12.5Cross+ectionshape.C&C*M9.xLmum

10、 cross+ectionalarea,squarefeet 0.1235Ratioofmexfmumcross+ectionalareatowingarea omo50ga71a15Thewingwasconstructedofsolidsteel.Thebc&yspaxwasalsosteelfacesandwascoveredwithaluminumtoformthebodyc&t&rs. Thesur-ofthewingandbodywerepolishedsmooth.TESTSANDIm)CEDmRangeofThecharacteristicsoftheTestVariables

11、. -. model(asafunctionofEuuzleofattack)wereixrvestigatedforarangeofWch &uibersfrom0.60to0.92andfroml.mto 1.70.The,maorportionofthedatawasnmiberof4.80million.Datawerealsoobtained1.92millionand3.08millionatMachnumbersofl.o.The testdatahaveReductionofDatabeenreducedtostandardFactors whichcoultifectthea

12、ccuracyoftheseobtainedataReynoldsforReynoldsnunibersof .0.60,O.m,1.20,anda71NACAcoefficientform.results,togetherwiththecorrectionsapplied,arediscussedinthefollowing&a&aphs.- CorrectionstothesubsmricresultsfortheinducedeffectsofthetunnelWELLSresultingfromliftonthemodelweremadeaccordingtothemthodsofre

13、ference13. Thenumricalvaluesofthesecorrections(whichwereaddedtotheuncorrecteddata)were:Ax = 0.554 QMD = .00967CL2Nocorrectionsweremadetothepitohiomentcoefficients,Theeffectsofconstrictionofthe_flowatsubsonicspeedsbythe&nnelwallsweretaknintoaccountbythemthodofreference14.This correctionwascalculatedf

14、orconditionsatzeroangleofattackandwasappliedthroughouttheangle-of+ubtackremge.AtaMachnuniberc&O.90,thiscorrectionamountedtoarcent increaseintheMachProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.IUX!ARMA51H02 5numberandinthedynamicessureoverthatdete

15、rminedfromacalibra-tionofthewindtunnelwithoutamodelinplace.Forthetestsatsupersonicspeeds,thereflectionfromthetunnelwallsoftheMachwaveoriginatingatthenoseofthebodydidnotcrossthemodel.Nocorrectionswererequired,therefexe,fortunnel-walleffects.Streamvsxiations.-Testsatsubsonicspeedsinthe& by&footsuperso

16、nicwindtunnelofthepresentsynmtricalmodelinboththenor- andtheinvertedpositionshaveindicatedastreaminclinationof-0.050anda streamcurvaturecapableofproducingapitchiemmtcoefficientof-0.004atzerolift.Nocorrectionsweremadetothedataofthepresentreportfortheeffeetofthesestreamirregularityies.Nomeaswemntshave

17、beenmadeofthestreamcurvatureintheyaw.plane.“ Atsubsonicseds,thelongitudinalvariationofstaticpressureintheregionofthemodelisnotlmun?naccuratelyatpresent,butapreliminarysurveyhasindicatedthatitislessthan2percentofthedynamicpres-sure.Nocorrectionforthiseffectwasmade.A surveyoftheairstreaminthe6-by&foot

18、windtunnelatsuPr-sonicspeeds(reference11)hasshownastreamcurvature only intheyawplaneofthemcdel.TheeffectsofthiscurvatureonthemasuredchaPacteristicsofthepresentmodelsrenotknown,butarebelievedtobesmallasjudgedbytheresultsofreference.15.Thesurvey(reference11)alsoindicatedthatthereisastatiepressurevaria

19、tioninthetestsec-tionofsufficiexrtmatudetoaffectthedragresults.A correctionwasaddedtothe=asureddragcoefficient,therefore,toaccountforthelongitudinalbuoyancycausedbythisstatic-pressurevariation.Thisc-erectionvariedfromasmuchas-0.0008 at a Wch n-r of 1.30 to O.0W6ataMachtier of1.70.&pmortint.- Atsubso

20、nicspeeds,theeffectsofsupportinterferenceontb aerodynamiccharacteristicsofthemdelarenotlalown.Forthepresetitaillessmodel,itisbelievedthatsucheffectsconsistedprimerilyofachangeinthepressureatthebaseofthemodel.Inanefforttocorrectatleastpartiallyforthissuortinterference,the basepressurewasmasuredandthe

21、dragdatawereadjustedtocorre-spondtoabasepressureequaltothestaticpressureofthefreestream.Atsursonicspeeds,the effectsofSUX imterfe”nceofabody-stingconfigurationsimilsrtothatofthepresentmodelereshownbyreference16 to be confined to a changein base pressure. ThepreviouslymntionedadJustmzrtofthedragforba

22、sepressure,therefore,wasappliedatsupersonicspeeds.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 NACAEMA51H02REsuLmTheresultsarepresentedinthisreportwithoutanalysisinordertoeditelication.Thevariationofliftccefficientwithangleofattackandthevariatio

23、nsofdragcoefficierrt,pitchientmt coeffi-cient,andlift+ragratiowithliftcoefficientataReynoldsnumberof4.&lmillionandatMch numbersfrom0.60tol. areshuwninfigure2.TheeffeetofReynoldsnuniberontheaerodynamiccharacteristicsatMachnuaibersof0.60,0.$)0,1.20,and1.70isshowninfigure3. Theresultspresentedinfigure2

24、havebeensummarizedinfigure4toshowsomimportantparamtersasfunctionsofMachnuziber.Theslopeparsmtersinthisfigurehavebeenmasuredatzerolift.AriesAeronauticalLaboratory,HationalAdvisoryCommitteeforAeronautics,MoffettField,Calif.REmmNcEsa711. Smith,DonaldW.,andHeit=yer,JohnC.: Lift,Drag,andPitchingMomntofLo

25、w=Aspc=atioWingsatStisonicandSupersonicSpeeds-PlaneTrisngulerWing of AspectRatio 2WithwCA 8-63Section.N/MARMA50K2Q,1951.-2. Smith,DcmaldW.,andHeitmyer,JohnC.: Lift,Drag,andPitchingMcmentofLow4specMatioWingsatSubsonicandSupersonicSpeeds- PlaneTriangularWingofAspectRatio2WithNACA00Q5-63Section.NN2ARMA

26、54X21,1951.3. Heitmyer,Jti C.,andStephenson,JackD.: Lift,Drag,andpitchingMomntofLowAspe_atioWingsatSubsonicandSupersonicSpeeds-PlaneTriangularWingof Aswct Ratio4 WithIWM0005-63Section. IWCAm A50K24,1951.4.Phelps,E.Ray,andSmith,WillardG.: Lift,Drag,- pitcMomentofLuw4spect+RatioWingsatSubsonicandSurso

27、nicSpeeds- TriangularWingofAspectRatio4WithNACA000%3ThicknessDistribution,Ca?iberedandTwistedforTrapezoidalSpanLoadDistribution.NACARMA50K2hb,1951.5. Heitmyer,JohnC.,andSmith,WillardG.: Lift,Drag,h PitchiMcmntofLow4spect+latioWingsatSubsonicandSupersonicSpeeds- PlaneTriangularWingofAsctRatio2WithNAC

28、A0003-63Section.RACARMA50K24a,1951.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACARMA51H02 76. Smith,WillardG.,andPhelps,E.Ray: Lift,Drag,andPitchingMomntofLcm+Aspect+atioWingsatSubsonicandSursonicSeds- TriangularWingofAspectRatio2WithNACA000%3H

29、ckness Distribution, Ca-red andTwistedforahazoidalSpanLoadDistribution.NACARMAK27a,1951.7. Reese,DavidE.,andPhelps,E.Ray: Lift,Drag,andPitchingMomntofLuw+lspect+atioWingsatSubsonicandSuprsonicSpeeds- PlaneTaperedWingofAspectRatio3.1 With3-Percent-Thick,BiconvexSection.NACARMA50K28,1951.8. Hall, Char

30、lesF., md Heitmeyer,Johnc.: Uft, Drag, andPitchingMomentof Law+lspect+atioWingsatStisonicandSupersonicSpeeds-TwistedandCaniberedTriangularWingofAspectRatio2WithNACA0003-63ThicknessDistribution.NACARMAlEOlj151.9* Heitmeyer,JohnC.: Lift,Drag,andPitchingMomntofLow4sct-RatioWingsatSubsonicandSupersonicS

31、peeds- PlaneTriangularWingofAspectRatio4With3Percent-hick,BiconvexSection.NACARMAID30,151.10.Heitmyer,JohnC.,andHightower,RonaldC.: Lift,Dra&andPitchingMomentofLow4sct+atioWingsatSubsonicandSupersonicSpeeds- PlaneTriangularWingofAspectRatio4With3-Percent-ThickRoundedNoseSection.NACARMA51121,1951.I-1

32、.Frick,CharlesW.,andOlson,RobertN.: FlowStudiesintheAss-mtricAdjustableHozzleoftheAms 6-by6footSupersonicWind5el. N4CARMAz24, 1949.12. Olson,RobertN.,andMead,MerrillH.: AercjmamicStudyofaWigFuselageCoMIMnationEmployingaWingSweptBack63. Effective-nessofanElevenasaLongitudinalControlandtheEffectsof(%m

33、herandTwistontheI&ximmLift+ragRatioatSupersonicSpeeds.NAC!ARMA50A31a,1950.13a71 Glauert,H.: Wind-TunnelInterferenceonWings,BodiesandAir-screws.R.&M.No.1566, British, 1933.14.Eerrlot,JohnG.: BlockageCorrectionsforl!hree+imensional+?lowCloqed+l%roatWindTunnels,WithConsiderationoftheEffeetofCompressibi

34、lity.NACARep.995,1950.(FommrlyNACARMA28)15. Lessing, HenryC.: AerodynamicStudyof a Win&!?uselageConibinationEEoyinga WingSweptBack630- Effect ofSidesliponAerodynamicCharacteristicsataMachIhuEberof1.4WiththeWingTwistedandC-red. NACARMA5Cn?09,1950.Provided by IHSNot for ResaleNo reproduction or networ

35、king permitted without license from IHS-,-,-816. Perkins,EdwardW.: ExperimxdmlInvestigationoftheEffectsofSupportInterferenceontheDragofBodiesofRevolutionataMch Ibiberof1.5.NACATM2292,1951.(Frly MICARMA8B).Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,

36、-,-. rEquotien of fuselav radii+!wAll dimensionsshownin inahesr .-(III)-. ./ . IZ32+2i.58 k 46.93.3- -*- 1,Figuret. - Front and plan viewsof the model.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10 I?ACAm A51m2.6.7.6.5.4.3J?.10-./-.)?-3:46 -4 2 O

37、 2468 /0 for M = 0.60Angle of attack, a, deg(o) CLVSaFiguret?.- The variation of the aerodynamic chara cteristlcs with Ilf tcoefficient at various Mach numbers.Reynolds number, 4.80 million.“.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.*I!TACARM

38、A5m2 9 11.8.7.6.5.4i I I c1 1 1 I I I r I I VI I G1Iw 1 $ I A If+111(Jw I I 1/ dd rI f / d w-.3/ Mm ooo323QEkmewing-.4.04 0 -.04 .08 -./2./6for M = O. 60Pitching-moment coeft7cient, Cm Figure 2.- ContinueProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-

39、,-12 NACARMA5113)2.(c) csG*figure 2.-Continued. .-. .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . K , . *1614l.?-$0.$ 8:bb6$4420-t?-J o .1,2 .3 .4 .5 fw MU 0.60Lift coefficitw d) /0 VS Fipre 2.- Cciwlufed.,Provided by IHSNot for ResaleNo repro

40、duction or networking permitted without license from IHS-,-,-Drag coefficient, C. Pitching- moment coefficient, C-10 -8 -8 -4 -2 0 246 8 10Angle of attack, a, degb) M= 0.60Fire 3.- The variation of the oerodynomic chorooterktics with fif coefficient ot vorfous Reynolds numbers.* .Provided by IHSNot

41、for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . .8 E.7 ii&=.6Em.5.4G. 3fII&2ezw“ t%-1.0II-J:2:3:40 . .04 .06 .08 JO .i2 .08 .04 o -04 -m tif?Drag coefficient, C, Pitching- moment coefficient, Cm6_4-P 0246 eioAngle of attack, a, deg(b) M= 090Figure 3.- Continued.G

42、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4N&4 GW3+3.:Q%.eoQ$4Drag coefficient, Go Pitching-m on?ent co8fff”cient, Cm-8 -4 -2 0 2 4 6 8 10Angle of attack, K, defl. .(C) kf= 1.20Figure 3.- Continued. .IProvided by IHSNot for ResaleNo reproductio

43、n or networking permitted without license from IHS-,-,-wq .10-J-2730 .02 .0+ .06 .08 .10 ,08 .04 0 .04 -.08 ,f2 -.16 .20.Drag coefficient, Co itch:g,- yornent coefficient, &6 4 /? O 2 4 6Angle of attack, , deg(d) #f= 1.70Figure 3.- GOncIUdedProvided by IHSNot for ResaleNo reproduction or networking

44、permitted without license from IHS-,-,-NACARMA51K)2.fo.08 -4 . ,ma 0003-s3P&m wing.06 /.04.02-I06 .2 .4 .6 ,8 10 U 14 /6 18.MuchnumbeM(u) Vs M.Mach numbeM.Figure4.- Summqy of oerodynumicchmzferistics os u function of Much numbeReynoldsnutnbe4.80 tnilfon.u.Provided by IHSNot for ResaleNo reproduction

45、 or networking permitted without license from IHS-,-,-NACA A51KX2 “ 19/6/4+ - A“ /2NXA 0003-63Plmewing !0$8640 .2 .4 .6 .8 /.0 12 L4 /.6 /.8Moth number, IV(c) (%) Vs M.ttFigure 4.- Continueo!Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-06c0 0.2.4 .6 .8Mache)Figuie1.0 /.2 /.4 /.6CD w M4.- GoneWed.,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-