NASA NACA-TN-2495-1951 Wing-tunnel investigation of effects of various aerodynamic balance shapes and sweepback on control-surface characteristics of semispan tail surfaces with NAarc .pdf

1、fJcdacsJ1NATIONALADVISORYCOMMITTEEFORAERONAUTICSTECHNICALNOTE2495WIND-TUNNELINVESTIGATIONOF EFFECTS OF VARIOUSAERODYNAMICBALANCESHAPESANDSWEEP3ACKONCONTROL-SURFACECHARACTERISTICSOF SEMISPANTAIL SURFACESWITHNACA0009,0015, 66-009, 66(215)-014, ANDCIRCUMR-ARC AIRFOILSECTIONSBy JohnJ.Georgia InstituteHa

2、rperof Technology,*1,$Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECHLIBRARYKAFB,NM1llllllllllljppNATIONALADVISORYCOMMITTEEFORAERONAUTICS “”-=-”:-TECEINICALNOTE2495WIND-TUNNELINVESTIGMXCONOFEFFECTSOFVARIOUSAERODYNAMICBAIANCESHAPESANDSWEEPEACKONC

3、ONTROL-SURFACECHARACTERISTICSOFSEMISPANTAILSURFACESWITHNACA0009,0015,66-009,66(215)-014,ANDCIRCUIAR-ARCAIFWOILSECTIONSByJohnJ.HarperSUMMARYA summaryofforcedataonunsweptandsweptbackairplanecontrolsurfacesispre.sented.Liftandhinge-momentcharacteristicswereA determinedforfourunswept,semispcontrolsfaces

4、d lif!drag)-7 hingemoment,andpitchtigmomentweredeterminedfortwosemispsn,sweptbackcontrolsurfaces.Thesecontrolsurfacesweretestedinthe. g-footwindtunneloftheDanielGuggenheimSchoolofAeronauticsattheGeorgiaInstituteofTecbnoiogyandwereofthewide-chordtypesuitableforuseaselevatorsorrudders.Measuredvaluesof

5、thevariousparametersarecomparedwiththoseobtainedfromsectiondatabyapplicationoflifting-surfaceandlifting-linetheory.-.INTRODUCTIONThedatapresentedhereinaretheresultsoftwowind-tunnelinvestigationsintheGeorgiatistituteofTechnologyg-footwindtunnel.Thesetestswereconductedunderthesponsorshipd withthe _fin

6、ancialassistanceoftheNationalAdvisoryCommitteeforAeronauticsaspartofsmetiensivewind-tunnelinvestigationtodetermtietheaerodynamiccharacteristicsofbalancedcontrolsurfacesinorderto -supplydatafordesigpurposes. . Force-testmeasurementsweremadeinthree-dimensionalflowtodeterminetheaerodynamiccharacteristi

7、csofthefollowingcontrol-. surfacearrangements: .-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 NACATN2495 +(1)A seriesoftailmodelshavingNACAOO09,66-009,0015,and66(215)-014profiles,a sweepangleof13.5 atthe25-percent-chordline,a tailaspectratioof3.

8、36, anda ter ratioof0.4withvariousunswepttrailing-edgeflapconfigurations.Theflapconfigura-tionstestedincluded30-percent-chordellipticandsharp-nosedaero-dynamicallybalancedflapsandinternal-balanceflaps,aswellassome30-percent-chordplain(radius-nose)flapsThebalancedflapshadanosebalanceoverhangof35perce

9、ntof thelocalflapchordandaconstantflapnosegap.Plaintabsendtwosizesofunshieldedhornbalancesweretestedwithsomeofthemodels.TheNACA66-009and66(215)-014airfoilmodelswerealsoconstructedwithoutthecusptogivestraight-contourflaps.(2)A seriesoftailmodelshavingNACAOO09org-percent-thickcircular-arcprofiles,a sw

10、eepangleof40atthe25-percent-chordline,a tailaspectratioof3.30, anda taperratioofO.k.withbalancedandplainflapswhichweresweptback30.7Oatthehingeline,Themodelflapswere30percentofthetailchordmeasuredparalleltotheairstremandhada 35-percent-flap-chordoverhang.Theflapnosegapwasheldconstantforthevariousover

11、hangstested.Onlyonesizeofshieldedhornwastestedinconjunctionwiththeplainflap.AmorecompletedescriptionofthemodelsisgivenInthesectionentitled“Apparatus,Models,andTests.”SYMBOLSA aspectratio(/)bzsB hornbalancecoefficient(Hornarea.XhornmeanchordFlapareax flapmeanchord)b twicespanofsemispanmodel,measuredp

12、erpendiculartoplaneofsymmetry,feetbf twicespan ofsemispanmodelflap,measuredperpendiculartoplaneofsymnetry,feetCD airfoildragcoefficient(2D/qS)Achb incrementofhinge-momentcoefficientcontributedbyinternalbalance“FP_.-._L-.Provided by IHSNot for ResaleNo reproduction or networking permitted without lic

13、ense from IHS-,-,-NACATN2495 3.ccf.!ChfclDfhf.Lflaphinge-momentcoefficientpf/3f)airfoilliftcoefficient(2L/qS)incrementofliftcoefficientduetodeflectionofflapairfoilpitching-momentcoefficient(2M/qS5)airfoilchord,measuredinfree-streamplane,feet()/b/2 zC dbomeanaerodynamicchord,feet/b/2C dbochordmeasure

14、dperpendiculartohtigeaxis,feetchordofbalanceroot-mean-squarechordofflapatfeetroot-mean-squareoverhang,measuredh free-stresmplane,feetchordofbalanceplate,feet.my section,measuredintiee-stresmplane,chordofflap,measuredperpendiculartohingeaxis,feetflapchordmeasuredperpendiculartohingeaxis,feetflapsecti

15、onhinge”momentcoefficient(hf/)airfoilsectionliftcoefficient(Z/qc)measuredtotaldragforce,poundsflaphingemoment,foot-poundsflapsectionhingemoment,measuredtotalliftforce,foot-poundspounds.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-casectionlift,pou

16、ndsmeasuredpitchingmomentaboutqrterchorddynamicchord,foot-poundsratiooflmomentcontributedbyflexiblesealcontributedbybalanceplate-.c?la=resultantpressurecoefficientdynamicpressure,poundspersquarefootReynoldsnumber(pV5/I.L)twiceareaofsemispanmodel,squarefeetthicknessofcontrolsurfaceathingeNACATN2495 .

17、a71a15 a15a15 ?ofmeanaero-tomoment-root-mean-squarethickneseofoverhang,measuredatihingeline :velocity,feetpersecond .modelaugleofattack,degrees A control-surfaceortabdeflection,measuredinplaneperpendiculartohingeaxis,degrees n=sweepbackangle,measuredatquarter-chordline,degrees *taperratioCfl:=)coeff

18、icientofviscositymassdensityofair,slugspercubicfoottrailing-edgeangle,measuredinplaneperpendicularsxis,degrees()bchf= 5f,5ttohinge._.- .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN2495 5b.ac.uacmKa,tsloeofpitching-momentcurveatconstantaugle

19、ofattack()acm slopeofpitching-momentcurveatconstantflapdeflection .=f)% Subscripts:b balancee effectivef flapt tabu uncorrected. .-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 NACATN2495Thesubscriptsoutsideconstantindeterminingthetheparenthesesp

20、arameter,ACCURACYOFDATA,indicatethefactorsheld P-rTheaccuracyoftheexperimentaldatadependsuponthemodelcontours,deflectionofflapunderload,andaccuracyofforce-measuringapparatus,Thesmallhingemomentsreadwhenbothangleofattackandflapdeflectionwerezeroindicatethatinaccuraciesinmodelcontourwerenegligible.Ast

21、heflapwascontrolled=remotely,itcouldbesettoanydesiredangle,andanydeflectionunderloadcQtidbecompensatedforbysimplyresettingtheflaptotheoriginalangle.Theflap-angle-settingapparatuswascompletelyseparatefromthestrain-gagearm,andnodeflectionsofthegagearmortorqueshqfiwere.registered.Theaccuracyoftheflapan

22、glesandanglesofattackwaswithin*O.lO.Thehinge:?mentsweremeasuredbymeansofstraingagesusedinconjunctionwitha pommerclalWheatstonebridgecontrolbox. Frequentrepeatrunsindicatedthatliftandhinge-momentcoefficientscouldbeduplicatedwithin4.002and*0.0002,respectively=Thejet-boundarycorrectionsfortheunsweptmod

23、elsweresuppliedbytheLangleyLaboratoryandsxeasfollows:Asmodels,model.AL= 1.38L-ACL= -0,021CL0.208Achf - O.OIOICL forAChf=0.0130cLforfewdstacouldbeobtainedAcLf35-percent-cf_overhgplainflapforthewallcorrections. -,.ontheswept thecrrectunsappliedaresimilartothosefortheunsweptTheyareaf3follows: however,b

24、othmethodswillsomettiesgiveerrorsthatarenotgenerallytolerableforuseindesignofacloselybalancedsurface.GeorgiaInstituteofTechnologyAtlanta,Ga.,August2,lgkg.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24REFERENCESNACATN2495.1.Glauert,H.: WindTunnelW

25、terferenceonWings,BodiesandAirscrewi3.R5$. 4.30.7.17 3.59 5.566 5.01 31.48: 4.46 7.43 3.91 6.081 5.15 36.u 4:1730 4.y 7.% 4.16 6.k70. :33$ 4.445.15 40.74 4.356.920 4.94 45.37 4.4750m 3:42 5:70 kg 6.962 4.52 yl.oo 4.51G.7 .3.862.75 4.58 3.46 5.224 3.10g . 1.97 3.28 2.22 3.375 2.aw 1.09 1.81 .92 1.389

26、 1.2595 .60 1.01 .37 .523100 (.10)(.16) (.10) (.095) (:7)100 0 0 0 0 0L.E. L.E.rauus 0.89 2.4a o.55e 1.206 tills o%tationati ozdinates in percent chord.%easured. in plane perpendicular to hinge axb. TProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-!C

27、ABLE11.”-EOLtP1IC-OVERHANGOKOINNLESStationo1.092.143.164.22.;7:348.38g.4210.46Unswept mdels(a)000901.251.691.932.242.342.472.552.602.662.73*Lo “o2.03 1.042.81 2.083.25 3.123.62 4.173.9Q 5.204.M7 6.3;.:; ;:g4:w 9.374.53 10.46f%go2.343.183.754.124. 34. b4.955.055.135.16NACA66(a5)-o14o1.512.032.342.762

28、.82.993.283.333.393.40Sweptmodels. .stationo.431.01$4.575.756.938.129.3010. xlo 0.78 :.C$1.181.70 2:322.03 2.792. 3.132.48 3.412.58 3.552.65 3.672.70 3.762.72 3.79ah percent chord meamred from leadlng edge of overhang. _%leasurd parallel to free stream.Provided by IHSNot for ResaleNo reproduction or

29、 networking permitted without license from IHS-,-,-.Hornnumber1122al1.aC2blab* hTABLE III.- DU?A FOR HORN lMLKNCESAirfoil sectionNAcA 0009NACA0015NACA0009NAM 0015WCA 66-009NACA66(=5)-014w 66-009MACA66(=5)-014sweptmm 0009Sweptcirculararc4.364.946.366.g44.364.846.366.844.464.46Hornsxeasqin.)60.1663.92

30、89.2896.00%.1063.10E!8.o93.033.4032.88qchord“(in.)13.613.414.2513.9513.8513.8214.2614.227.257.25Flaparea(Elqitl.)517.4318.4317. 4“518.4516517.17516517.17434.0434.0Flap meanchord(in.)10.1710.1210,1710.1210.0510.1010.05.10.109.159.15B0. w.404.484. 4g6.392.408.492.503.244.244aHOs am s= for stfit-contour flaps on bd.h 6-series airfoils. bShielded horn used on swept mcdels.I 1Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-