1、 , . . . “ p :”-.- .- r .+ t+. ?-s w # -l -“i. . i. . .- C .s w ., , ,. . . . . d .“. ,. -lottedaga;nst-.Cla is given”infigure45. The scatterof yointsis somewhatlessthanthat infigure41. A curverepresentingtheaverageof thetestTointsis slitly belowthetheoreticalcurve.The dataconsideredherein.therefore
2、Indicatethattinetheoreticalvaluesof Ee arq toosmall,The IJ.ft-curveslopesfcq finite-aspectratioswerecomputedbyuse of equation(1)so thata comparisoncouldbe madebetweencomputedandmeasuredvalues. Thiscomparisonis yresentedinfigure46 andshowsthatallvaluescouldbe computedwithin10 percentof themeasuredval
3、uesLiftofAirfoilswithEnd PlatesIa71.In determiningtheeffectsof tip-locateddoubleendplatesontheairfoillift-curveslome.datafrcmthepresenttests.,frcmreferences 17analyzed.AttemptsAas - or asAto20, and fcrnunpublishedsoces were colectedanilweremadetoClj% withc.acorrelatethoendplateeffect,givenepsuchrati
4、osas ., d fls bpepThebest correlationwas obtilned when - was plottedagainst.Af bTherelationobtainedandequaticn(4)wereusedto constructcLafigure470 By use of the curvesin figure47,valuesof ._.!?l?CLCI,auepwere calculatedandplottedagainstwleasuredvaluesof cLain figure48.Provided by IHSNot for ResaleNo
5、reproduction or networking permitted without license from IHS-,-,-10XlevatorEffectivenessThelii?teffectiveness wasestfmatedreferences21,22,23,and thepresentpaper.smpirj.cal.equationwasusedAa Au(dz= A-ainsealedFigure49, whichpresentstrailing-edgeangles,wasThe effectof theThe effectof the(fig.50)of da
6、taThemeasuredNACATN NO. 1291by use of dataThefollovringinderivedfromfigures16 and 17 of reference22.overhangwas obtainedfrom figure26 of reference 22.elevatorcut-outwas obtainedfrmaa correlationfromthepresent paper.Aavaluesof areplottedAR.L3Vvaluesinfigure51. Aboutthree-fourthsofwithin10 percentof t
7、hemeasuredvalues,ElevatcrEingeMcmentsThehinge-momentparameterswerecalculatedaccordingto lifting-surface theory%y themethoddevelopedinreference9 foruse cn awingof ellipticalplanform The sectionvaluesfor theplainflapusedin thecomputationswereobtainedfromreference22. Thebalanceeffectalsofoundinreferenc
8、e22 was addedto the plain-flap valueswhichhadbeencorrectedforaspectretie, Theeffectof thehornbalancewas ottainedfromreferemce4. Themeasuredvaluesof hhge-?nornentparametersareplottedagainstthecalculatedaluesinfigures52 to751No attemptwasmadein thecalculationsto e.ccountfor theeffectsof cut-outs3becau
9、seaccurateestimatesof the values ofthesectionparametersin theregionsof thecut-outscouldnotbemade. With cut-outsopen,theagreementbetweenmeasuredandcalculatedvalueswaspoor;themeasuredvaluesgenerallyareconsiderablylessnegativethanthecalculatedvalues, Better-a71a71.Provided by IHSNot for ResaleNo reprod
10、uction or networking permitted without license from IHS-,-,-NACATN NO. 1291agreementwas obtainedwhentheelevatorcut-outsthisconditicmabout percentof thecalculatedandabout65 percentof the calculatedvaluesofwithintosoolo of the*Froman analysisfollowingconclusions10 The slopeoffcrall themodelsby2. The i
11、ncreasedoubleendplateswas*mee.suredvalues,CONCLUSIONSof testdataon 19maybe drawn:theliftcurvewasisolatedwerefilled. Forvaluesof caCha aretailsurfacesthepredictedwithin10 percentuse of thelifting-surface-theoryequations.in lift-curveslopeprovidedby tip-locatedshowntobe dependentuponthesquarerootofthe
12、areaof theendplatedivided by theairfoilspan.3. For computedvaluesof theelevatorlift-effectivenessparameters- aboutthree-fourthscf thepointsagreewithin10 percentof themeasured.values.4. Thehingemomentparametersof,el.evatorswith cut-outscouldnotbe predicted.accurately,For elevatorswithno cut-outs,abou
13、t59 percentof thecalcula-tedvaluesof therateof changeof hinge-momentcoefficientwithangleof attack Cha and,about65 percentof thecalculatedvaluesof therateof changeof hinge-momentcoefficientwithflapdef?.ectionCh6 arewithin0.0010of themeasuredvalues.LangleyMemorialAeronauticalLaboratoryNationalAdvisory
14、CommitteeforAeronauticsLangleyField,Vs.,February19, 1946Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-K NACATN NO, 1291REF!333H?CES1. Silverstoin,Abe,and.Katzoff,S.: AerodynamicCharacteristicsofHorizontalTailSurfaces.NACARep.No. 668,1940.2, Garner,
15、I.Elizabeth:Wind-TumnelInvestitionof Con.brol-SurfaceCharacteristics.XX -PlainandBalancedFlapson an NCA000$1I?ectngularSemispanTail.Surface.NACAANo. L4111f,1944.3. Gcett,HarryJt,andReeder,J, P.: EffectsofElevatorNoseShape,Gap,Balance,andTabson theAerod;m.micCharacteristicsof aHorizonta3. Tail Surfac
16、e. IMCARep.No. 675, 1939.4. TJowrYjJohnG.,Maloney,JamesAs, emdGa.rmer,1.Elizabeth:Winii-TunnelIn.vestiflationofShieldedDor.BJ.antesandTabson a Oc-ScaleModelof theXFFVerticalTailSurface.NACAACR No. 4C11,1944.7. Sears,RichardZ.,andHoggard,H. Page,Jr.: CharacteristicsofPlainandBalancedElevatorson a Typ
17、icalPursuitFwelage atAttitudesSimulatingNormal-F13.ghtandSpinConditions,NACAARR,March1942.6. Swanson,RobertSo,and l?riddy,E. Javerne: Lifting-Surface-TheoryValuesof theDampinginRolland of theParameterUsed inEstimatingAileronStickFcrces. NACAARF No.L5F2311945.7. Wenzinger,CarlJ.,andEarris,WhomasAa: T
18、heVerticalWind!lhnmelof theNationalAdvisoryComnitteeforAeronautics.NACARep.No.3, 1931.8. Ames,MiltonB, Jr.,andSears,Richard1s: Pressure-DistributionInvestigationof an N*A.C.A.0C09Airfoilwitha 30-Percent-ChordPlainFlapandThreeTabs. NACA?O.,l$kO9. Swanson,RobertS., andCranda3.1,StewartM.: Lltting-Surf
19、ace-TheoryAspect-Re,tioCorrections to theLiftandHinge-MomentParametersforFull-SpanEJ.evatorsonHorizontalTailSurfaces.NACANo. 1175,1947.10.Pinkerton,RobertM., andGreenberg,Harry: Aercd.waticCharacter3.stiesof aLarfleNumberofAirfoilsTestedin theTariable-DensityWindTunnelNACARep.No. 628, 1938a?9?*Provi
20、ded by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN NO. 1291 13.wm*11a Jacobs,EastmanN.jWard,KennethE., endPinkerton,RobertM.:TheCharacteristicsof 78RelatedAitifoilectionsfromTestsin theVariable-DensityWind Tunnel. NAC!ARep.No. 46, 193312: Abbott,IraH.
21、, vonDcenhoff,AlbertE., %d Stivers,LouisS., Jr.:,SummaryofAirfoilData. NACAACRNO.L5C05,1.945.1.3* Purser,l?aulE*, andRiebejJohnM.: Wind-TunnelInvestigationot Ccmtrol.-SurfaceCharacteristics.XV -VariousContourModificationsof a O.0-Airfoil-ChordPlainFlapon anNACA66(217)-OlhAirfOil. NACAACRNO. 3L20,194
22、3.14. Underwood,VilliamJ.,Braslow,AlbertL., andCahill,JonesF,:Two-DimensionalWind-TunnelInvestigationof 0.20-Airfoil-ChordPlainAileronsofDifferentContouron anNACA 651-210AirfoilSection. NACAACR No.L5F27,1945.15a71 Sears,RichardI.: Wind-TunnelDataon theAerodynamicCharacteristicsofAirplaneControlSurfa
23、ces, NACAACRNO. 3L08,1943.16. Riebe,JohnMO, andChurch,Oleta: Wind-TunnelInvestigationof Control-SurfaceCharacteristics.XXI -Mediumand llurgeAerodynamicBalancesof TwoNoseShapesenda PlainOverhangUsedwitha O.hO-Airfoil-ChordFlaponan NACA0009Airfoil.NACAARRNO.L5C01,1945.17. YlnglerjW.: TheLiftDistributi
24、onof Wings withEnd Plates.NACA TM NO o 856, 1938.18. vonK6rm6n,Th.,andBurgers,J. M.: GeneralAerodynamicTheory-PerfectFluids. AirfoilsandAirfoilSystemsofFiniteSyan. Vol.II ofAerodynamicTheory,div.E, ch.IV,sec.19, W. F. Durand,cd,JuliusSpringer(Berlin),1935,pp.211-212.19a71 Betz,A., andNagel,F.: Unter
25、suchungenan FIO-gelnmitEndscheiben.Ergebn.Aerodyn.Versuchsanst.Gottingen,Lfg.111, 1P7, 3?P*95-9920. Reid,ElliottG.: TheEffectsof ShieldinGtheTipsofAirfoilsoNACARep.No.201,1924.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-14 NACATN NO. 1291a71 .21.
26、 Swaneon,.Ro%ertS.,andCrsndall,StewartM.: AnalysisofAvailableDataoh thel?fteciveness”ofAilezonkidthcut *ExposedOverhausBalan% NACA.ACRNo.LOl; lh!.22.LangleyResearchIkpartmcnt:“Sumuarj7.of,LateralControl vResearch. (Compiledby T!houisA. Tel?)NM2TN NG.1245,1947.23. l?uzzser,.PaulE., and TolljThou!sA.:
27、 AnaQsis ofAvailablella”tonControlSurfacesHavingPlain-0v6rhand ?FriseBalances. NA.CAACRNO.L4X13,194. . ,.,!, . . . . . .,.,.!. .,., . .,., ,. ,. ., ,., .,., . . . .:,.:. :,., ,., :,. ,.!,9.,.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-h* ,v.bTASm
28、 I.INFORMATION RWRDIRO -DI-IoW-w MODRLRTssmo IN wicmr 4- 2Y 6-FOOIIVRRTICALT7nnisLflhrbul.n.efactO.,1.9Plan form SM.ante sectionMode:and“Igurl1Correctionsaddedto testdatav9JS I sb/seData3s:13 iNATIONAL ADVISORYCOMMITTEE FORAERONAUTICSFigure 2.- Plan form of horizontal tail 2.*. Is)Provided by IHSNot
29、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-X703011- #3E-+ 380%“” I - +66”F /7.8” Ya71d .Figure 3.- Plan form of horizontal tail 3.,.G7A-AYo1.421.%2.673.153.51Ml 1!4.X dL.46 4.50 4.353.9?3.422.751.97 +e1.09 _3.095B-BY7ro1.421.%2.673.15 la3.51 4.01 $14.30 84.464.50
30、4*35;:Z i2.75 1.97 q1:%5 -Izt-NATIONAL AOVISORYCOMMITTEE AERONAUTICS4 9Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-* . .I/6.00”/2.80- a71L 1?60”L.- -6.40-1t-3?CiLL;3.m4*IUk.945.325.495.320l.%1*Wfl3.W3.U3.974.254.34jJJ1,72.92.099.Provided by IHSNo
31、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-,ixQ-m tico1.252.55.07.51015202:26.,76963.163.764.365.366.769470.972.4:1%A-A II SectionB+ I1,n, J x)eme Deroentco 101.65 1.252.?T3.4s.L.-u.4.945.3201.162.322.90348-4.%1.72.92tl1Yo1.652.252.973.483.37L.u4.945.32 _“ 5$95.
32、32L.S63.s3-l3.051.72.92.099PF/$!2.49RY_;J!i1 ,051l-. ll.= p-.f4E-becflon A -A 1,-.lldtie,YExhikje h.nt -. . m.?” - *Ir,A4!9di2L .- -=_._-_-_-_-=-E!L!W2i2 _ 4.57” _ -_-_-_-_-a=_-=._-_. =.-.=_.-.-_-=-=-=-LA14.08”Figure/”+BNATIONAL ADVISORYCON!NTTEE F AERONAUTICS/675” 7),4“.i ,.Elt7cQl fI)I behind.5c1:46”TL z,40 R8.- Plan form of horizontal tail 8.coProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
