REG NACA-TN-2483-1951 Effect of fuselage and tail surfaces on low-speed yawing characteristics of a swept-wing model as determined in curved-flow test section of Langley stability .pdf

1、NATIONALADVISORYCOMMITTEEFORAERONAUTICSo00-LnmmruTECHNICAL NOTE 2483EFFECT OF FUSELAGE AND TAIL SURFACES ON LOW-SPEED YAWINGCHARACTERISTICS OF A SWEPT-WING MODEL AS DETERMINEDIN CURVED-FLOW TEST SECTIONSTABILITY TUNNELBy John D. Bird, Byron M. Jaquet, andOF UNGLEYJohn w.CowanLangley Aeronautical Lab

2、oratoryLangley Field, Va.WashingtonOctober 1951- “-_.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECHLIBRARYKAFB,NM :IllllnllllllllllllllulllliliODb558i k1.NATIONALADVISORYCOMMTIEEFORTECEDKKXLNOTE23EFFECTOFFUSELAGEAND TAILSDRFACISONCHARACTERISTIC

3、SOFA SWEET-WDTGMOIIELIN CURVED-FLOWTE9TSECTIONOFSTABILITYTUNNdL1By JohnD.Bird,ByronMO Jaquet,andSUMMARYAERONAUTICS “-“-”-LOW-SPEEDYAWINGAS Dl?UJERMINEDIANGLEYJohnW. CowanA wind-tunnelinvestigationwasmadein theLangleystabilitytunnelfordeterminingtheinfluenceof thefuselageandtailsurfaceson therotaryde

4、rivativesinyawingflightof a transmit airplaneconfigurationwhichhad thewingand tailsurfacessweptback45. The resultsof thedeterminationof therateof changeof theyawtig-momntcoefficientwithW- VelOcitYby 0 osciationteChniUeSagreedwe withthedeter-minationsby the curved-flowyrocedure.Theverticaltailwas the

5、main* contributorto thisderivative.Thevalueforthe completemodelwasessentiallyconstantup to theangleof attackcorrespondingto maximmliftcoefficientandcouldbe accuratelycalculatedwhenproperaccount.was takenof theend-plateeffectof thehorizontaltailon theverticaltail. Therateof changeof rolldnn-momentcoe

6、fficientwithyawingvelocitywasmainlya contributionof thewing. Thisderivativeincreasesapyroximatel.y linearly withangleof attackto theangleof attackwherethe curvesof liftandpitching-momntcoefficientplottedagainstangleof attackdevelopnonlhesrities.INTRODUCTIONResultsme presentedof oneof a seriesof test

7、smadeto investi-gatethefactorsaffectingtherotaryderivativesof variousswept-wingconfigurations.Thisinvestigationwasbegunbecauseconventionalstraight-flowtestsof sweptwingshad givenresultsthatwereverydif-ferent,particularlyat moderateandhigh13ftcoefficients,fromthosegenerally obtainedfromtestsofunswept

8、wingsandthatwereof a nature. not readilyadaytableto thoroughmathematicalanalysis.lSupersedestherecentlydeclassifiedRML8G13, “Effectof Fuse-.lageandTailSurfaceson Low-SpeedYawingCharacteristicsof a Swept-WingModelas DeterminedinCurved-FlowTestSectionof LangleyStabilityTunnel”by JohnD. Bird,ByronM. Ja

9、quet,andJohnW. Cowan,19M.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 NACATN 23The investigationdiscussedhereinwas conductedfordeterminationof the influenceofihe tailsurfacesandthefuselageon the low-speed *yawingderivativesof a transonicairplane

10、configurationhavingthewingandtailsurfacessweptbackho.Thesetestswereconductedinthe 6- by 6-footcurved-flowtest-sectionof theLangleystabilitytunnelwhichwas designedfor simula-tionof steadyyawingor pitchingflightof therigidlymountedmodel. Theprincipleof.operationof thistestsectionwas conceivedbyMr.M. J

11、.Bamberwhilehe was a memberof the staffof theLangleyLaboratory.S-YMBOISTheresultsof thetestsarepresentedas standardcoefficientsof forcesantimomentswhicharerefened to stabilityaxesforwhichtheoriginis assumedtobethe quarter-chotipointmodel.and%CYcmCnclxYThe stability-axissynibolsusedheretiat theprojec

12、tionon thepl:=. ,., . .Figure 2.- Model mounted incurved-flowtestsectionoftheLangleystabilitunnel. #Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Screens 7.IIISECTION A-AFigure 3.- Schematicdiagram ofcurved-flowtestsectionoftheLangley stabilitytunn

13、el., * . .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.,/2.0.6 /2B40-4/Z17-1F I.- 1Id?-.?V(30El ,032: .og7ZZeoretlcul -Figure 4.- Variationacrosstestsectionofdynamic pressureand angularityofairstream inyaw forfourflowcurvatures. GProvided by IHSN

14、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-$ 3.6 NACATN 2U3.- 54.0.-4-+I/6./8/4./4 Ifip of revohhon ._tJAJec+fon 4-A=5= “-.Figure5.- Geometriccharacteristicsofmodel. Wingratio,2.61. Alldimensionsare ininches.aspect .Provided by IHSNot for ResaleNo reproduction

15、or networking permitted without license from IHS-,-,-3.2k63TII I r I I I II I I I I I I 117 “-bP.2 Q./o0 4 8 A? /6 20 24 ZR= 1,40 x 106,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-18.NACATN 23 *.2./72.“Figure 7.- Comparison of values of C obtaine

16、dbycurved-flow,rfree-oscillation,andforced-oscillationtechniques.R = 1.07x 106.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN 23 19.4!, Iw. #11n c1A“74FFFmTrlw I l I 1%1 1/ I4 I I,/-J:2,-.H- I I Ill I I=G+A 1./P. mtmmFigure 8.- Variation of Cz , Cnr and CY withangleofattackr rforallmodel configurations. Curved -flow technique. R.= 1.07 x 106.NACA-Langley - 10-2W - 1000.-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-