NASA NACA-TN-4397-1958 Static longitudinal and lateral stability characteristics at low speed of 60 degrees sweptback-midwing models having wings with an aspect ratio of 2 4 or 6《在.pdf

1、,ui-,NATIONALADVISORYCOMMITTEEFORAERONAUTICSTECHNICAL NOTE 4397.Thedatahavenotbeencorrectedfortheeffectsofblockagesincethesecorrectionsareconsiderednegligible.Noaeroelasticcorrectionshavebeenappliedtothedata;however,calculationstodeterminethemagni-tudeofthesecorrectionsindicatethattheyarenegligiblef

2、orthedynamicpressureofthesetests.PRESENTATIONOFRISUITSJ?Theresultsofthisinvestigationarepresentedasforceandmomentcoefficientsandderivativesplottedagainstangleofattackorsideslipforthevariousmodelconfigurations.(Seefigs.4 to24.) A summaryoftheconfigurationsinvestigatedandofthefiguresthatpresentdatafor

3、theseconfigurations,togetherwiththepurposeofthesefigures,isgivenintableIII.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN4397 7DISCUSSIONIngeneral,thediscussionoftheresultsofthisinvestigationwillbeconfinedtothedirectionalstabilitycharacterist

4、icswithemphasisonthecontributionofthevariouscmnponentsathighanglesofattack.Itshouldbepointedoutthatcompsringmomentcoefficientsforcon-figurationswherewingaspectratioistheonlyvariablecanbe,somewhatmisleadingsincethecharacteristiclengths and onwhichthecoefficientsarebasedchangewithchangesinwingaspectra

5、tio.Thischangeinthecharacteristiclengthresultsina givenmomentbeingtransformedintodifferentcoefficientsforeachaspectratio.Exsmesofthepossiblemisinterpretationofdatamaybenotedinfigures5and14,whereintitsarepresentedforthewing-offconfigurationsforthethreedifferentaspectratios.Inordertoeliminatethisappar

6、enteffect.ofwingaspectratioonthetailcontributiontodirectionaltabi=itycn,=d with a forthevariouscomponentsandcom-binationsofcomponentsarepresentedh figures4 and5 forwing-onandwing-offconfigurations,respectively.Ingeneral,allwing-oncon-figurationsshowanincreaseInlift-curveslopeanda rapidincreaseindrag

7、attheangleofattackatwhichnonlinearitiesoccurinthepitching-momentcurves.Sincethecharacteristicsshownhowever,someindicationofeffectstobeexpectedfromincreasesinReynoldsnunibercanbeobtainedfromotherhighReynoldsnum- berinvestigations.Forexample,referenie8 showsthatincreasingtheReynoldsnumberfrom1.2x 106t

8、o4.45 x 10!-hadnoappreciableeffectonthedirectionalstabilitycharacteristicsofa completemodelcon-figurationhavinga 45sweptbackwingofaectratio6butdiddelay .therefore,thesideslipderivativesobtainedfrompitchtestsat$= 5and-5 shouldberepresentative.xTailcontribution.-Thetailcontributiontodirectionalstabili

9、tyc%,VEaswellastotheothersideslipderivatives,wasobtainedbysuhea, Sqft . . . . . . . . . . .2.250Span,ft. . . . . . . . . . . . .2.122Meanaero-c chord,ft . . . .1.o83Rootchord,ft. .1.326Taperratio . . . . . . . . . 0.64moNACA65AOO;2.2503.0000.7660.9380.6Verticaltail:Aspectratio . . . , . . . . . . .

10、. . . . .Quarter-chordsweepangle,deg. . . . . . . . .Airfoilsection. . . . . . . . . . . . . . . . . .Area,sqft . . . . . . . . . . . . . .Span,ft. . . . . . . . . . . . . . . . . . . . . .Meanaerodynamicchord,ft . . . .Rmtchord,ft. . . . . . . . .Taperratio . . . . . . . . . . . . . . . . . .Ratioo

11、ftiilareatowingarea . . . . . . . .Taillength,distancemeasuredpsralleltofuselagereferencelinefrommomentreferenceto5/4oftail,ft. . . . . . . . . . . . . . . . . . . . .6600NACA65AOO;2.2503.6750.6250.7650.6. . . . . 0.9. . . . . 60. . NACA65AO08. . . . . 0.338. . . . . o.x. . . . .0.626. . . . .0.767.

12、 . . . . 0.6. . . . .0.150. . . . . 1.392Horizontaltail:Aspectratlo . . . . . . . . . . . . . . . .Quarter-chordsweepangle,deg. . .“ . . . .Incidence,deg. . . . . . . . . . . . . . . . . . . Airfoilsection. . . . . . . . . . . .Area,sqft . . . . . . . . . . . .Meanaercchord, ft . . . . . . . . . . .

13、 . . . .Rootchord,ft. . . . . . . . . . . . . . . . . . . . .Taperratio . . . . . . . . . . . . . . . . . . . . . .Ratiooftailareatowingarea . . . . . . . . . .Taillength,distancemeasuredparalleltofuselagereferencelinefrommomentreferenceto5/4oftail,ft. . . . . . . . . . . . . . . . . . . . . 1.790.

14、. . 600iLA.65Ao08. . .0.450. . . 0.512. . . 0.627. . . 0.6. . . 0.200. . . 1.392Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-14 NACATN4397TABLE II.-COQRDINATESOFTHECIRCUL, plottedagainstu and plottedSnst $c%c%C%plottedagainsta%, %, cl plotteaagain

15、stJ3f3,vE%ad. c$,VH plottedagainst-aCq,w -C%,vlt(%,V+=O”plottedagainstaConfigurationFigure Purposeoffiguretoshow-1 W?ii!ii!i!ziii?+V-E 12.1 1w,w?,WV-E,WFvH Effectofvariousmodel13 componentssinglymd inF,VH,FvH 14 combinationm staticlat-eralderivatives.FvH 1191F 20VH 21EffectofvariousmcdelVE,FVH-F,22

16、can.ponentsonthetailWvH-w,WFVH-WF contributiontothe.staticlateralderivatives.EffectofwingaspectVE,WvH-w,23 ratioontsilcontributionti-F,WVH-WF todirectionalstabilitywithandwithoutfuselage.WF, WJ?VH-WF,FVH-F 24Effectofsweepbackonwing-fusee contributiontodirectionalstabilityandrateofchangeoftailcontrib

17、utiontoUrectionalstabilitywithangleOfattackwithendtithoutthewing.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN4397w8Wchmg Lfft Rohlngmomentmoment ii.cAPProx. Re/ufwewmu drag/.00Lateral+ fone,-Ang/e ofyow. RoMngmomentAzImJthreferenmAppro(.clr

18、ogC=o”Figure1.-Systetioffffrces,axesused.Arrowsindicatepositivedirectionofmoments,andangulardisplacements.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN4397 17I* 6Akmentrefwnce,tjw4#- . . .bwIIFigure2.-Generalarrangementofcompletemodels.Alldi

19、mensionsareininches.*Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN4397*.+- 25.46-160”/b36_-l4.09e Momentrefwence,Ew/4Figure3.- Geometriccharacteristicsofwings.Alldimensionsareininches.Provided by IHSNot for ResaleNo reproduction or networkin

20、g permitted without license from IHS-,-,-2/4.10B6.420-24 0 4 8 12/620.%2832Adanmtcdw(a) Aspect-ratio-2*.“98.765%,4-4 0 4 8 /216.ZtJ242852/adm&xtczLi?(b)Aspect-ratio-hwing.+ 04 81216 ZUHBZ.41Cfw%zt,fx,oi$g .-(c) Aapec&ratio-6 wing.Figure 4.- Static longitudinal6tabilitycharacteristicsofthewingalonean

21、dInvaml.ouaccmbhmtionawiththefuselageandtails.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-OFa75 w,ofli.,., .II I 11111 I 1111 11111I 1! 1o- A-d+&-4 0 4 8 12”.6”zD%A?32 40:812 BWB 28PAJ&atw G? /!9d6m.CGc4g(a) Coefficientsbased on (b) Coefficientsb

22、ased onat3pect-rath-2wing. aspecti-ratiG4wing.,., , ! “t“ :“”1lillllllll:llllll4 0 4 8 /2/620242832Addta, d?g(c) Coefficientsbased onaspect-ratio-6wing.Figure 5.- Static longitudinalstability characteristicsof the fuselagealone, tail alone, andfuselage-tailcombination.Provided by IHSNot for ResaleNo

23、 reproduction or networking permitted without license from IHS-,-,-NACATN4397 21E, dego 0n /0.3O 20.6./Cm 0/.0.8CL.64.20., ,. . “?-20 -/6 -/2-8-4048/2 /620Angleof sdeshfip, gFigure6.- Variationof CL and Cm with forthecompletemodel.Aw=k.Provided by IHSNot for ResaleNo reproduction or networking permi

24、tted without license from IHS-,-,-22 NACATN43970$O&go0a75 /03 20.6.2.,-J10:.6.4.2:.-20 -/6 -/2 -8 -4 0 4 8“ /2 /6 20Angleof sfdesllp,/, oeg.Figure7.- Variationof and Cm with B forthewing-fuselagecor.tibination.Aw=4.Provided by IHSNot for ResaleNo reproduction or networking permitted without license

25、from IHS-,-,-NACATN4397 23u/.2/.0.8CL-64.20-20 -/6 -/2 -8 -4 0 4 8 /2 /6 20AngA?of sdeskp,/, dega71Figure8.- Variationof and Cm with forthewing-tailcombi-nation.4.4.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-*.Cm.3./“0.8.6CL.2-20 -/6 -/2 -8. . .

26、 .-4Ang/eofFigure 9.- Variation of andO 4 8 /2 /6 20sdeshp,/, U&cm with 13forthewingalone./lw= 4.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACATN4397.2cc,d?gQ oa75 /c/oo zoo,.”I , , , , 1 , , , ,1 . . . . . . Y I I I I I I II I t?-t-Ei-20 -/6

27、-/2 -8 -4 0 4 8 /2 /6 20Angk of sdeskp, degFigure10.-Variationof and Cm with p forthefuselage-taflCcmklination. Coefficientsbasedonaspect-ratio-hwing.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 NACATN4397CC,O&go 0a75 /0.0o 2(20.2, I t I I I I

28、I I 1 I-20Figure11.-/6 -/2-8-4048/2 /6 20Angkof sideslip,P, e9vSJ?iaOnOf CL cm with B forthefuselagealone.Coefficientsbasedonaspect-ratio-4wing.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN4397c, O&g:“/0.:o 2(7.0270.3-2o -/6 -/2 -8 -4 0 4 8

29、/2 /6 20Angleof sdeshp, degFigure12.-Vsriationof and Cm with forthetailalone.Coefficientsbasedonaspect-ratio-hwing.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-iv0)mo-m-m+9/2az l%=I L4/-035 Illlllllli I 1111 Iwd“4 O 4“8 12”162t7-& 2332-A?C&m, e, C

30、. .(a) Aspect-ratio-2 ting.Ow1=1WFG WVH7-4 04 8121620%.3932”A?dal%CGdq :(b)Asp.ect-ratio-4wing.+,04 812,$520%2832,fl(gk?cf.mmt E, L&?(c)Aspect-ratio-6wing.Figure 13.- Static lateral stabillm characteristicsof the wing alone and in varloup ccau-bhationa with the fusela ad bib.rIProvided by IHSNot for

31、 ResaleNo reproduction or networking permitted without license from IHS-,-,-1mo-m-C#-0/2.m034%?.CK!2ax-mmmoal?-4 04 8 /2/620%283?Aidafk3atcGc4g(a) Coefficientsbased onaspect-ratio-2wing.Figure 14.-Static lateral* t-4 04 8/215 ff25728.Z?.4 Orm, lx, “*(b) Cceffi.cientsbased onaspect-ratio-4wing.1 *4 04 8/26. 20242?.3?Arcdomz%, a, O&?(c) Coefficientsbased onaspect-ratio-6wing.stabili-bycharacteristicsof the fuselage alone, tail slone, adfuselage-tailcunbinati.on.J-8Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-