NASA NACA-RM-A52K14-1953 Experimental investigation of the aerodynamic characteristics of an air-to-air missile employing cruciform wings and tail of rectangular plan form at Mach .pdf

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1、 sECURll_Y .NFOl=tMA7111QYf,uhortfot” = Lqh fiwbm 1 “- 22 P;,+7y I;A:.IEPmAL. .-,.” .GRADE Of OFFlER MkKINQ CHANGE)213 m .HOO-*rm-.*”uAE”-”- NATIONALADVISORY COMMITTEEFOR AERONAUTICSWASHINGTON f?ECEWTS:(WCTUIFebruary 16, 1953 RQLIMEDE“bmmiwProvided by IHSNot for ResaleNo reproduction or networking p

2、ermitted without license from IHS-,-,-IL NACARM A52KL4L NATIONALADVISORYCWMITTEEFOR. RESEARCHMEMORANDUMTECHLIBRARYKAFB,NM :- .=-+- ._.Iil!llllll!lllllllllllllllllln143h23AERONAUTICS.- . .EX2!ERIMENTALINVESTIGATIONOFTHEAERODYNAMICCHARACTERISTICSOFANAIR-TO-A3ROFREacANmMISSILEEMPLOYINGPLANFORMATMACHBy

3、MerrillH.suMMARYTheaerodynamiccharacteristicsofCRUCIFGRMWINGSJWOTAILNUMBERSOF 1.4 AND1.9 .-Mead.a modelofanair-to-airmissile ,-employingvskiable-incidence”cruciformwingsofrectangularplanform .d a fixedcruciformtailofrectangularplanform,and”thecha-racteri-“- ticsofitsbody-wingandbody-tailcomponents,a

4、sdeterminedfromawind-tunnelinvestigationforMachnumbersof1.4and1.9, arepresented.Theresultsincludenormal-force,pitching-moment,andaxial-forcedataforthebody-wing-tail,body-wingsandbody-tailcombinations,andnormal-“force,hinge-moment,sndaxial-forcedatafortheindividualwingpanels.- -Theinvestigationwascon

5、ductedata constantReynoldsnumberof1.51mfllionbasedonthewingchord.Alltheresults=e presented. .4 incoefficientformplottedagainstWgle ofattack.No discussionofthe-resultsisincluded. -=INTRODUCTIONOneofthemostpromisingdefensesagainitthehi-altitude,hi-speedbomberistheair-to-airguidedmissflesTheneedfordeve

6、lopingaccuratemd reliableguidedmissilesbecomesincreasinglyimPorttascontinuingadvancementsaremadeintheperformanceofbomber-andattack-”“typeaircraft.T problemsassociated.withtheaerodynamicdesignofair-to-airmissilesareoftencomplicatedbyphysicalrestrictionsplaceduponthesizeandshapeofthemissileanditsvario

7、uscomponentstofacilitateitsstowageaboardsmallfighterorinterceptoraircraft.Paramountamongtheserestrictionsisusuallya limitationonthespanoftheliftingsurfaces.Toreconcilethehigh-normal-accelerationperformancegenerallyrequiredofanair-to-airmissiletiththedesira-Lbilityofsmall-spanliftingsurfacesbecomeson

8、eofthemajorproblemsfacingthemtssiledesigner.Oneapproachtoa solutiontothisproblem-.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 NACARMA521u4liesintheuse.of-low-aspect-ratiorectangularliftingsurfaces.The.presentreportpresentstheresultsofa wind-tun

9、nelinvestigation“of. _ 4theaerodynamiccharacteristicsatMachnumbersofl.1+to 1.9 ofonesuchmissileconfiguration.Inordertoexpeditepublicationofthese” data,noanalysesorapplicationsof.thedataareincludedinthe -.presentreport.wingchord,feetwing-hinge-momentwingpanellandNOTATION -+ .-7.coefficient(based_onth

10、eexposedareaofone .thewingchord)(winghingemoment- )pitching-momentcoefficientaboutthsrnodelcenterofgravity(basedontheexposedareaoftwotiingpanelsd thewingchord)ritchingmoment)-.qscaxial-force.coefficient(forcemeasuredparalleltobodylongi-tudinalaxis,basedontheexposedareaoftwowingpanels).(axialforceqs

11、)wing-axial.forcepanelpalle1m.coefficient(componentofforceononewingtobodylongitudinalaxis,basedontheexposed”areaofonewingpanel)( )wingaxialforceqslnormal-forcecoefficient(forcemeasurednormaltobodylongitu-dinalaxis,basedontheexposedareaoftwowingpanels).( )normalforce _ -.wing-normal-forcecoefficient(

12、componentofforceononewingpanelnormaltobodylongitudinalaxis,basedontheewosed( )wingnormalforcearea.ofonewingpanel)qsAAs usedinthisreport,thecompletecruciformwingisccmposedof.fo!u?- wingpanels. th the . .:-,;exceptionofthedetachable,ogivenosesectionofthebodywhichwasofaluminum. . .Themodelwas”mountedin

13、thewindtunnelona cantilever-beam-typesupportstingThedownstreamendo? the suw?ort. stiw ww pin connected -.to two cross-streamsupportingmembers:.D3$fe.renti?lmovement?! the.jw?cross-streammemberspitchedthemodelinthehori%oalPlaneofthe - “-,:windtunnelwithoutchangingits.relativeFositiontnthetunne.A bent

14、.-.support.stingwasemployedinordertoobt?inanfigle-of-attack.rangeoffrom-8 to+200. =-.-.-,- .=,MEASUREMENTSANDCORRECTIONS .-The.normalfurces,axialforces,andpitchingmomentsonthemodel .weremeasuredbymeansofa four-mmponent=electricalstrain-gage -balancecontainedwithinthebodyofthemodel”.-Theelectricalunb

15、alce - “ofeachstrain”gage,.der an applied lod-”wasmeasuredW a recordw 7.light-beamgalvanometers. ., Flexure-typeJX-be= balancesmountedwithinthebodyofthemodel .ateachwing-bodyjuncture(seefig.2)measuredthenotialforces;axalforcesj andhinge momentson each individual ng panel. The general . arrangementof

16、 theX-beambalqnceis-showninfigure3. Inoperation,thewingpanelis.mountedrigidlyontheti”n-gmountingblock,shofiii: -:- -,-n-thesketch,bymeansof.a”shortconnectings-haft.Theloadappliedtothewingistransferredthiough.thewingrnountgblockd_b_e.flere$. .“x-tothebendingpe Theappliedloadisthenre.olvedtitofoforcev

17、ectorsparalleltothefom bendingbeams.dthemaiudesofhe - .-forcevectorsaremeasuredbymeansbfelectricalstraing%es mounted. .oneachbendingbeam. Sincewe systemcanbe assumedtorepresenta -:.=pin-connected,pin-loadedtruss,thefourm-easuredforcecomponentscan - -T-2Althoughtherolling-momentcomponentofthebalancew

18、asoperativeduring the invesigati.on,theedaare-.body-bination,inwhichthemodel.waspitchedthrou the angle-of-attackrangeatVaTiQus.lresetVgles ofb- all .r?11Sn6._ -”momentswererecordedbutthesewerewithinthelimitsofprecisionoftherolling-momentcogrponentofthebace *d arethereforenot “- .presented.Provided b

19、y IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-5.:thenbe resolvedintotwoforces,normalandparalleltothebodylongitudinalaxis,anda momentaboutthehingeline. Thecompontsoftheappliedloadtendingtoproducesideforce,yawingmoment,androllingmomentonthewingaretransferredth

20、rough.thewingmountingblockandsuitablerestraintflexurestothemodelbodystructureandarenotmeasured.Thefour-componentbalanceandtheX-beambalanceswerecalibratedintheWnd tunnelperiodicallythroughoutthe_investigationby aPPlg .:lmownforcesandmomentstothemodel.Thesketchofthemodelpresentedin-figure1 indicatesth

21、edirectionofpositiveforces,moments,sndanglesaccordingtothe sign conventionfollowedinthisinvestigation.It shouldbepointedout,however,thatforthetestsofthemodelina bankedattitude,themodelwasrolledaboutthefour-componentbalance,whichremainedfixed.Under”.theseconditions,thenormalforcemeasuredby thefour-co

22、mponentbalancewasineverycasethecomponentintheplaneinwhichthemodelangleo;attackwasvaried,regardlessoftheangleofbank. Likewisethemeasuredpitchingmomentwasalwaysthecomponentofpitchingmomentaboutsaaxisthroughthecenterofgravityofthemodelnormaltotheplaneinwhichthemodelangleof attackwasvaried.Thetingnormal

23、forcemeasuredby theX-beambalances,ontheotherhand,wasalwaysthecomponentofnormalforceonthewingactingnormaltotheplanethroughthehingelineandthebodylongitudinalaxis. Inotherwords,thedirectionsofthewing-normal-forcevectorschangedwithbothanglesofattackandbank,-whilethedirectionof thetotalnormal-forcevector

24、(measuredby thefour-componentbalance)changedwithangleofattackbutwasinvariantwithangleofbank. Notethatwhen.thewingsweresetatanangleofincidencewithrespecttothebody,thisarrangementresultedinmeasuredwingnormalforceswhichwerenormalnoth thewing-chordplane,butalwaystotheplanepassingthroughthehingelineandth

25、ebody-longitudinalaxis. Theeffectsof smallstreamirregularities,knowntoexistintheAmes6-by 6-footsupersonicwindtunnel(reference.1),onthemeasuredaerodynamiccharacteristicshavebeenmifiimizedinthepresentinvestig-ation byvaryingthemodelincidenceinthehorizontalple ofthewindtunnel,therebyutilizingthemostfav

26、orableflowconditions.Thisprocedurelimitedtheadverseeffectsof streamirremlitiestohe.axialbuoyancyeffectonthemodelresultingfroma longitudinalpressegradientinthewindtunnel,an-da smalleffectiveangleofyawresultingfromtheflowangularityintheverticalplaneofthetindtwel (modelyawplsne). Themeasuredaxialforces

27、werecorrectedforthisbuoysmcyeffectbyutilizingthestream-surveydatapresentedinreference1. Thepressureatthebaseofthemodelwasmeasuredthroughouttheinvestiga-. tionbymeansofa liquidmanometerconnectedtothreepressureorificesatthemodelbase. Themeasuredaxialforceswerethenadjustedto. -.-.-.-,.-.Provided by IHS

28、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-scorrespondtofree-streamstaticpressureNACARMA52K14actingonthebase. Theflowdeviationsintheverticalpke ofthewindtutheeffectofthissmallangleofyawwasobservedinthewingnormalforcesandhingemomentsmeasuredby”theX-beambalances

29、forthetwo-verticalwings=atzerobankahgle,andforallfourwingstoa lesserextentwhenthemodelwasina bankedattitude.No correctionshavebeenappliedtothedataforthiseffect.Theanglesofattackpresentedintheylotted”datahavebeencorrectepitching-moment,-andh.xkl-forcecoefficientsforthebody-tailcombinationarepresented

30、infigures9(a)and9(b). Normal-forceandpitching-moment.data=forthebodyalonehavebeenobtained,fora Machnumberof.1.4duringa previousinvestigation“-arepresentedinreference2. -w,.=._. .AmesAeronauticelLaboratory ._NationalAdvisoryCommitteeforAeronautics ._MoffettField,Calif. .-.RE-NCES -.-.1. Frick,Charles

31、W.,andOlson,RobertN?: FlowStudiesin.the :“Asymmetric”Adjustable.NozzleoftheAmes6-by 6-FootSupersonic .-.-WindTunnel.NACARMA9E24,1949. .,2. Edwards,S.Shemnan:Experimentaland_!J!beoreticalStudyofFactors .Influencing,theLongitudinalStabilityofanAir-to-AirMissileata MachNumberof1.4. NACARMA7i_J19,1952.2

32、=-.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 , IzI C*f4c%?c+;f%wl Wind direction CxFigure 1,- Sketch of model showing wing-panel identification numberspositive forces, moments, ond ongies.and directions of=1.%1=Iz- Iu)Provided by IHSNot for R

33、esaleNo reproduction or networking permitted without license from IHS-,-,-.3mnoseshpe oeL?k?nessratioWi16uspwct ti7tio /./6ttlkh?ss-w mh (203 Iq-ie.qmedorew-mepmd 0.5/3 1d,(sme fedaspecf rdo 0.48t!iMess -chwdrutb 0.02 “ re470.9xf-oreo-aoepae;/2z/1: 1:,1I III 1 11, 1 111 IMf19 # +ifl _W7ng mounting b

34、lockBendinq beam (typ.) U-+)-1, i- Bending- beam fiexl?e (tP.)Fgure 3.- Generol arrangement of the X - beom baiance.,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.-Normol-force coefficient, Cz Pitching-moment coefficient, Cm Axiol - force coeffici

35、ent, Cx(o) Mach number, i, 4,Figure 4.- Normal- force, pitching - moment, and axial- force characteristics of the body - wing - tailCombinations at O“ bon, ;,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-m/6b l.?%4*b-4-87Wing- normal- force coeffic

36、ien CEW Wtng-hinge -moment coefflcien Cv Wing- axiol-fome coefficient, Cxw(f) Wing panel 3; M?c#I number, i. 9,!2Figure 8.- L%ntinued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“1al16”Mach number,Figure 8.- Continued.I, , . k,“-1 I I I I J,Wing-

37、 uxlol - fof coefficient, CXWL 4.I,1 ll/iE!4*bGO-4-8-.Wing-normal- force coefficient, CZW Mng-hinge -moment coefficient ch #7ng- axial-force coefficient, CXWw(h) Wing panel 4; Much number, 1.9,Figure 8.- Concluded,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-