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rml50i27
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  -4-- *’)7f)&Q&+ ~q- t&copy–-‘RML50127) ‘“-ii&i--Ac”A:r. ...—.—*:-,_..----—-..;..=--* RESEARCHMEMORANDUM”’ THELONGITUDINALSTABILITY,CONTROLEFFECTIVENESS,-ANDCONTROLHINGE-MOMENTCHARACTEIWTICSOBTAINEDFROMAFLIGHTINVESTIGATIONOFACANARDMISSILECONFIGURATIONATTlW4NSONICANDSUPERSONICSPEEDSBYROYJ.Niewa.ldandMartinT.MoulLangleyAeronauticalLaboratoryLangleyAirForceBase,Va. \.. .:’. IF_) -—Y i’ u Thh umsntccfmhmcla.wiEed MOrwtkm M dinsUmtiMad D3fenseof theUnltdS@Lea wlthh Lbymof=~abmad ;Ct, mm adSs hformatton only to pmo m hbMIIIlsry Umi vaxmlwlco sortinubitadofscem UKI  @Oywa of tb Federal mwmmdwhokvs a WsMmats iutemmtmunwds ckiz.m of ADJWIIamltymldkmtfon* of C-I* must Ir fbrmd therd. NATIONALADVISORYCOMMITTEEFORAERONAUTICS WASHINGTON Novembsr24,1950 .—-.  .  r ‘Iassificalion?nc?il~dorchanggdo~~~~a~~~$tea...........-ydyf.uthoritvf~ T~hPuMfii~Q,uncem.e,OL,,,,,, A“T~9.j~Eo~jc~ )5~ By.............ib ~~,.....................................................,\%............p...a~.........““’’%~~o~”-~~”~f~ic~~A~~;;~-”C~~KQg)“’.........................................../($H>~}oru..............”................****** m**vTE..“.-: .--.—.—..  NACARML50127 . NATIONALliWISORYCOMMITTEEFORAERONAUTICS v RESEARCHMEMORANIXIMTHELONGITUDINALSTAB~ITY,CONTROLEFFECTIVENESS,ANDCONTROLHINGE-MOMENTCHARACTERISTICSOBI AIN3 DROMAFLIGHTINVESTIGATIONOFAAT TRU?SONICANDByRoyJ.NiewaldCANARDMISSllECONFIGURATIONSUPERSONICSPEEDSandMartinT. hfOld AflightstabilitysndSUMMARYinvestigationhasbeenmadetodeterminethelongitudinal‘controlcharacteristicsofa60°deltawingcanardmissileconfigu~tion.Theresultsincludethelongitudinalstabilityderiva-tives,controleffectiveness,dragcharacteristics,=dcontrol-surfacehinge-momentcharacteristicsforaMachnumberramgeof 0.7 to 1.45.& ThelongitudinalstabilityderivativesshowednounusualtrendsandagradualvariationwithMachnumberattransonicsndsupersonicveloci-.tiesandappearedtobelinearfunctionsofangleofattackwithintheaccuracyofthedataandforthesmallangle-of-attackrangeobtained.inflight  Theaerodynamic-centerpositionshowedarearwardshiftofI-2percentofthemeanaerodynamicchordbetweenMachnumbersof 0.9 andl.=.ControlpitchingeffectivenesswasmaintainedthroughouttheMachnumberrange,althou@liftproducedbycontroldeflectionwasslightlypositiveatsubsonicspeedsandslightlynegativeatsupersonicspeeds.HingemomentswereverylowatallMachnumberstested,especiallyatsupersonicspeeds;therefore,excellentaerodynamicbalancingcharac-teristicscanbeobtainedwithall-mmabledeltacontrolsurfaces.ThevariationofminimumdragcoefficientwithMachnumbershowedasuddenincreaseataMachnumberof 0.85 toamaximumvalueatM=1.05.Themaximumlift-dragratioatsupersonicvelocitieswasabout 3.7.  z I INTRODUCTION ..———~ NACARML50127  AspartofthegeneralresearchprogramLangleyPilotlessAircraftResearchDivisiononguidedmissiles,thehasbeenconductingaseriesof=li&tteststodeterminethestabilityandcontrolcharacte~isticsofacanardmissileconfiguration.Theaerodynamicparametersarenecessaryforthe-lysisanddesignofvariousautomaticstabilizationsystemsandtillalsoprovideusefulaerodynamicdesigndataforestimatingthestabilityandcontrolcharacteristicsofsimilarconfi-gurations.Thelongitudinalstability,control,hinge-moment,anddragcharac-teristicsobtainedfromtheflighttestofa 600 deltawingcanardmissileconfigurationattheLangleyPilotlessAircraftResearchStationatWallopsIsland,Va.arepresentedforaMachnumberrangeof0.7to 1.45. Theresultswereobtainedthroughtheuseofamodelutilizingapro-grammedcontrolsystem.‘Therollingstabilityandcontrolderivativesandaileronhinge-‘momentcharacteristicsofthisconfigurationusingwing-tipaileronshavebeenreportedinreference1.Resultsoftheflighttestofamodel’incorporatingcwingchord,feetaroll-stabilizationsystemwerepresentedinreference2..-SYMBOLSSetwIyPwingmeanaerodynamicchord (1.49ft) totalwingareainoneplane(2.89sqft)~canardcontrol-surfacemeanaerodynamicchord(0.387ft)canard’control-surfaceexposedareq (0.192Sq ft)_wingthickness,inches;ortime,secondswei@t (115.4 lb)momentofinertiaaboutY-axis (20.0 Slug-ftqmassdensityofair,slugs.percubicfoot‘Pcoefficientofviscosity,slugsper v velocityofmodel,feetpersecond . foot-secondsJ. -..—-,— 3. b:.---—. .  ..—
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