NASA NACA-TN-1404-1948 Collection of test data for lateral control with full-span flaps《带有全翼展襟翼的横向控制试验数据采集》.pdf

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1、“F “NATIONALADVIK)RY COMMITTEEFOR AERONAUTICSTECHNICALNOTENo. 1404COLLECTION OF TEST DATA FOR LATERAL CONTROLWITH FULL-SPAN FLAPSBy jack Fischel and Margaret F. IveyLangley Memorial Aeronautical Laboratory Langley Field, .Va.=JiJIRJi-j7.,WashingtonApril 1948 LIBRARYC(iiiim-p019$3u1401Provided by IHS

2、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NATIONALADV5%ORYCOM- FORAERONAUTICS.isCOIXJWTIONI!ECHNIC.ALNO2XNO. 140kBy Jackt,/ A collectionof theOF ZESTDATAFOR LIWERhowever,theaileronsarenotveryeffectivein theflaps-Up Oondition.The datageneralJyindicatea sharpi

3、ncreasein aileroneffectivenessforsmallandmoderateailerondeflections(flapsdeflected)witha decreasingincrementin eflectiv,enessat largerdeflections.Thehingemcunentsproducedby slot-lipaileronsindicateanopeningtendencyof theaileronnearneutralwhich,coupledwiththelargedifferentialrequired,may causeoverbal

4、anceof thecontrols.In the fltghttestsof slot-lipaileronson a fightewbypeairplane(figs.A28toA33andreferenoe5),a springwas introducedintothelateral+ontrolsystemto countezaottheoverbalancingtendencyoftheailerons. In general,if suchadveme hingeammenteffectsareenootered,bala.noingof thecontrolsurfaceormo

5、dificationof thecontrollinkage probabJywouldresultin satisfactoryslot+lip+ileroncontrolforcesin all flit conditions.If slot-lipaileronsareusedon extremelylargeairplanes,someaeromc hlanoe wouldberequtredto reducethelargehingemomentsat thelargeailerondeflections.k4-.-,-*s8w: .lnap-trailidg e ailerons.

6、-Whenflap-lmailidge (plain)aileronswere testedin thepresenceof full-spanslottedflaps,theaileronswerenecessarilyonlyaboutO.10cbecauseof structuralProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.m-B-.*-1considerationsandhad largespansIn orderto provid

7、eadequateeffectiveness(figs.Al to A33). In the flap-retractedposition,theaileronis a narrow-chordlong+pan aileron. (Seereference26. ) Inflap-downoperation,theaileroneffectivenessdecreasedin thepositiveailerotieflectionrangeezxlgenerallyincreasedslltly in thenegativeai.leron+ieflectionrangeas the fla

8、pdeflectionincreased(figs.A3,A5,A14,andA21). A changein thecontrolMnkage toprovidea greaternegativeand smallerpositiveailerondeflection,andprobablya greatertotalailerondeflection,thereforewouldbedesirableto provideadequatelateralcontrolforKlapdcwn operation,if equalup sad downdeflectionswereusedwi f

9、lapsup.Theplainailerons,flapsdown,haveaboutthe samevaluefortherateof changeof hinge+ucmentcoefficientwithailerondeflectionastheaileronswithflapsretracted.Plainaileronsalsohavean upfloatingtendencyat aileronneutral,flapsdeflected.Thisupfloatingtendency,coupledtiththedifferentialrequiredforgoodcontrol

10、,willhelptoreducethe stickforcesbutmay causeoverbalanceif the differentialfor fl+psdownis too severe. The adverseyatingmomentsproducedbyailerondeflection,flapsdeflected,were largerthemthoseproducedbyotherlateralcontrols.Slot-1ipand flap-trail.ifi+ilgeaileroncombination.-The charac-teristicsetiibited

11、by slol.ipandplainaileronswheneachis usedaloneindicatethata lateral+ontrolsystemconsistingofbothtypesofaileron- that1s,plainaileronsfor flaps+p operation,slot-lQpailer031Sforfl.aps-dmoperation- combinestheheatqulAties of eachtype. Thisazn?qementrequiresa mechanismthatprovidesforchangingfromplain-ail

12、eronto slolileron operationwhileextendingtheflap. Flighttestsof suchan installationon,a fite%type airplaneindicatedthe adequacyof controlprovidedby thisement, particu-larlyin he low-speed-e (fis.A28 to A33,andalsoindicated ithatsomebalancingof theaileronsis necessazto providesatisfactorystick-forcec

13、haracteristicsoverthe ccmpl.eteflit range.Syoile-e AileronsOtherThanSlot-up AileronsSupplementainformationand acmeof theresultsofvaIIiousinvestigationsonmodelsequippedwith soilethati,appreciableucmentsareprovidedby the zype andhinged-plate-typepoileraileronc(fi.gc.B30,B76,andB101)endlittleornomcment

14、sareprovidedby a thinretractableaileronhingedat thecen!mrof thespoilerarc(fire.B14,B130,B131,emdB133andreferences15 and 16). Anappreciableamountof controloverthehingemanentssto provideacceptablecontrol.fozces,canbe obtainedhowever,by such spoilermodificationas varyingthethicknessof theretractableail

15、eronorinstallinga plate(hingedor Gtatio- on topof andnomal to theopoileraw (fius.B33 andBihtoB50),venti orbevelingthespoiler a71(figs.B12 toBlh,B57 toB59,andB96),andprovidi otheraero-dynamicbalance(fire.B11OandlZL18).Witheitherthehied plate, FootPressureTunnelof a l/2.7cale MoCielof theF4U-1Airplane

16、withSeveralBalenceaElevatom, Full+p.anFlaps,andDroppableGas Tank. NACAACR,Ott.19420Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No, 140):Rogallo,Ci8 M., andSwanson,RobertS.: Wind-TunnelTestsof a Twin-EngineModelto DeterminetheEffectof Dire

17、ctionof?ropellerRotationon theStatictabilityCharacteristics.NACAAJ?U?,Jan.1943.Willhmm”,W. C.: A l ./I!AC/? 230/2 m - - - .+ - - - 73 - - - w” =./ ,dmen.vonulM= 021ma I NRCA 0009 m - - - - - - - Two R=L4ZX/04b f/ap O!#i/e&W NATIONAL ADVISORYCOMMITTEE FORANtONAUTICS-30 -0 -/4 o /5 26 34Fhh -fh/o defk

18、ctiofl , deg(a) SLOttedflapretract-,5=OO.FiAwe A5. - Effect d ptlillflftdeflection on tm Ifftcacterfstfcs NACA (3+-215, a = 0.6 flfl Rwftb 0.S2C SLOttedand O.10c plefn flap.FfgIUE A4.- Plan form and secUons of an NACA 66,2-216, a. 0.6 airfofl wmh a slotted and plaln flap astested fn Lsey two-dimenst

19、oml low-turbulence tuuuel.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.6.2-30 -0 -/0 o /0 20 30Plolh-flupdef%w?bn, degi.8.4Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- /0.66n+IIIIII1IIIIIIIIL-

20、IIIIIIIIIIIIIIIIIIt -w.,Jb& .s/07=/$ ai/eTon or 30c. S/ot-hp ai/eroD of 0.556, NATIONAL ADVISORY CONNITTEE F(M AERONAUTICS70?vp Ul%?mh 0/ f255c Wirh +ot?clal slot aFre A6. - Plan form and Sectfons of the Clark Y WIQStested with slot-ltp afleron.s nnd fl-span slt flapsin the LangleY 7- by 10-foot tun

21、nel.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.A,/erin defkcflon, &d, uegI , , , 1 , , , 1 1 1 1 l-I Ill$& 5q-1 i NLL!VISLJ 1i1.7d+AMlnEE F AERONAUTICS?:$ “02I I I Ihi %1-n! .+ I ! I I !1II ,7 .,! I, L *,-+-+-I-., I iS-MF I ! II I 11!1 I., w.,!

22、 .IIProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4, ,1d !4-90 -a -70 -60 -50 -. -30 -20 -/0 O 10AI&oQ def/ecflon, 6&l,ciegI&) CL-3 .780 1/2Aileron cief/ectlon, doi,deg(b) bf, L?OO.Figure A8.- Condd?d.(a) 6f, OO.Fi8uIw A8.- Rolling-moment and yawing-mom.snt coefficients of the Clark Y wing due to slot-lip aileronsat O.WC.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-