NASA NACA-ACR-5D28-1945 An additional investigation of the high-speed lateral-control characteristics of spoilers《对扰流板高速横向操纵特性的附加研究》.pdf

《NASA NACA-ACR-5D28-1945 An additional investigation of the high-speed lateral-control characteristics of spoilers《对扰流板高速横向操纵特性的附加研究》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-ACR-5D28-1945 An additional investigation of the high-speed lateral-control characteristics of spoilers《对扰流板高速横向操纵特性的附加研究》.pdf（41页珍藏版）》请在麦多课文档分享上搜索。

1、.% .- -.IllllmllJlgjnllg!llMAY2G, “ACR No. 5D28NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSWAlrmm luw(mrORIGINALLY ISSUEDJune 1945 asAdvance ConfidentialReport 5D28AN ADDITIONAL INVESTIGATIN OF THE HIGH-SPEEDLATERAL-CONTROL CIWRACTERISTICS OF SPOILERSBy Edmund V. Laitone and James L. SummersAmes Aero

2、nautical LaboratoryMoffett Field,California,. . : -.,;.,.,.,:NACA” WASHINGTON?JACA WARTLME REPORTS are reprints of papers originally issued to provide rapid distribution ofadvance research results to an authorized group requiring them for the war effort. They were pre-viously held under a security s

3、tatus but are now unclassified. Some of these reports were not tech-nically caitmi. All have been reproduced without cge in order to expedite general distribution. n.A-al.?kProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-i!)-, .!, . . .,NACA ACR NO,

4、6D28 : , -. :.“ : .l!7ATOALADVISORY COMMITTBE FOE AERONAUTICS. . - ,. ,.; - . ., . .,. . . . . .AIltiAECECONF.I-DENTIAL RE%ORT: .:.“. +-.1 ? .b- .:,.,. . ,. .AtiADDzTIo.Q l+#sT*ZGATImEor.TRE. HIGlVkqlt?q andiJhrnes L; Summers. -.”. . . . *. . .:, . . .d. :.SUMMAEY #. ,-1, . . . . . . -.,Tho characti

5、oristlcs of p.nrtifll-span spoilers- located at0.75 of the chord on an NACA 66-series tapered wlug,-qarticn-lcrly at high speeds, were Investigated. The effect of smallspoiler proections was found. to Increase with an increase ?.nspeed until the critical Mach number was excdoded. Tho dataindicato th

6、at a spoilor having a small projection In front ofan aileron rovldes a considerable increase ,in controlt espe-cially at high speeds. A spoiler projecting from “the upperwing surface producod no adverse effects on the aileron.However, “spoilers- projecting from bdth upper and lower .sur-fnces, which

7、 were invontigatod as a poseible control.for tail-less airplanes, produced serious buffeting and reversl of thehinge momonts of the lloron. . . .introduction.,. .PrcVous tests (reference 1) showad that a. spoilar infront of m conventional aileron will increase tho rolling Iac-ment as well as decrens

8、e the stick force. At high spoods,even a small projection of the spoiler produced .a large in- “crease in the lateral-control effect.lvenkss. In;referenco 1 .It was also suggested tha.a spoiler; could be used In frontof the elavator of:a conventional tall plane. for addtlonalcontrol at high speeds-

9、The possibility of using .spoilersfor.tho diroctlonal or longitudiqfil control of tailles air-planes was also noted,!Che present Invostlgatlon was mmde to provide further in-formation on th effect of n spoiler, especially at highspeeds- Smaller nnd larger spoilers were tested ovor an cx-tendod speed

10、 rangee In addition, spoilers projecting simul-taneously on tho upper and lower surfnces were investlg%tedcProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .-. . . . - .-. I2. - . . -. . .“. ?JAC ACR I!Tom5D28. . . . . . . . . ., . . . . . .APPARA!l

11、W6. MfD METHbD. “ “ “The riodel tested was a eu.mi.spnnlow-drag (NACA 66-sorles) tapered wing (fig. l(a). It wns mounted In the16-foot wind tunnel of the Ames.Aeronautical Laboratory, US.,.shown 1:1figure 2,. This modelt was cne used fop tho tests “roportod in reference 1 except thkt.the aileron nos

12、e bnlancewas 0.45 of the nileron chord-(flgi l(b) And-most of the ;spoilor dntd were o.btuined with tho ai.loron unsealed, “.Tho spoil.ers.extended along the 0.7d05 to 008 of the local wing chord (c). +11the spdilers had “smooth piano “%urfaceB except the 0.04c slo-tted spoiler whichhad l/4-inch-vid

13、e slots spaced 1/2 inch center to center(figs l(b).The spoiler tests were made with the wing surfaces smoothand with the aileron unsealed, Since the gap at- the”leading ,.edge of the aileron balance ,wa . “guare feqt”. . .1 .“” - unc.orroc;ed .ralllng mornent.B“du:t.oaileron ati/?r “ . :poiler, abou

14、t wind “Z+XIE“i”nplane af symm,etry (at .thp wind-tunnel We-n), .f”opt-ppuhdsm .:. -“-cor”ro.c”ted yawing mo.iueht,dfio at,oaileron! ador . “ -.spollqr, r.bou%.wind-axk ln”plane of symmetry (nts. “,the wind-tundel Wall), foot-pounds. . ,. . ,. . .- 1t?rica uncorqcted pltchXng”omeqt .(abeut .Zo.of M,

15、A,C.)of somlupan model and “hut,foot-poundd . :. . . .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 liACA ACE NO. 5D28D twice uncorrected arag of semlspan model and strut,pounds.*L twice uncorrected lift of semlspan model and strut,pounds “H aile

16、ron moment about hinge axis, foot-poundsa uncorrected angle of attack, degrees. .8 aileron dofloction relative to wing, degrooe (deflectionpositive when trailing edge is down). .RESULTS AND DISCUSSIONThe data prosentod (figs. 4 to 24 are based on the com-pleto wing dimensions given in figure l(a). N

17、one of the dataare corrected for strut or tunnel-wall effects. All tho dataexcept thoso presented in figure 16 aro based on the assumtion that only the left alloron was deflected and the spoiler,when present, was on the “left witig only. “ The data presontodin figure 16 aro based on the assumption t

18、hat the spoilersare simutanaously projectod on the upper surfaces of bothwing tipsa The pitchinmoment coefficient Is based on themoan aerodynr.mic chord (3-84 ft) and on the pitching”momentnbout the one-qunrter-chord point of the mean aerodynamicchord.For to angle-of-attack range of 0 to 4 and with

19、smallspoiler projections the critical Mach number varied from 0.68to 0.53. Tigures $.to 8 show that,. In general, the affectsof small spcilor projections became a maximu-m o.ta Mmch numberslightly greater than the critical Mach numberJ cnd then de-creased rapidly as the Mach number was further incre

20、asodsThorcforo, It may be necessary to use larger spoiler projec-tions at Mach number”s greater than tho critloal, since thelargo procctlons e.re relatively more effective at n Machnumber of 0.75. However, figures 9, 11, and”13 ohow thatspoilor projections loss than Ot02c UTO proportionally moreeffe

21、ctive thnn larger o“nosin affecting the rollinmoaont,pitching-acment , and lift coefficients, for Mach numbers lessthan 0.75. .Ilgures 14 and 16(a) indicate. that the “spoilercould bo used for additional lateral control during lnndlngslnco it is effective evdn at the arigl-eof stall, EYgure 16shows

22、that the effectiveness of the spoiler on the upper sur-. .face docrosed with angle of attack, and therefore ”the lift-. - - - - -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-PHACA ACE-NO. 5D28 5cur?e slope ”waB a71,%ncreiaaea By the sp6iler.* .

23、Figures 17 and 19ehov-;how tiuch*lid spoiler indreased”the rolling moment andat th6sarue t.nie”-decreataedthe allern hinge moment .,:,., . .1.i. .6, :” . . Riiin A“CR :No”.” 5D20,. .” . . .-. . . . . .,” . . .”when the spol”lorpr.oJootio”n was” 0005c tThe effoctlvehessof the sm+ll spoiler pro Jectlo

24、hs tn.tese tests- mn; beattributed to the large Reynolds” numbers and low” airstroamturhltlenoeo Previous tests (refererice 2) of conventionalwing sectioni at a Maqh. number of 0.05 and a Reyndlds numberof only 2,000,.000 with a relatively high alr-sttieam tu”rbu-ence indlcatod.that spoiler proJeoti

25、.one of O,OIC or leashavo no effcot on tha rolling moments Figure 24 showe thatthe rolling moment due to the 0G0.05c spoiler decreased whenthe Reynolds number bscame less thatee for Aeronautics,Moffett Yield, Califo.REBEREMCES1.2.Lmltono, Edmund V,: An Investigation of the High-SpeedLateral-Control

26、Charnoteristics of a Spoiler, lTACAACR MOO 4C23, 1944.Wenzingcr, Cnrl JO, and Rogallo, Francis M.; Wind-”Tunnel Investigation cf Spcllor Deflector, andSlot Lateral-Control Devices on Winfls with lull-Span Split and Slotted Flaps. IYACA Rep. Ho. 706,134 L=.- - .- - - Provided by IHSNot for ResaleNo r

27、eproduction or networking permitted without license from IHS-,-,-_. -. !CHARACTERISTICS OF THEMO;j = !.SPOflER (ATJ!5U#R0)sm- - 4fiftP#RWEcnN - .Om772 .041 OF fOCAI.WING CU*D:m“*-. - - - - - . -“-3-BillATIOblALADVISORYCOMMITTEE .FOR AERONAUTICS STRUT -Provided by IHSNot for ResaleNo reproduction or

28、networking permitted without license from IHS-,-,-.- -.7- 7w “c”+K-AT GAP - y.03 m0./ 2- %00?NOTE SCALE BREAKM.3 .+ .5 .6 .7 4903- .,6- 1-770/“8,.-9: Oz - a-. - .-/0 h Av ,035 .04. .-.047 .m5C.C-/r.7I I I I I ! /(.6f./ J/:8 7 /.- ?CL4WE #;-f;-7 - . 0 WWILL4 5,VfL.?R/3/. / .0/ - / 2 .Olc .04c 3 .Lz?c

29、 .a?c-4 4 .04C o/c_Y -5 .04C .04C6 .08. 7Ii=- 8,-,-+-.00.? I3-.,/0- I I /.-1 I I I I -t-,-/(-.004Cn-.006 3, y cm= JM5-002 :-”I k=/” I I T-:6, .65- Lx= 3-OwTFT?TFProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACAACR NO. 5D28 Fige. 11,12.04 I I I I I

30、 IA Cm=-” l_u_LA71_J-0 / 2 3SmlLER PROJECTION, P.?RCENT c.04-A Cm _oc=/” M .020 o /z 35POI.LER PRO./ECT/ON, PERCENT c.02-0 / z 3SPOILER PROJECTION, PERCENTC.04A cm =lj” M-.7.02/7o / z 35#ltiR PROJECHON, PEUCENTCNATIONAL M)VISORY COMMITTEEFOR AERONAUTIC S.02 .OzMAC* A CD _Lx= -/0 ,7.0/ .0/iO=-0 1 I I

31、 I I I I I I 0 I I I I I I I I I0 / 2 3 0 / 2 3.5WI.LER PROJECTION, PERcE#7_ c .5POfl ER PROJEC T/O/%f PERCENT c.02A co m= /0M.01 . 7/o0 I z 3SAXLER PRLUECTION, PERCENT cAc/.l k=3.01 N,:.50 0 / 23SPO/LE/? PROJECTION, PERCEN T cProvided by IHSNot for ResaleNo reproduction or networking permitted with

32、out license from IHS-,-,-SAW AORMO. .5D28 Figs. 13,14SmUER PRQJECZION, PERCENT C SI%YLER PRWKCTION, PERCENT CO?/-2? 3, t Of, , f,: I I,- #I I I 1 I 1 I I (SPOILER PRWECTION) PERCENT c SPOILER pRoJECT/OU, PERCENT co 2Y3 o /z 3Y. MACL M, A CL h “= -,75+ -:75 -.3. . . .?/0 -; * - /0 Y * :.-,5- . .K= /0

33、 :-.%5- ,:.:25:7 . 3“ 7llATIOlfALADVISORY COHMITTXEFOR AERONAUTICScc,aeg-4 0 4 8 /2o /6 .?0cl -.O)C-.02/ /0 -/ o 0 /0/ deg. q ae%J, deg./0:0 /0 -/0 00 /0 -/0 00 /0L . . .bo5c; .,0/-.03c” .03C-” ,ozc;.ok -“ w-.004 - -.00 4 / -.004-4 c-”-.006 -.OC%M=03 /%=06 M= 07MATIONAL AOVI&3RY 00KHITTEEFOR AERONAUTICS.002 .002 OozG .- cm .- G .1 ,1 -o.0/-,!92 -Wlc.,:03. / -.04C -” . . Ook :04 -.00 z -:0 * -.00 z-.00 4 -,00 4 -.00 4.Lwc.& /, -.006N= 03 /V= O.6. /W=C27:hProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-