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AIR DOCUMENTS DIVISION

•j:r.i'|'> !H

'Üiiiiiiiliüili :Hli mill *

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HEADQUARTERS AIR MATERIEL COMMAND

WRIGHT HELD. DAYTON, OHIO

J

Reproduced by

5^ US.GOVERNMEINT

IS ABSOLVED

FROM ANY LITIGATION WHICH MAY

ENSUE FROM THE CONTRACTORS IN -

FRINGING ON THE FOREIGN PATENT

RIGHTS WHICH MAY BE INVOLVED.

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,r~ 'Nov. 19l»I

NATIONAL ADVISORY COMM/TTEEJOR AERONAUTICS

h „

WARTIME REPORT ORIG/NALLV ISSUED November 19il as

Advance Res trie ted Deport

WIKD-IUKHKL DEVELOPMENT 0? A PLUG-OTBE SPOILER-SLOT

AILERON FÜR A WI1K} WITH A JULL-öPAN SLOTTED FLAP

AND A DISCUSSION OF ITS APPLICATION

By Francis N. Royailo and Robert S. Svanaon

Lang^ey Memorial Aeronautical laboratory Longley Held, Va.

*• I! r 00 r 1 C t I »baa V' •••• » 8 RETURN 10

SpirialDi -U..1 -n's .i.:c',- rSÄWM

Aif Loc.m*nis L'Jiin • -1- iti ••>•« (i'D >N,6»l 1 Uli, Ujf.Ofl, l/iiM. NACA

WASHINGTON

NACA WARTIME REPORTS are reprints of papers originally Issued tu provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were pre- viously held under a security status but are now unclassified. Some of these reports were not tech- nically edited. All have been reproduced without change in order to expedite general distribution.

L - 420

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WITO-OTHBM »STlIiOriDUra C? A PLT7G-TYP3 SPOH.Sa-ST.CT

AIIBJLOH "-'Oi: A »X»B WITH A ITLL-SPAE SL0TT33 JLAr

AIT3 ;. DISCUSS103 01' ITS -M-PLICATIOIT

3y 3fr-_n^iB X, Pocallo and Sooert S. Swanoon

stnauAT

A:i luv3 attention wr.s EaJ.e In wind tunnel of ooverel arran^eaen slot alleres or. M 1TACA P.S013 air slotted flay« OUT arran^eirsat wa With a f-ill-crit-n oplit flap« The ••attally c tapered plus that fit wine so r.a to cenforr. ti the oriß tour when in the noutral position plug projocts fron the u~>pcr surf, spoiler, at the i&se tli.10 leaving bohind ihc sjioilci'« The nf-.tic r BOBo&ta wart determined and are T> glor, of. attae1.: rnd flap doflectio

the TU.uk 7- hy 10-fo-it is of a plus-type, spoiler- foil with a full»apa& B also testoO. on a wir.;; plug-type aileron 13 oo-

a into H slot through the inrl external wing con-

When deflected, the aao of the wine as a a slot through the wiatf

ollinf», yawing» and "ain^o ?orentod for several an- •10.

Tin result! indicated that ». Tiltts-typc, e.->cilor-slot aileron prooahly hac r-ogligiolo drag la the neutral posi- tion and will ;.roYii".o satisfactory lateral control for air- planes oqulppod with full-spaa slotted flaps. Tha ailaron whoa located aa tested was unsatisfactory for ueo oa a wing with a full»«pan svilit flap out Bay ho satisfactory if up- rljccd about 10c whoa tho flap is dofloetod or if located noaror the trailing odgo.

The appliootion of this aileron to a pur suit- type air- plane is ccaalricrol ,-nd the resultant characteristics aro OStiaated. Slight tests of the O.ovieo on an airplane with a fu?.l-o.ian olottad flap aro roeoinaondod.

I

isMwwrcsio«

Tho t'ACA has recently undertaken an extensive InvestI« patlor. for the purpose of devaloplng lateral-control de- vleea primarily for use with fullospoft trallina-ed^e high- lift dovicoB. In tao present investigation a 3pollor-3lot

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aileron hr.s tnon deve 3->r.r. sic tte3. flap, S r.llcron vero testoA r. foil Kit h r. flap nuut ra-.f.cina'n te 0 f tho lev attack \ ith the flp.p 40\ 8t at la rolling. alnri. La*; testa '..'er ni-ovi our tes tc of sir. thp.t tho lag will pro arc loot ted rolativcl foil.

loped for use on a win? with R fn evnrr.l different baric sy-apoa of t a Binjlo n.n«le of attack of r.a ral and deflected 4CT ico wore tested at

and ;o;:o evoral anglaa

neutral end deflected 20°, 30 , a yawing, sni. hinge noiTiiitc wore &

e not conr.idai-ed necosnary bee-u liar devices (reforeneo 1) infic bably tu accoptable "hon tho i.ovl y near the trr.illn"; Bag« cf the a

11« the p.ir- r- of id otcr- • ted cos lr-

^»rAHATVS Arc la^KODS

All teats wero made in the "TACA 7- by 10-foot cloied- thront wi&d ttumaji (see i-ef orcneos 1 and E) at an air speed of stout 40 -liloa Tor hour, corron-jondinc: to an offectivo Koy&oldi nu"abr-r of p.pproxiraatcly tiro ni".llo:is. Tho tost aet-up it shown schematically in fi^ura 1» The aileron was ir.ctallof". in the outer 0.37 o/2 of a 4- lay 3-foot "ACA 23013 nirfoil with B. O.JjtSSs fttll-«pan slotted flap. Thfc slotted-flr-p installation wa3 tho installation deoip- nated 3—1» in reforc-nce " and tho flap was operated along the reaor.r.ended optima path. One eiloron arrangement was tested with ,- 0.20c fiill-s^ar. split flap deflect ad 60 . She airfoil «at suspended -iorizo-.it."lly in the wiad tunnel with th* inboard and attached to tho tunnol wall so as to sir.ulate tho Boniupan of a 16-foot vriag. Tho attachr.o:-i.t at tho tunn.il wall rostrp.lnad tho r.irfoil 1M pitch out not in roll cr raw, Tho rorcos r.ocosspry :ostrain tho out- bop.rd j?.i of tho airfoil were d3torninöd by acrns of tho ro,~ulr.r "oplaace sr-stea. Tho lift of tho airfoil with the aileron neutral w.-.a computed fron the vertical outboarä re- action and the assumption that the latarrl center of tires- sure of the BOBlopaa war 0.^5 b/3 :'ro:i tho plrne of »yamo- try. Tho rjllin,- r.omont v.aa coaputed fron the differsneo •between tho vertical rotation! ct tao outboard oad of tho airfoil with tho alloron neutral and deflected; tho yawing aoaoat was esterninc;1. slnilarly fro?, the horizontal roac— tionn.

The- aileron was annually oporatod hj- BOaai of p. crank out si'1', J tho t-annol v.-all noar tho inboard end of tho model. The allaroa hin-o !.iome:its wero determined by moans of p. oallbratod tornuo rod aonnoating the aileron and tho crank.

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The plug-typo ill that fits into a slot the original external eition. V71ien defitsot surfpee of the wing a a alct through the wi on rrrau&eoents most 2. Sketches of other stops In the develop given in tha figures

loron in osse through tha wing contour

ed, tho plug s a spoiler, i:.- Dehind the completely ta

rrangouent s ent of those that prosont

ntially a trxoroft pluf; wing so as to conforn to whan in the nsutral ;po~

projects from the upper at the sajin tiac leaving spoiler. The two silir-

sted are shown in fi ;:ure , which were prallmt&arjr shown in fijura 2, nro the ter-t results.

RS8ULT8 A"D DISCUSSION

In tho presentation of rosultB, the following nyuhols are uso:

11ft coefficient (1/qS)

rollins-i-OEent coefficient (L'/qhS)

ya'.-.'infl-'nor.ont cooffieiont (S'/o.hS)

stiel: doflcction

aileron defloction

stich force in pounds

aileron hingo aocent, inch-pounds at 40 nilos per hour

airfoil chord

tvico tho lift on tho half-stian model

ftwlOO tho area of the half-span model

twice tho span of t'lo half-span codol

rolling r.or.cnt eoout wind axia

yawing moment aoout wind axis

dj-r.ar.ic pressure of air stroan

uncoi-roctod anglo of attack

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A positive value of I1 or Cj' corro 0 tn lift on tho nodal and a positive v „' corrocponds to pn increase in drag award deflection of tho ailerons is con as is tho oaao of conventional aileron

1 lift, area, and span of tho todol wer tiou of results bocruso tho uoiol ropro otii win;;, as previously etaiod. So cor made for tho effect of tho tunnel walla rod tho corrections cay be rather largo

ercas or C

A do'.; tivo, actu."> roduc COIL.pl

Veen belie up.

Tho results of preliminary tosts in which the basic shape of tho plu^-typo spoiler-slot aileron wr.s variod ovor a fairly '-'idc ran jo, Including spoilers vithout slots (retractable ailerons), rre presented la figures 3 to 5. These toFte were uade with the airfoil oat at 8° angle of attaok and with tho flap neutral and deflected 40°.

snond :s to a do-

alue Of : •I

on th o model. aider et", posi- a. S wi c o the e use d In tho sents half of a reetl OlLT . avo alth ouch it is for this sat-

An ODeni ie i a slot eonpln toly aileron deile ctio little „ ffect on cier.ts. (Soo fi£ where a slot ..',"1 s inercaso in ralli rollins- no;.'-on t c'r. uro S ar o eeaelde tivoness at 1 ov a slotted flap .10 fl are unst at la Wd

n the lower surfac through the air

ns DO low 5-1 ° fot tho rolling- anl y .3.) At aileron actually opened th ngoBoaent cooffici arnoterletlee of rod uniatisf act or;- iloron deflections oited. The iilngi- therofore consider

o of the airfoil without 11 (a condition true at he doviee of fig, 3) had a.v.in ;-t'.or.ont coeffi- Aeflontions above 54 , rough tho airfoil, an er.t was noted. The he devloei thOWB in fig- oocaupe of inoffoe- oarticularly with tho

neaeat characteristlco ed uaeatlefaotorr.

A slot opr. Aeflectios.s of rollinj-nor.ent especially at 1 alone is shown gat ion of euch effectiver.ess xi ran^o was not i tio.n of slot wi ror.oval of thj tho lower roar slot was closed downward. The tics of t:-.oce J generally sstii tics r.oar the :

a through the a tha aileron can coefficient, as ow aileron defl to be lneffeetl Bpoilors (refer as not detected nvo3tigatod. I dth fror. 0.030c rear half of th lip of the slot when the ail

rollir.L-- and th poilor-slot CO:J factory but the iutral position

irfoil at all negative (up) sed a Barked increase in the shown in figures 4, 6, and £

ections where the spoiler e. In a previous lnveetl-

ünce C) this region of in- bec-ura the low deflection

n fixtures S and 6 p. vr.ria- to 0.015c w«.s effected by a plu- and a lengthening of so that in all cases the

on waa neutral or dofloctod o ynwire-nor.or.t oharacteris- blnatloni were cor.sidorod ir hlnge~BOBOBt charncterlo- wore not. Tho narrowest

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basic shape (see fig, 4) vas ohosen for farther dov^lo?- aeat hecvue-e it had the lo'.\3st hiago r.or.erits aad Iti rolling- and yawing-r.eaent chare.ctarl sties voro ooJiaid- erefi as eatiefrctovy as tl.osa of tho thicker ailerons.

sol eho two air cd was to who tho tho «a to flC Hit

So-.o ely to

n in i' tor as vent 3

ho low t dofloe

ineroa*.-, n at po

eh anile offoot

«= 5° a tho top

) th II thoso

detailed iirprovo t li;uro 2. of which in the so he lover tofl. posit o negativ citivo do r fcihJ.nd lT3Ui)56 O aft SR of the T

e hiage oaea figure e.

aileron alteration! that irore na&e he hinge-aoneat characteristics -re One of the i-ost important alt orr.t ions,

are ahOVB in figv.re 3, ras to provide ollor with inlot opeaiag* that ^rojoot- s-L.rf:\eo o£ the airfoil when the ailoron ivoly. The purpose of these vents was alj- the hinge aoseato of the alleren flections by iaoroaolag the pronj-u.ro in tho epoilir. In ori'är to illuatrntc f tho vents in tho rar.~c VOtwoon ll"°, (in which rang« the aodlfl cat ions

lug had no,;".icl"slo effect, no ah own la t ourvei of fis-cro 4 »ay ho or.-, area

rang epoc aTjov Chi • itiv e ou'.L •tal ty r-. isti

Tho enea tire

th :..od lr ca

lati eaae CC 0

B ."

lr,

te

60

ifio at r. •lly on. of

oula

xa

oil " or. atl o r. £ t 3V.i

o f

i the uriper surface of the spoiler on ar- > (ace fig. 3) were tilted and. tent, ra- it tho trailing edge -projected ill&htly oor.tour when tha rilaran vas neutral« which increased tho hinge aoaenta pee»

ve (v.p) defleotiono as shown ir. fl7c.r0 7, ado ae an ediJuEtcaat in a praotieal ic- ho plata were hinged and its ancla verlad aoio linkage tho hingo-aoaeat oharaetor« rthor aodlfiod.

She slots or gay 0- through tho top of the 3-poilor (fig, "(n)) wore provided to aiii-.inato the «nap la tho hlago~noaoat eurvo at very »aall aogatlve dcfiactionn. If tho clots :-rc ar.do appreciably Irrg-ir than tfcoao shown in figure 3, howovor, they will docronao thO ci'f oot lvaiiars of tha alloroa at low def loot lone.

In o--dcr to dotomiao tho ci'f set of r.oro quickly os- ) coin,- the -vent whoa tho ailoroa is Cofleotod downward, the piata P (fie. "?{*)) *»• renoYoa. Although roaoviag t'.is .lato vaa oor.3iC.orad acnOiicial to tho blngo-nonoat eharaotorietioei it was thought "aost to ier.ro the jlato in plaeo to avoid ir.craanlT.;; tho drat: of tho r.irfail wit., the ailoroa neutral,

Hollir..:-, yawing«, and hi:iüe-L-.o:.-.ent chr.raatorlstiee of the aileron arrangeneate eho'-r. la ficai'o 2 are proscr.ted

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typical pursuit airplano. (Thoso computations can also bo directly compared vith the couput-ttlons of the char act »r- Istics of othor la.teral-con.trol devices for 1130 on the 5a;e wing with full-spaa flaps, as giver» in references 5 and 5.) Tha general arranger.ent of th? wing is shown in figure 11. A full-apan slotted flap of 0.20c is Indicated although the flap on the wiad-tu-nel i.odal was about 0.25c. It v:a3 ac- IU»t th.-t illeran characteristics at a ;jive-i flap deflec- tion and lift coefficient are independent of flap chore1, over the range of flap cherts frou C.20c to 0,30s. Sach aileron hes a r.pau cf 115 inches or 0.514 b/2, as shown in figure 11« 3ross sections at the inboard and the outboard ends of the ailerons aro shown in figura 13; notico the al- terr.eto suggestions for plus construction. In either da — eisJi the rear openings of tho vents should "be within the wir.g contour vith the aileron full down and the upper plate should he freie to be bant up. A schematic dlarran of the aileron oi-erating linkage is shown in figure IS; the angu- lar deflecticr.s and the r.echnnieal advantages of the ailer- ons relative to the stich are shown in figure 14.

The computed aerodynamic characteristics of the ailer- on systcn (soa fl•. 15) are based on the ciuple but approx- imately correct assumption that the rolling- and the yawing- coLient coefficients due to the ailerons vary directly with the a 11 J: or. span. In percent of wing eanlspan, and with the distance fro*; the aileron axis to the downstrean edge of the top free, a distance approxlaately proportional to tho projection at any t"ivon aileron deflection, la percentage of the wing chord pt tho aileron. The section hinge nonont was assunod to vary dlroctly with the width of the top face and with tha distance fron the aileron axis to tho down- stream o.\:-;o of the top face; this variation waeindicated by an analysis of the hir.go-r.oaar.t data of figures 4, 5. and 6. Tho aileron-control characteristics presanted cover the ranee of lift coefficients estimated for the wing ia the tunnel. (See Apparatus ar.d Methods for lift-coeffisieat estimation.) This lift range was probably greater than could be realized on the airplane, oven if the chord of the slotted flap were increased to 0.25c.

The aileron-control characteristics given in figure 15 r.ay bo directly co-pared with those given In references 5 and S because tho oar.'.a airplane was assured In the three set3 cf ao:..putatioas. Although tho naxisua stich deflec- tion in decrees was slightly altered, tho stich travel in Inches was tha ear.e. At a lift coefficient of 0.17 with tho slotted flap neutral, the stich forces on tho spoiler-

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slot aileron "ere ooti 0.10c piain aileron fo loss than 0,0a2; at hi slot aileron has tho h dua to the apollor-slo for systor.s "lth plp.in onoo S) and thcso x'crc crease ir. tho width of ono of tho objections wast he aluoat cor.ilot3 (Soo reference 4.) It as the gvoll^i'-slot ai width li reduced and t tractable r.ilcron, a d shown to Tie ir-effect lv nasr variation« over t fi;;s. -1, P, and 6) did offoctlvo: os? with flu dofleetlons. If tho d or vory fast airplane« ailerons designed to &

uatoi to oe less than those of the r rolling-uouent coefflrior.br, J;1, her valuos of C;1 the spoilcr- lgher stick forces. Tho stick forces t aileron appear to oo no higher than Herons of about 0.15c (soe refor-

es r.ay so further reduced by a 4a- the plug; i'- ~ay oo recalled that

to a thln-plata rotraotahls aileron aocanco of aere&ynanio hinge tt&aeat« should he pointed out, however, that

lerea thiakaeea is reduced, the slot ha device 3e-AL-.es nor« nearly a re— evice that wind-tunr_el test 3 have a at low ailoron deflections. Thick- io range of the present tests (see not anov.- any raduetion of ai 10r0:1

g thlokaaaa (or slot width) at low evico i; to "00 aopliai to very large additional test3 should ca nade on

lvo on-ill stick forces.

Except for tho eouewhat high stick forces at high sp.Tcd, the spoiler-clot piloron appeare to 'so nerodyaanio« ally os good or hotter than ar.y of the plain ar.d the slot- lip aileron oonhinatlona dleoueead la reference ö. llechan- ioally, the ipoilar-ilot rlloren allows at. aileron linkage systeu far eiapler than any discussed in reference b. She structural design nay present soaa jroaler:s not encountered In the lesign of Conventional trailir.g-e.'.ge devices, hut the .".ifficultios do not appear to "so Goricue.

Beoauas the plug-type aileron :-.ust dlaplaoe sor.c air fro:.; thj slot in.r.'.ovir.g downward fror, neutral• itB action is elcilar to ^hat of a viscous dar-.por or dashpot. There- fore, it :

I<

OC^CITOIES SEItARI'-S

a.miler- ooatrol 3ocr>uso tho v.'iMt aceoptao Tho spoi nnaatlftf flat) mil fleeted, the trai piar.o •:;!

results slot ail or. air^la the aller

Hhen it lo for us lor-slot actor? fo 0 z a % fee a Lut it ft

Hag oftco th a full

of thi-3 invest ron will provi rs.es e^uippod w on require a 3.0 in in the nout o or. iiodera lii !i.ilcro:\ locate r v. se or. a via lieron is uprl ay 'be sr.tisfc.s

flight teat pr.n p.lottc d

i.-ation i do aatief ifn ftt.ll- lavee si

ral resit h-jicrf or

il. as test G with a G~ad v:hor. tor" whou e of tho flau are

ndicate thr.t actory later span slotted ots or opor.in ion, it ehov.l ".aneo air-plar. cd was coriald i'ull~spa;i dpi tho flap is located near

c'.ovico on an roeonronloa.

1 fla^s, s in

& 1)0 OS. ZTOÖ. it do- or air-

Lancloy Kciiori.-.l Aeronautical Iroorator"i Rational Advisory Cor.nlttoo for Aeronautics,

Laasley ?ieli, Ta«

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HEFEK3TTCSS

1. Venzin£.,er Csrl J., and RosjaUo, FranciaM.: Wind-Tunnel Il^veotigation of Sudler, Defiejtoi'i and Slot Latorel- Coetrol Dovices n Winga with FiOT-Span Split and Slotted Fla?e. Bsp. Eo. J06, MACA.1QM .

2. Vtaulagur, Cf>ri J., and Harris, Themas A.: Wind-Tunnel TiiVfi&titation nf sn N.A.O.A. gJQtt Airfoil with Various Armsgowota of slotted Firpa. rep. |o, 66-V, HACAj 1939-

3. V'enziivrer, Cfrl J.. ondErjiber, Milloid J.: Wind-Tunnel Teat.0 of Three JV-.taraL-Contr-l I'eviceB in Combination with a Full-Svan Slotted Flai on an H.A.O.A. 23013 Airfoil. T.N. No. 6?9, fOOK, 10?8.

h. Beule, H. A.| ;tnd McAvry. W. H.: Flieht Iir'eetlgation of Latent! Control novices for Ttes vlth Full-STJtjn Flapo. Ecp. K.?. 5^ V, KACA, 1935.

9 RoMlto Fr^ncia M., «nd Sparo, Bjrtlv-li-jnev S.: Win*-Tunnel InvoBtiKRticn of a l'laiin ard p Siot-Lin AJleron on a "inß with a FuU-STJon Blotted Flap. t'ACA. .'.CH, Arril lOUl.

6, Hirrie. BUWM A., in1 Purser, ?aul 7!.: Winä-Tunne1 Xaveetlgfttlon of Plain Ailerons for a Wag with a ru.U - Gp?n Flap Conuiatln^ o* an labo.ird Forfler aad an Outbntrd 3etrftctable Gpllt Flep. KACA ACT, March 19*1.

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GOffCIiUDXM ?.S!'_iH::S

The results of this ln.va«ti&atiOB indicate that a spoil er-s>I ot ailoron will provide sati sfact cry latornl control on airplanes equipped with full—span slotted flaps, Boor.uso tha ailcran requires no largo slots or opanin-s in tho viog v.ho.i it ii in tbfl neutral position, it should he ancoptaolo for uso on codorn hi,;h-pcrfsrr.aneo airplanes. Tho spoilor-sZ.ot aileron located as tested war considered, unsatisfactory for v.so on a wine with a full-span split flap UJIIOES tho aileron is upi-icjod whon tho flap is de- flected, Vttt it na;r 'be ar.tlsfactor;- when located nearer thu trailing odpo. Tllßht tests of tho dovico on ar. air- plane with a full-rpr.n sicttc d flap are rocour.ondod.

Lanf:lor'- iicDorir.l Aeronautical Lrhorator", ITa'jion-.l Advisory Gor.r.ittoo for Aoror

Lanslay Field, Ta. Ktt i i c • |

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NACA

IC 4

Wing hinge axes at tunnel wall

Figure 1. Schematic diarnun of test set

Fig . 1

i 4 T—I

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i r Mi N -i go

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Flg. 3

J

r

assess

J

r

i • MCA

Fig- 5

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Fig.

•a HkCt

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n

Figs. 7,Be

-j«? -BO , -10 o 10 Ai/et on 0etlec*ion ,o\?q. Down

7.3 S.S 4.0 B.O 0 -B.I Aileron projtBcli^ntperctnt chord

fa) pnt-.e tilted

•V -BO -10 0 10 BO

Aileron drflerJion,deg. Qotfn 5.8 4.0 BO 0 -B.I -*/ Aileron projection,percent cnord

(b) Plate bent at center Fi?uro7.- The effect on the h i n.-;e-moment characteristics of tilting or bending the upper

r-'irface rlite of in 0.3? b/? snoiler slot aileron or an NACA 2:

n

Fig» Bl,b

HACA

L j

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Fig"- 9»ib

d DACA

J

r

NACA Figs. 9e,10

*lf'tu»^toui at. ii,.ma if

J

WLC&

. rf th. »p«il«-l.t .11«- "ntro1

rieor. it.. «^.:T0^r;«r.uit-tyr»e •*»—

J

MCA

i •

I

I

Me. iz«

L J

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j

W-k

I

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rig. »

J

r

:;KCA Jig. 14

I

so 20 10 0 10 Stick •WlactionifiBi'ieg

figure 14.- Spoiler-slot aileron-control linkage chAracter- istics for a pursuit-typo airplane. 2ffuctive stick

length,21 inches) naxiaum stick inflectiont "4°.

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NA^A Fir. 15

it A T3 fa • f-l « I « r* »

scdcdooKO o hgh ^ tf H D4J h'H (

»

A

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ISO« FOB« (OHM 47)

Hogallo, Francis Svaneon, Robert

AUTHORS)

/)-(?) DIVISION: Aerodynamics (2) SECTION, Control Surfaces (3) CROSS REFERENCES: Ailerons, Spoiler -Slot - Aerodynamics

(032U2); Flaps, Slotted (371166); Control Lateral - Flap effectiveness (2520

REVISION

u AMER. TITLE: Wind-tunnel development of a plug-type epoller-slot aileron for a vlng _ full-span slotted flap and a discussion of Its application FORCN. TITLE: A :L ORIGINATING AGENCY: Hatlonal Advisory Committee for Aeronautics, Washington, D. C. 0//4 TRANSLATION: ' ' 3

COUNTRY D.S.

LANGUAGE |FO»G'N.OASS| U..S.CUSS Eng. ünclase,

r DATE NOT'41

PAGES

25 IUUS.

15 FEATURES

diagrs, graphs ABSTRACT

Wind-tunnel tests were made regarding aileron to determine static rolling, raving, and hinge moments for several angles of attack and flap deflections. Aileron is essentially a tapered plug which is fitted into slot through wing and conforms to external wing con- tour when in neutral position. Results Indicated aileron has negligible drag in neutral position and provides satisfactory lateral control for airplanes equipped with full-span slotted flaps; It is unsatisfactory with full-span split flap. Application of aileron to pursuit type airplane is considered and resultant characteristics are estimated.

ROTE: Requests for copies of this report must be addressed to: N.A.C.A., Washington, TJ. C.

T2, HO, AIR MATERIEL COMMAND AlR TECHNICAL INDEX WRIGHT FIELD. OHO, USAAF WF-O-ll MAX 47 1

-ULüiruu-ffinssr tiMMl maunja

ractraara (omo) Hogallo, Francis Svansan, Robert

AUTHORIS)

DIVISION: Atrodynamics (2) SECTION: Control Surfaeee (3) CROSS REFERENCES: Ailerons, Spoiler -Slot - Aerodynamics

(0321*2); nape, Slotted (37466); Control Lateral - Flap effectiveness (251189)

ATO- 6362 ORIG. AGENCY NUMBER

ABE-L-1>20

REVISION

AMER. TITLE; uiad-tunnsl development of a plug-type spoiler-slot aileron for a vlng vlth a ___ full-span slottsd flap and a discussion of Its application

FORCN. TITLE:

ORIGINATING AGENCY: Rational Advisory Committee for Aeronautics, Uashlngton, D. C. TRANSLATION:

COUNTRY Ü.S..

IGUAGE [fl LANGUAGE I Eng.

:ORG'N.CU« U. SXLASS. Dhclass.

DATE Nor'41

PAGES

25 IUUS.

15 FEATURES

dlagrs, graphs

AQSTOACT Uind-tunnsl tests vers made regarding aileron to determine static rolling, yavlng, and

hinge moments for several anglss of attack and flap dsflectians. Aileron is essentially a tapered plug vhich is fitted into slot through vlng and conforms to external vlng con- tour vhen in neutral position. Results Indicated aileron has negllglbls drag in neutral position and provides satisfactory lateral control for airplanes Equipped vith full-span slotted flaps; it is unsatisfactory vith full-span split flap. Application of aileron to pursuit type airplane is considered end resultant.characteristics are estimated.

DOTE: Requests for copies of this report must bs addrsssed to: H.A.CA., Hashington, D. C.

I-J, HO, AIR MATERIEL COMMAND Z^aVi ECHNICAl . NDEX WRIGHT FIELD. OHIO. USAAF