Force tests of a 1/5-scale model of the type GB-5 controllable glide bomb

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Title:
Force tests of a 1/5-scale model of the type GB-5 controllable glide bomb
Alternate Title:
NACA wartime reports
Physical Description:
12, 44 p. : ill. ; 28 cm.
Language:
English
Creator:
Pitkin, Marvin
Langley Aeronautical Laboratory
United States -- National Advisory Committee for Aeronautics
Publisher:
Langley Memorial Aeronautical Laboratory
Place of Publication:
Langley Field, VA
Publication Date:

Subjects

Subjects / Keywords:
Guided bombs   ( lcsh )
Aerodynamics -- Research   ( lcsh )
Genre:
federal government publication   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Summary:
Summary: At the request of the Army Air Forces, Materiel Command, the NACA is assisting in the development of a type GB-5 controllable glide bomb equipped with a "target-seeking" device. In order to measure the stability and control characteristics of the bomb in its original condition and with various modifications a 1/5-scale model has been tested on the six-component balance in the free-flight tunnel. The tests included the development of suitable means for altering the effective dihedral and the directional stability by simple structural modification, the development of a device capable of altering the lift-drag ration of the bomb without changing the angle of attack, and the measurement of the rolling- and yawing-moment characteristics of the ailerons. The results of these tests are presented herein.
Statement of Responsibility:
Marvin Pitkin.
General Note:
"Report no. L-133."
General Note:
"Originally issued March 1944 as Memorandum Report."
General Note:
"Report date March 1944."
General Note:
"NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."

Record Information

Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 003610203
oclc - 71126554
System ID:
AA00009421:00001


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Full Text

KIJfAru


NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS





WARTIME ll EPOIRT
ORIGINALLY ISSUED
March 1944 as
Memorandum Report

FORCE TESTS OF A 1/5-SCAIE MOIEL OF THE
TYPE GB-5 COGTROLLABLE GLIDE BOMB
By Marvin Pitkin

Langley Memorial Aeronautical Laboratory
langley Field, Va.


WASHINGTON


NACA WARTIME REPORTS are reprints of papers originally issued to 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 133


v


DOCUMENTS DEPARTMENT
I


-133













































Digitized by ihe Iniernei Archive
in 2011 Wtlln LIndinI g Irom
University ol Florida. George A. Smathers Libraries wilh Supporl from LYRASIS and Ihe Sloan Foundation
































ii


hllp: www.archive.org details iorceleslso1l5sc00lang










:!ATON AL .A"IT r:'{. CO?"MITTES .v: ;. :;,.", "7,

t?:'- T RL?'TC

for the

Ar--" Air Forces, Materiel Cormand

F;:RCE I--?? :"= A 1/5-SCAL' "CJLL OF 7 T:

-"',r. OG^-F. .::F-? r L.-!T GLI7DE T .D.3:B

r- :a:vin Pitkin


INT'^DUC Ti _.:


At the ri'uest of the Army Air :'rces, .;iteriel
Command, the TNACA is assist' irn the cdvel:-. Fr-.t of
a t:Te G3-5 controllable ,.lJ-- b):.-' equipped with a
"target-seek i:-,-" device. In order to measure the
stability arn control characteristics of the bomb in
its original corid',tion and wit- various imod" 'ications
a 1/5-scale model ta- been tested on the 5ix-component
balance in the free-fli-ht tunnel. The tests included
the development of suitable means for altering the
effective dihec'rl r.n, the directional stability by
sI-'.le structural mori f!cations, the development of a
device cpc.able of alter'-ir the lift-dr-r ratio of the
bo-rrb without tin'r! r..". the n-~le of attack, and the
measurement of the rolllr'- and yawirc-moment charac-
teristics of the aileron0. Th- results of these t"t.s
are pre-ented herein.

F r',-e. te t ':..erc -.3iF r'; i -. 12 fferi't t ',r tic? 1-
ta .i c nr C ir.tit r. r he 'f ct ~': i:: fi fferent
sets cf vwir.-t i .-d plat.c *n- ,r. the effrctve a dihedral
charec t --rl st ce- of the :.':~' l ti -. studied. I"T1. influence
of t'.--; "- t? -,f s il' rs, tvr ci ,r d trltl E-C .lit
ridot rs, .on1 cEt o' .:u<,le-spli t fl' ps., e:,3 ; .'v. zets
-f -,plit faic- urp)n! the 1'it-dr-c c-h.racter1stics of
the r' de vao irve,.t' g-ated a'na t.e c'..ractep risticr of
t'hie beveled--":se, ?l i-flap-tre &l ler:". "'ere oL ied.
r~M st f t'rh teotse :*.*r .n~ad at sr Ar, a' l, .-of at tnck of 82
which correscor.de J to the ]slaiuncrire arP'le f thc full-
scale bomb.















au *-.r:i rf i .,:t ac"': i bonL c nLer l r'e, Ja -re-e

,9 1 '- c'..1 .R,, ., J -" reee


: ft :coc f'ric-:it


'",i 2 ': oe ffrr ic i : t


L ift
.i
p.,2?
LtI
)"

T^.1


Fitc'-in nrcrr,:ent
Cr., x.. tchiL'g-m ~ i =nt i:.c. fficieat c i crn-
*^SV-c

Fl'? 11!: -r o-l-0en t



,f Lter.l force
t- latrrl-frc.e ccnric' nt- I_2r


T Yv.'i., r'o0n--t
S ... .i'-.--ic. ..r c i Tf ic ir-t p-----
Sd pr r


i i f-.?'e-dildrl a-.;iet.r, rate of chanq: of
,'P .iiw- -::.o.n:.rt coeuf'icinrit wit>. an'gl of vyaw


C -reccrlonal-stal- liti nara-neter, r-.te of change of
a "i.'l --noent cc.eff cie.t wit h an Ile of


L/D


I lt o'-er drar r-:.ti.o


S ,crnslty of air, slurs per cubic fort

S ./*ri_, ar ac sqLiar fat

V t:'ua alrspe.rd, f.ec.t r-- second


b .'i:- so.n, flet

c v ing chord, feet











S control deflection, degrees, with subscripts as
follows:

f flap

e elevator

r rudder

a aileron


APPARATUS AND METHODSS


Wind tunnel.- The tests were made in the free-
flight tu...el, a complete description of which is given
in reference 1. The free-flight-tunnel balance, upon
which the tests were made, is a six-cornonent balance
which so rotates with the mod l in yaw that all forces
and moments are measured with respect to the stability
axes. A photograph of the 1,/5-scale model of the- .clide
bomb mounted inverted on this balance is given in fig-
ure 1. A more complete description of this balance and
its operation is given in reference 2.

Moocel.- The mc.del was supolioed by the I.!ateriel
Command, Army Air Forces 'and was prep.;ared for balance
testing by the installation of a standard mounting plate
used to attach models to the balance strut. A three-
view drawing of the model is i'iven in figure 2. Photo-
graphs of the model as it was originally received are
shown in figure 3.

Skzetches of the winr,-tip end plates used in the
tests are presented in figure 4 ~and sketches of the
various vertical tails tested are -iven in figures 5
and 6. The aileron system tested is also shown in
figure 6. Figure 7 snows sketches of the various glide-
path controls investigated in the tests.

Test conditions.- All of the force tests were run
at a dynamic pressure of 4.09 rounds per square foot
which corresponds to an airspeed of about 40 miles per
hour at standard sea-level conditions and to a test
Reynolds number of 204,000 based on the mean chord of
0.55 foot. The moments and forces measured on the











Lb-lance wre tr.Ar.sf3r:-ed to the center-of-pravitv' loca-
tion bfl;.:.' the '2-cercert chcrd- line at a dlstjnce
4-r. rctnt chord abo're7 the cnte--' line of the born.


T3EST PFCCZ3DUP


The test projrm vwas zC l1-c' out that all of tne
stability ihan:'i .s c ou'ld be cbtl.iried Ib- si!rip.le structural
n.oditic:i:icn :.f thta lije bcirb. This limitation wa3
do!eeed nc.?essarT; in order to aermit full uise cto be -lade
of iull-s l3 ',.sor,.b units ulread.iy .nu.Iact u'e d. A
pr 1 liriia; y an TIl.sis of the staLilit.' requi.remr-nts f.or
S. coiit.r ileCd .de boib i-dica'ed. t.ih des- ratio lit of
trin;: atle to obtain a ra:ire of values of the effective-
dihrtral rarnam'nter CZ a:dc the diarectional-stabili t
',I
a-ar':m te t ". fror: the values fo- t-h. bomb as ori-

in l.l received ,*1,",' to zero. The test nro.r. n was
lIid. o.t, ther.ecrs-, in such a ,ar:ler that any desired
val.-. i" thD.ese st t.ilit:, i..ar'-i-,'ters could Le obtained
by7 -. s lectic-n r Itn prorer enci plates and vertical
tail :iz:-. sp:eci: l effort wv..s maICd to find a cc.nbina-
tio-n of : u r'f aces.- that w;-ld! yild a v"Alu. of C r of
O.C'Z'?" -nd Cn, of -0..01B because cal-ulations had
indi.cated that thin co.'.:,:;ation cf derivaft 'es ir.i.iht
T.ilid go:.d: flight h.'h.ract..r. istics with a ru-Ider c.ontrol.

The directional stability of the bo:-b was red-iced
by rx.o :."ifer.-.TO m thcds. 0 -u v.as li,-e reduction o area
on the e-:.stin.-: tail t cois --d vwas accomniish-d simply
V ij re.o-..lr.a one of the 'ils oy' b-i r rrn:o"in,. Oc'rtions
fro. the top A-nd bottcnC o tch tf .le, ke-pin r tthe chord
const t, .^'on in fi ,ure 5, to aorr ta.ils 1 to 11.
TI-; second nt.t:.od was t'-; addition o- tail area on
forward bco'.os Lo for-': tail 1 n fi -.ure e. This arr.-.n9-3-
nm-.4t wi3 tested. bec-iise t vwoulu result irn greater
d i.i.1:lr in ya.';.

P'o, each "ertical-tail and -nd-.-late arrange-ent,
the rolling m.nriment, yawivv.;- mo,:.inrit, nmdn lateral force
duai to .aw were determined.

The rolling and yawing moments produced by the
aileron3 rewa measured for the riiht aileron alone











deflected up and down various amounts. The moments for
simultaneous deflection of both ilerons may be obtained
ub sumration of the moments for the u: and the down
deflections.

The goal of the ,lid- eath control tests was to
develop. a device -hich would .c; e the L/D ratio froii
7 to 0 v without altering a -Lven angle of attack or
elevator setting. A "urth:r proviso was that it :hca1l
be possible for some setti r- of this device to obtain a
lift coeffi.Ltent of 0.-4 a condition corre-:rc'rdinr to
the most suitable lau,1.ti.: i sper of the brmb. Alhou-h
it was cbvious that only lift-decreas4n~ devices could
red'ce3 the L/D p'atio to z.ro, tests were oi f of
several devices opjratir- wholly on d'o.-:-increasin.
principles in thj ho1-Pr that ti..ir s n.'i.city of operation
woul. o:ffst their inability to '*-cdduce an L/D ratio of
zero,


IT aD LICUYSIC'

Effect of End Plates on Di'-idril Parameter

The use of vertical end-plate area butzed to the
ends of the w:inrs as shown in fi-,ure 4 v!as found to be
an effective i.nd sirm.l- r.; is of altering the di'cLaral
po.ram.eter Ci,. 'lhe effect of end: plates 1, 3, 4,
and 5, which extended wholly belo1.v the lower surface
of the :ring,upon the static lateral-st'hility chlrac-
teristlCs, is sho"'n in fi.-ure S and tah. variations
of CL, with vertical end-plate area are surumarized
i. fi-rje 9. Theae data indi-cate that the effective-
dihedral Far.:-'eter C, was reduc-d al''ost directlyy
opnopicrtU.onal'1. to ihe i,,cunt cof v rticil ar.i, added
be!.ow the "-irun: at th- "r'r. : ?rJ action of the
vertical nd tlat-s i.n rcL.! tcii 7ff:,cti."? Cibdral
;n'.r. bc e ,Iti' ly a.cr b. .d to t.-. ? .etrir tio s irr.:'o jd
by these ar-eas u.o:. the cross-.fle'', rcndlrio"i, aro]n'-.
the wi.g tips. This wi3s indic,.ted by calculations which
show l ti,iat tiip rol] in-Lo.r:=nt contri;i-ction f the end
places -s islC.ted c.erody-ranic sur'fc-;s ny.s not only
very smail tut v'as such as to jincrase thc effective
dihedral because che resultant center of pressure of
the aerodynai-ic loaas on: the end plates tested is above
the csntr of gravity.











The action of the- ur'ne-r-sirface end plates 2 upon
the efl'ctivc-dinedr l rparan-etsr CE is -icvwn in
fLi u r 10. These data indicate t',:at oudcin-: end-ul.ate
:.rT a ai.'ove tlhe s1 face of ti-e :Finr arts ornasite)] to
a.- i: '-, r.i I .helo.: th W.. a.d c r rse uen!,t.l7 i c .rE. ed C "
The l:rc'.e redi ct on ofr Cl ini.ia]ll caiusd by loiwer-
'1
u.lrf'ace .lrd ,-latec 1 Vias al !oct :crpl-tely nullif'ed by
U-e ad.ld'"rioni of the snalle" nrid-i-'late S.urfaces 2.


Effect of Ver'tic:i1-Tail A;rr'nrerLrnt

UpoT,.n Dire ct on- l Stability

The -ffect of tr twin-tlal ,.e siJas 1 thraou-h 4
'!.:PO : l r at:r l- t'-t li t7 piara'.-t Ler i ccs of the r.odel
,-t ,-o' auii-l of a -iac.: are sio\.'n in fi itre 11. The
r s.!l : of 1 : t.- ts c..ond.uc ted w",ith the as -,e tri-ially
lccat,;d in le-v-rtic Il tail desi-ns 5 thro.uib 3 are
r.res-.nted in fiu 12. Althou.h' the laterai-force
'aid yai Jilng-, iom ent d ta pa.r'es i-.ted in fiLures 1-1 and 12
-are c"i:Lis tens, che rol ii..-rrtc,:ic n c dat i of th 3es UiL-
ure-s Ar'-c 'i;r'r.tic ..nid do not ar.:e '...it, ti.e ,corr si.-'onding,
d-ata of the nz-en i -pl t. e r'.-i of I r. j .'.ni .h .ere
obt.-in-d at o0 angle of attack':. The rollin--; oin-:it
data ) fLi ure ..,-id 12 .'ere s lit ,ed erratic b--c-ause
Dj tr tuL r.. winr s3tl- .rL *-used 1y th. lo. sc-i L of
Lhe t: .Is, their f -or h r-emaininir dirtctinr.al-
3 abil i. tests r;s cIort.'rcc ed cit. 1 fly t an annle of
itra2 :: of T:h reil3t .- o' fi -iC re 12 also ind icated
.hat i -le-Cail -. :l c ~l.--.:-d un. c reetr ical yawinc-
ior.':nt --.a i cterist s i t'-h-' : w 'c, hence 'rCo l ca,-se
uinsatisfactory flight bela'vror. This roint is illustrated
in fi il1ie 15 in which ca e ~t': es n -ecd ayu"ing-mnorment data
for tv'.n tail' and for tail: locited on the left or
ri.--.t Df the stabilizer.

The res-.lts of fi,-ures 11 ad 1 2 are suaaLL rized in
Lf. ur3 14 in which is shon the 'variation of the
d. oC ti..onal-stabil1 t{p p.T'rarril ter n with vertic.al-
tail area aft cf -.he 1 'nter of -:'a.it Th-se data
indicated that a t'."in-l:-.il design of three-.irhths the
area, of itail 1 Iwould orobtb17 create the desired value
of C ,l of -0.0oiOle. The "-sults cf tests made '-rith
4'











a vertical tall of this size (tail 11) and with lower
and plates 6 are shc r, in figure 15. ihese end r.lutes
were selected -r. the basis of the results presented in
figure 9 which indicated that the end plates of
13.5-per'> ent win.- area would provide the desired value
of C1,j of 0.00030. The results of figure 15 indicate
that the desired specifications for Cn, and were
met at 6t an le of attack with these vertical tails and
ind plates installed.

The variation of the lateral-stability characteristics
with an--le of attack of f-he model eqvuipprd with and plates 6
3sid vertical tails 11 is shown in figure 16. These results
indicated that there was c.islderable variation of Cn:
with an le of attack and that when the specified valu'
of Cn, was obt'3in;d at 60 angle of attack,the value
of Cn,,, was too large at the required ingl- of attack
of 80. It was further indicated that directional insta-
btlity would occur at smaller Lancgl.s of attack and
tnit, if the vertical-tail area was further reduced to
yilid th= requir.d dz-ri of .-ir.rtio.-ril stability at 8
angle of attaj.k, the bomb a'ouIlc th;n be dir.ctio-na1ly
u,-,table over ricst of th-e lo-. an!ile-of-attack ranice.

It was bulived that the variation of C, with
angle of attac'c of the bcmb airc.se due to w'in; crharac-
teristics inasmuch as tha results of reference 3
indicated similar variations of Cn with anfgl of

attack fcr rectan.-ular w/irns. Additional tests were
therefore run tc check this onint. For these tests
the characteristics of the model as originally received
(tail 1, no end dates) wer3 in,,estigated over the ingle-
of-attack range. The results of these t=sts are plotted
in figure 17 and ar- summari-jd with thj cata of fik-
ures 15 and 16 in figure 1&. L'at't for an isolated
rectangular winp, obtain.jd frecr. r-;fre.ice ., are also
shown in figure 18 for purposes of corrptriison.

The results of figure l~. indicate that the increase
in dir3ctionul stability with increased an:l of attack
is indspendint of tail dasii n and, therefore, must be
primarily a wing characteristic. It appears, thLra;fcre,
that th3 desired djgriee of directionrl stability cannot











be achieved at o.. an..,e of attack withoutt resuiltin- in
directio.n-1 insttil .t.y t as, jls of attac.1, sm-ller
tha.i C This co.r l--si.n w Ls further substanti.-.ted by
te3a3s f f.-rv:adr tails 12 acti.s together ..itl. the
orii&nal tails 1 1 confi,.ur'at.on. 3hown in figure 6.

The static latertal-stat ility characteristics of
the !nodel coul-'red .-th te criminal -ertical tails 1
and forwa-&d tails 13 pre is.es-.. ed In figj'ue 19. Thcse
data r.'dicate -hat t.ne directional statility of the ,Iiodel
at S aniale nf ittac' was 'vst .rl : stable. The results
cf "i.rur ..: 17 apse uirc'arizd in i'ir "e 20 and s1'ow, the
samen variaticn of directional stability ":ith ;an.-]e of
att.a .: -.revious.l7 noce '9 li data indicated that the
rmicdl v'ith the curled t.il -rr. A-nem nt would be direc-
tion]A.lT ;inzt1 'blet at an-les of attack : sinallr ti:n .


.Uileron Tests

The data fr'c t-.:ts ~f t:'- a:. lson system shown in
figure 6 a:'e nr.E;s --ite in i' uri 21 at va:rious m ales of
attc': f-.r rL i' ht .-ileron alone e leflc;ctrd various
amc i:nts fr.:,, 15' uo to 150 ol'",.


Glide-Path Control

In order to :ro';i de th-= data necessary to convert
pit hLi nori.ients to -levator deflections required to
tri, at given n.gle of atta.c, tests were run of the
nodel %.ith -l.evator 3st at OCand 110'. Tne results of
thesu Lests aie ,res=..t-d in fi. .iie 22.

Snoile.s.- Tests w:erd r-n to determintr the effect
of t'.e urne:-surface 'r-cilc-rs 3ao'n in fi-'ure 7, inasmuch
as thi.s t./pt of Ce'.ice both decreases lift a-nd increases
c'ra_. The results o' these tests are shc'.on in figure 23.
These data show that ;.atho.,l' s).'ilears of 39 Der-cent of
te- s..-rn dri-eased thne L/D ratio at the corr3s :ondj.rg to CL -- 0.64 from 7.0 to '.9 a further
increase in DolileR s. an of 22 ee:cent soan only decreased
"he L/r oatio to 2.3, `a value deemed una3cAsfactcry.
In ad-lition, both inboard ar.o outbcard s'poilers created
large -'ivii-r rmou:rts, parbitclla-"1- inboard spLoilers 1,
and consequ. rtly requir-ed rather lar.r- ch-an.es in elevator
deflecrticn to maintain cont.3-cnt a:in-l of attack.












The large .:'.:1i.-i moments encountered W1th spoilers 1
were L. 1io.red to be b rirm1aril. c..-.c: by the influence of
ths d--ucreased .;i..- downwash uoon the tail surfaces
i.diatelJ .t ,ind.

Dou'I~ .-so.it r,-iders.- Fi..ure 24 prasesnts the effct
of doirtle-s lit :ud-ie:s .A (mounted on e..d -olates 4 as
7j.:v.v;n in fitur- 4) on the iIerl:,'r.. .'c characteristics of
te model. The data on f.. ure '. were rear..n:,:ud in
conjunction ,it'. the elevator data iven in figure '.
to show the variation of L/D ratio, CL, and elevator
&anle- required to trim with r.i~.d6r electionn -.;d are
thus presented in ft-i..re ''5. Tlhese data are --iven for
the apile of at':ack E'-' at which it was nassile to
a--cr.-o'c;.h t.Le sj.-leified value of lift coefficient of O.C4.

T',e data ,.--sent-cd l.n fi':ures 24 .-r.d 25 inl,.icate
th-at the dol:le-split rvid1.-r .1 was i:-Ia.equate as a 7lide-
at}1'. control .,''i--ice "-....f. "', '.'.d rely al_ t .- :le L,/" rati",
f-on'- 7.7 to 4.1 .-:.- f. 1I r1:, ."?". election (e5.t") :L
lfr't.th- att'- .t ':1 .. ;'e t- ]cr.: t-e L/D .-. i ti by S
of s",lit i;-..:e': of '"re&ter .. th. n. r.'d -1rs r]. 'T e
results c f tests rdade with 'cu' le-.-i.1 .t rurld fr3 i? mr.unted
?i 1-! r.i.e .3 arr shown "i flejre- 2-. t; '". .1 t".-i, -h
idd -s re t' e : -n f i they re11.-:d
the L/,r rptio or.ly a .l:-t t ..C .r1.t "'i' r and c3 on3 e-
Qti.-tly no cr ]ts" : test-3 !'s .... : -< t.i:i; 't "ie i'3 ", ;:"l- -
.--it--u'l-, t r- "7 7,rt r--ls. ITt i. e .nt r..- ti'- to
ncte t'':i rt- th :. .-. :-ti .. 1 r.. rui ;s E
ricrer s d t .e 1-: ..:,.-. r.;c ii.- tl- .::.L nr.hasi.i .: the
critic-.1 :r.n of i-' -fio. itio'-: ; Ut a t1-, 'v.in.
tips.

Dc.ruble-s',lit fla'ts.- T.-cts "-. re m'.de c:f :'.ou::le-s lit
fla:,s ext .rdi'-ng ovei r;.- rcit. .:rd 42 i--. ;:.t of ti,
aip, s' ..- sho-Jr i. fi -.'.r. 7. Th.e~ iesalts c.of thesc
tests &. i ...lctted si.ri5 arlo r to .Dos- D! t .= rudl:.,.'3 tr.ts
an6. a"... -erezent-d in fii-urss -- -n- I9. TP, r.s.i.ts
r-5es -:-Lied in-: fi:-ur-r 2D sho/ oi] :: t.r a.cu.ti-.::'lit fl-o:s
deflected GOC u -. i:nd dc-:n decreased ti'c L/D ratio fr.?:n
7.3 to 2.1. This :rec-r'as3, ..t'-.cuh c.s .erable, wis
still ,-ot ccnside-red sufficient. In addtior, a con-
cide-rale change i.. ele t,- -le :.';s required LO trim
at a const -ont ani...e -.,:- attack.

Lc wr--urfa_.ce s 1lt fla-s.- Fi-ures 20 ind .,1 show
the effect of a Icwer'-sur.f.,.ce ? iit flap 1 of *T -:.erc'-t













. -.. lo'- --1 as sI .'".n r .fi ~ -a "'. These d-ita show a

..y l -:ct=ci 1'.rs0 The c';ta o' i-. r.e-z t ts injiJ cated
7 1I. L J_ t F, Ir-, wn vi ci c
a? "t
i!-'.t hI-, '*"-irl 1.m ln2f.2 C- d? A. v, 2 2:s oCu Ur i *
.vfr- c..1..., st who ', nu.il if ioI,' cn -it e '.: .. -l e rn. del
'T':.. :ctio.i und ulte- i -v ar,.e o'.d.l-:u to rthe -ffects of
:.'~-: :L r -i e ri c,".'o '. on t: I' tchi :; ior'i
,. :.tri ut'd ..7 t'-; i i.z Lt.A-l I s.iyf'ac s.

UL.',er-ur"','I s:,lit. : 'l- ps.- The tests of lr',jer-
urlf',.r:e fla I .d i':.e: tat .1 .r.r-3ur face r s, v.o3 ld
. re:'i.ired to ..-lier t... L /D '/ ,:,io 1 as desired. It
'.ts Als ].;iui ato frno,1 t.--- 11 't-d lr ,o tih.; m:-oiler
test t 2. Vi Uisl d .Sc' is '.:. ,at vre u.v..''sh of f ts of
i-'. '-- .. r- i.erj, -,. rl i .s u -_'r' t' .o ritz....L t.l tsil r'ould
'c: *.i. L :r. 1'0- v l. I. i .. t.. 'l,- : _''..l- ; tal 1.i1 :i'.orr:n.ts
csisJ '- : .'e c Such c on f I- ri ':I.cnr :ould
t'i';n lt-; 1 tN L 'D ", ti '.-i ;thOj t ch F'F Ii, ti e t ,l
of .A -.: or ele-'a -- r:.l I-Ti rle- to 'i terr,:lie the
2K.,' i'. fl .. : i -. i lI ; i; I ocL tiion, '-lst- : e e firIst
.. Ide l. -t 2 li *r ide- r'ic l .ith i tr: 1
",'t l r. t :'':. 11 : ; c1 ". U .'.n 1.1F. -t '' ti' -
.',ib:,'..( 1- -_ t C -5: .F sl, :,.-.: r-.;sulC' of
.-h.se t .., i'? .,ted : fi:'ures *-'.! i dica te
:hs.t fl:.- s :2 ,? ''er- I,:,o to eii'-t L" aLl ru-ecifieatiorns.
'.1' i. : .-.. n o ,. -1 st:.r .t. is3 ..r c v s :e-q, ired
to t. .i I .t O t .-i. e of .tItac ,k: vt.c
red, c ".- f:- o .". T -' : ..: ..o. ..'*' :,. d'sfl, ctt.on.

In o.: -1er t') r d- -: s'", I i ti still fur er,
S ~ .t : C o 1i ;i -'. ino >-.T-ri to :;.--..;c?. e t .ving scan
to ,r fiel s ,5. 'h i'e- .lrz ,i tbh-e tests of fl-p 5 are
r:.e3 titeid -,. : i'..-r'.c s J '. .i. .-' .-.ltnhou,-h the .-.es lts
-' : t ,di ', t'- i Z 1 ,.1. .s .. i -l tei th t iL .p i .ould
..t. .tc to- til edIc -. D I*.tIo to zero .s desired,
1 i I-i _i. .. ,t .- i.. i.2' t.:., ,.' s :,- ,.g.i i.-'ea to tr. in ,
out t..- .:. itct i'- rro...' 1.iu a :..ussd Lb' fl-,.p deflection.

It -.-r.d i:;:.:1' t.h .ha t1 :1iv1 tn ',o f.:nts arising
fr'c'rn .-'e i cE -i- o : fr:.-. we re .t us d :. 'irownva d chr nges
on 'in, hor'i..-. o t:.1 t-i I .th that. t i. t-ail .,l.re-nts over-
t.ilnced thIe win, stall]inF n.:,0:'ats c"e;e te-d r7 flb deflec-
tion. In or-der o .3-s st In fl-,dinf-. the -DanS ie loca-
tion of a la, i 1 .ic'.. i eq u.1d -o ch..:-re n e:i.evator
*ettii,,s wtln d fl c t.d, :-.rt:-,:r tests v.'e;e run in ,which
fla... vJ.,. W c'.'- d to tI. oUbt'c 1 or'tion nf the wvin. -.
The -s0uli-s of tests tad e ,it', the flae in this position











(flap 4) are r sen-d in fl-ures "'- and ,7. These
results 1 -,icpted that th this arrin-.'-nt a lar-e
increment of ,-own elevator would be reqgri r' to trim
out the moments .1:-, to _1-0 .-:flections.

A sru.d" of the results --f the tests of fla'-. 3
ad;d 4 i.dicicite that a 60-SL -"cnt span :'! L loca'*e
at the center of each u. : -i should rc.0'de t.:;
*is3ir-d /D control ,'thout re uiri-i. lar eelvator
ch:rnn-s to maintain a constant an -16 of attack. T'it-
results of such a fla:- ('i., 5) are presented in
fi ur.'s Z a:-iI 3.f and substantiate this belief. sie:se
data i.-Ldicate that it is possible to secure a rdi.i:-
tion in L.D ratio with flap 5 f:-om 7.2 to 0 with
only 30 elevator-deflection ch..-vge tbei-: required to
maintain the des.-cd an -1; of attack (80). It a-'ars
that even this 11-'l.t ch--r:e of elevator : .-flection
could '.- eliminated by the e:-oe.'ient o'f moving fl-n 5
a sli cht amount inboard.


CC. : 'LUD .-'- :" A : 3


Force tests of a 1/5-scale model of a t'-e 07-5
o.ntrollable l ,-..:'~l b in the :'.2-.' fr,.--flitht tunnel
Ln'i a..t-,0 ,-'., fol o" i. n-:

1. Tr-e effective-, -Jhed'.-. haracte*' stics of the
r;dcel 'i--re .'c-1del- *"*r>,i'* 1- "-:. id-iti.-: cf "-'rt'i- l
3nrd l:.- t..il.tted to v in. tir,';. Ad irin of old-
ilate area r. lr' '. -i,- surI- reri. ed the eff-?cti'2
dl-.ecrcsl .;-.e.-: s L.ea I^,'ad j.'c .3 ,he -inc in-rer- sed the
effective 4 i-. dral.

2. Th-- :.-idal .;i:' cLhar.ctaristics were s U:h as
to cau..e .-n liCr'e.'ise in r;ir-,:i tL'i naI. stir. ,lit ; .ith
incre3-.,.i s. -Ile of att.c!. t.is cirn ae in irec tL: r.1al
stability' -..itbh .:-i.le C attack wa- ind- r:nd.it. of
ve tti '-.l-t il de?. .'I. Consequ .icly,I ..io Le ly l ar-
a:-cun atof direct nal s.3 atilt; ': -s r quired a t l'.:
seed. to 'void dir2 ctio.:l _in.r:t'-lit- o-.'er the hi,--
srieed .'citi'L n of the s;,.ed. rdrn .











Ur. Uer-.,-urfaece, ui'.rardly deflect. d, s-lit flaps
loc,_,ed at the cent.ir orf ech v.i,'nr nr.nel reduced the lift
o0'V?r d'rkT retio fro:-. 7.2 Trc 0 -'r'.tnout- a -,reciac-Jy ,.hanging
hjI an.le of attack' (.0).

Lan -le :-r .or l:l h:ercnautcal Latoratory,
Iati nal .'.dvisor. Cr.mmittee for Ae onautics,
Lan.-ley Ptiel., Va., -.arcl 27, C'44.




:.1r-vin Pitkin,
'e r o:'i-.tLti 3il Snairi'ine er.

a p-ri-.ved: *( -- /
1-j,,:. .c id
Ha L.ey a. iSoule,
Chief of Sta' ility re-s ach Division.

23







1. Sh.D -t.al, Jose nhi ., s. nrd Octter': nut, Cl&'yton J.
P elli nlar" r ta"'-,ilitt nidd C.ontrol Tests in the
SI. C 'ree-711 _.t ir.di Tui.nnel and rcr- elation
S.."th 1.ll-3 ale Fli:nt Tests. !,-i'A T.i 1o. "10, 1941.

2. Sh.-rta.l, ose'D r., .1 D-rpe:, John W.: Free-Flight-
Tunnel Investiiatlicn of 'he effect t of the Fuselage
Ler.Fth aP1- tih A cct cLa.tin ;ntid Size of thu Vertical
T'-il o La.I-ral S-t.abilit. uL id Contrcl. IUkW aIRR
ic. 3D17, 194Z.

3. Sho: t,..l, Jcseph a.: Tff.:ct -.f Tip 3h. ne and Dihedral
on L.te-lal Stabilit, Charac tei is -icie IACA flep.
n.. 548, 1535.








PI ,T.RE I.IE '".'S


F"'.ir= 1.- Fl'-.to-raph of a --scale model of the type
"'-5 controllable glide bomb mounted inverted on the
fr.F-flifht tunnel balance strut.

Figure 2.- T'reT view sketch of the type CB-5 controllable
clIde ':.;: b as ori-ir.ally receiv-ed!. ill dimensions are
in inches.

F'Ture 3.- F:-.tographs of 1- cale mod~- of ':..e T -5

c ntrollable 1 i _. bomb.

-FiE; 4.- "'etches of vertical wi-"--tip *--.. plates teste-
in the free-flight-tunnel invest'ri-tion of a l-scale
model of the t:-re GE-5 controllable glide bomb.

Fi-ure 5.- !,tches of aft vertical tall surfaces
installed on a scale model of the type GB-5 control-
5
lable -'I'de bomb tested in the free-fll-htt tunnel.

Frur.- 6.- Sketch of forward fins sa-d ailerons tested on
1
a 5- cale model of the t.e "~,-5 controllable Flide
-.'-'b ir.; Ml-- -r.--'fe l .hc t t1;:-:.e- .

Pirure 7.- I.:etcy-c- ?" -1 '.--. t :, -:t r- '- e t:,d : -, tl:e
*1





lis.r e 0.- ffeCt ?C- Lr:c 7.e
fr-ee- lif t ...d e r,.:.. 1 ,-.... .. r,-i ._t a ~ -- c 1r- :,dc l 'of
t:n e t-p e .'M-5 c.-". l]L1ble ,l}:.e o:b.





a r-scail :-];.) 'F," th :,', '-- c :.nt r:laolc r lidE
S r : f c r f = L t

fIr-.2re J.- 'Tfect. r j 1*wer'-' 'c ..~ : : tre 1.- tr p s
u rt te d-ae rsl c ar ea r'ter f7a-, -. f a C .-Ecale rrF.'i'F
'-i 1i.1e t',!pe '?-. cr r'tr.?l -].ble li e.e b r-b. = '.
5 = 5 = = e .-C- .

Ficuure 10.- Effrect ..' ur.er-=uf.'race e .dFrlatr- upon the
r lin- rerit cha cter-'tic f a --cale -rodel :f

the type GP-5 c.ntrollable rlc.'e bo":b. = 6 ';
6e = r f = Ef a = C".










FITrFE LE'..NDS C.ntinued


'-ivre 11.- 'f!'ect vort Ccal tall area removed equally
fr.:m te. tv'n /jrtitl ti .r of a --scale nodel of
5
the t' .e C--5 1.rtrl r ibl e i d.- c )r,.. 6e =6Sq =f C0o


F: .--.re 1..2 Fff~ :t "f eC:'.:.r .'' "ert-f cal tail cre i fromr






1
_te :' t'a 3 i r .~cal t-lor l ,c f a --- cs of .el -- c the
t,-,-!o `P-P C.r-t.- t,-.-)ll a')] E c-I Or- :ob. T




5
o".f-.r ae 1?.- Ta e ,r-dl].ue!-r e I.f : c rt: E tc. ol ]-csl one upon
'stabilt- tI v ----rr.?er t ?-i t f a ,1-scale o" t --cl e model
or th- tFve G- ,ntrol ntrtabl l.aIde pi .me Aq'-pomb nt yaw.
Fe i -a : r n 1 Cr = -'-

F'i.ii: 17.- 7ffecr f -f t ,7cl hCfe .etCal ti l nIze a df

S- "

-"r.-,re .- 2t:.t.tlc !st1 ]- t:"h)ilit'r cr-Larc'acter ?tIcs

-o a -- thcae t ,.-?e! :- t.i t:rce 'i'F-' :ntr.ellable m lide
t" b._ ePq ":.-..F.. '. : '. l v r-~--,rt ae,, E ",inF.-ti p, encrIlates 6
"ri. crt t .e .. 1] t = 6'; 6P = r -t a


i.-ure ]s,.- rLf',c t .-, e -. i tr -.cn:. t he late a nel
sf attack charri -cale t.f a *th-S tc e -E the
t'cne tF-5 cntrollll l ble br de a '. c ar edqu'pperi wit lower-
surlated rEc-tanlr npl'.tes r.c 'ertcl tail
design 11. = = = 0.

i _'.ire 17.- "2 f'ect F. ..'f rn-1 ~ f t.....-!:- on the rolling and
yiawinr '-rment characteristics in yvw of a i-scale

vodeal :,f the tve S--5 cmntrcllable c1 Ide bomb.
;'erticsl tall 1: Ce -C r -: t Ef C.

Pirure 1F'.- Vsriatirn .f director nal stability with angle
of attack of a I-scale r.ot.el o-f the t.-pe GB-S
c:ntrolla l-e crlice brlbh a' cMrpared to that of an
Isolated rectangu..lar .ingn.








F ?-F,~T I.T'.-.EI Continued


Fi-ire 19.- effect of an--le of attack on lateral-stability
characteristics of a ---scale model o0 the tvte 'V--.)
5
controllable :lide bomb required with ori- i.el vertical
tails 1 and forward tails 1.2. 6r = 6f = 6e = 6a = 0.

Firure 20.- effect t of '-rle of att-ck u"'-n the directional
stability -::rameter Cn of a 4-scale -ir>l of the
type GB-5 controllable glide bomb.

FP-ure 21.- Aileron characteristics of a I-scale model
of the ty-P GB-C controllable -1:::.1 borb. = 0;
be = 6r = 6f = 0; .. = 0 O

Figure LC.- 7.fect :. elevator cif:lection on the aero-
c'-.-, ic churacter-.stlcs oi a -_c'le model of the
b
Lt,-,e '. -.. controllable gl:'oc b."1I. br = = 6f = 0;
= = 0.

_7. res 2. Sffeci of "'-Allers on the aerer"..',- c harac-
teo'- -ics of a --cale .:.>-l of the t *e :--5
controllable 11 1 b bomb. b6 = 6r = of = 00

'ure .-,- effect of doutle-Pslit rudders on the aero-
".iaM.lcs character -tics of a -scale model of tr.e
t pcon 1 e b. Double- rlit
rudders A; e. <.iiate t; 6a = 6 = = C- .


t...: : ..'r ,.';:r,..? h-'" ,'.., .",: '. : .* t.^ i : ,:': -* -' -scaie m ::icl of
t:. r -- -sclle PPauc of
-r. .::.- ._ T".- : .' --- : h, -- :,. ble-split

i *' *" -*. ; ? .- .'.- ^ -.' ; e : .. : .; p n t h e

S.e." ",r.a.rc -. .>[ c .'.- I::' .'-.cale nodel of the
ty: C 7-5 co:r, trI :l]ao e l 'c : ':. 'e = 6a = 6f = 0;
enadp.late ..

Fi[u-'r? ,.- ifect :f doti1 e-- 1 c rt.LIder deflection on
the acr:'d-,iJ I-.Ilc ch.artcter'I ti.cs ;f a --m le f.ode'l of
th~ t-ype (C--5 c!: tr'-:ll-bl -li-de b-,ib; d',.,tle-split
ruddE-rs 3; endrlj te J: 6.J = f = -'0; a = '








FIG'.'hE LE7-IE'3S Continued


i.-ure '25.- EfLfect cf outboard doubl.e-s-,lit flaps A
up.in the aerod.narric characteristics of a --scale
"ciel cf the t-Tne '3?-?1 controllable glide bt:nb
tf = .42b; cf = ..? "* e s a 'r = r'

Fiure 29.- Effe't of double-jrli t fla9 deflec tons on
the her.nDr, r&smc characteri'sticS cf a --? ale mod.el
f r.hF t"'e '33-5 controlldble rl de orr.mb. Cutbeard
di uble-_cl t -ft A: b f = .-c2b: f -= .3.'; C, = 6 = 00;
a = 80.

'rlr- e 7 .- Ti feet f l.?ov'e.-. 1pfA' ce in'i; ari flash? 1 upon
the ei.rDt-lnairic ch ir cteristic of m --i ale model of
the t e 3 -5 .onr.tr,1 labl. pl 1ide b l.. b = .4'2b;
cf = .,'3c; Ce = Ca = r. = 00.

Figure 1.- Effect of flra defllection -.n aerodynamic
char. te ti cs= of a ---.?cle model l -f the type CE-5
contr llable .' -idJe bor.b. Lower surface, 7.id panel,
srlit fiapr 1; U = b; c5 = .3.'; a e r = 00.

Pifure 2.- Effect of ;iyper-cur f2ce inboard flaos
upon tn? sern-.''iLric characteristic of a --scale model
f th the tvpe -7 co ..trollatle elide tomb. by = .42b;
Cf = .3,'C; Le = r a = r = 0

Figure .1'.- Effect of 1rsp 1uefl c ch-i raFct c ri. stc ?f i a '- c .e .dFi cf th e type GE'-5
cntroila.ble r,]ie bj b. U .per surfce, inboard split
fla ; b; = .4ib; cD = .C'c; Ca O = e'; a o.

"igure 3,4.- r.ffect of '.i-!: er.-.-L:ru '-fCE 11 i1r ard flaps 3 unon
the aerodUrnaL-.e 'rarc te"- it-,s .; a '-sceale mo.del of
the t;ype 'GE-5 cc-ntrollable olide borb. bf = .6Cb;
Cf = .3c: e = = =

Figure E.,- Effect c'f ilap deflection on the aerodynamic
character.'ltics of a 1-L, ule nrdel of the type CB-5
controllable glide bomb-. Upper surface, inboard
sp:llt flap ; hf = .6C.b; cf = .30c: 6a = br = 0;
a = 8.








PIGCUR I;E.TS Concluded


Figure 36.- effectt of upper-surface, outboard flaps 4
upon the aerod:,,'ni'c ch ra:ceristlcs of a --scale
'nodel of the type GE-5 controllable glide bomb.
by = ; c = .0c; e =a gr = 00.

Figure 37.- ",fiect of flap deflection on the aerodyvnaric
characteristics of a f-scale model of the t., e >.-5
controllable blde bo--.. U-.er-surface, outbcard
split flap 4; bf = .S'b; cf = .-nc; 6a = 8 = 0;
a = 80.

Figure t3.- Efect of u:-er-surface f2d-.s 5 u.:;r, the
aerd:.Trmic characteristics of a 5-scale :mudel of the
typ;E '-5 controllable rlidF bomb. bf = .6'b;
Cf = .30c; 6e = 6a = 6r = 0

Filure 31.- effect of flare deflection on the aerodynamic
characteristics of a --scale -o3:1 of the type V3-5
controllable Flide bot-b. U. rer Furface miid-panel
split flap 5; bf = .60b; cf = .3')c; 6a = 6r = 0;
a = )'3 *















































*2~ 915


--1;2~ ,


0 C
Q. +.






E>
0
00



o 0)



o ,d










0 10i

a 4.
I 4)



I O r-



0. 0)0)
0I 1



bo









*H
C-
































































Figure 2.- Three view sketch of the type GB-5 controllable glide bomb as originally
received. All dimensions are in Inches.


uM/ncAd/de -2.2"
M/swsr/x-ad nce. -20's

























































1
Figure 3.- Photographs of ---scale model of type
5
GB-5 controllable glide bomb.



















7


I


T
01


4r
M *0

0
d
O
-4



ct





a
. o
43 '0



ao






SWE
.t



CI I
**

a.0
i4



*r4


C^



i *4
Ix. *-


QIC"'


-4-



















7-0//- J
>w7,n Ao//


7o//- 7


7i/r / -2


TaZ//- 9
31n9 e 1o I


72"//-,5









T/ Y/e 17


T//-k7 77/i


Wm
/
*3
4

7

9
/o
//


5./
41.4
3.g


,,e
f8
4 a
z2
/..y


2.Z


7T,

21/
1/7.3'
i/3.9



/0.3
/6i


Note Chords of all tails equal to chord of Lail-1. Sectors indicate manner of
subdivision nf Lail-i bj eightrs to form other designs.
1
Figure 5.- Sketches of afl vertical Lail surfaces installed on a --scale model
e e G- controllable de bomb tested n the free-flght tunnel.
of the tjpe GB-5 controllable Slide Lomb tested in the free-flight tunnel.


7t

T711-10
47112/-/o


r






















N








N


*


r4
.C4



to
r

o o

U(
0) C

I c







42-
-1"











to
0.
oa
MO
0
010
00
(- 4
i-4
do
a
*0 -c



e *-i

>-4
I 0







.00








5..


VI


__
















I-0rfoc


C


-Ehdp/a/e 3


.l S3~D/ft rudders A
.30C

/ole: b za2.8 rm e/ r/es
C- 6.6 7noe/ /ncxte


-^ 4?4
We


Double Sp//t flaos A


Figure 7.- Sketches of glide-path controls tested in the free-flight tunnel
investigation of a -scale model of the type GB-5 controllable glide bomb.
5


poIlerwng
5 po,/er .~-^
\----- 7


.06C
7Z


w


~jsi~--c.s/p



























S ------


I -Fop 4

.30C


(uLpper surface)
--I-


t t-


.20 ----.60f -.


Figure 7.- Continued.


T
r














.4 -^ --i.-~~~~- -- --^ l ^ r ^ ^ ^ r- -- -
L. .




S__i I
II iv
t _
I I I















&A -_ A -4 _
-- : : : : l I- -


-'- ___'i +/ /_ _o -. __- .. --. .
1 1 II
S-i- i "
-L --- '- i- -- --- r- -f--t _-- f -1 --


.t. -;. ------y-- r : .~.---, --



I-C-!.^ II1- ;--I l -^- i--- -I !- .1



i I
_9& | I
-- ;-- .. .
i L -.-, -- ^ ,.i^ --- ^-- -p- ---- .... .










..... i ii -t ittf^t M-2 Itt+_^ ^^ al J ^-; ui^ -^ it 1 -








^. _i ,_m- It' Ifi- 1A_ --- --i




-~ -L

-9- 1
---^ -V T--r ^--- -I ----71 --- ^--- --- ---1-
1. _- 1-*1 ----
4 -




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L .- -f '7 1 4 i
---- I -- -- -
IF 'K- _- ___ IF

IS- 111 1 1 1' -.


I 9 I







--t-LL_ 5 EI IL_
L- 1. -1 -1- 1 -1 -11 1
^ =- _^ / i---


_< -5 __i _-;^4 4 ^ _, __ J _


-- -- 4 --- -
- ^ y f.i w.a f ~ 7.^ 7. ~ ~ -
~~^^ ~ ~~^~ ~~~~ ~~^I~~~~~~~1









^ : ES q ^l..... ... -. .. .= : ^ .? : .... ---.. -...-: ---- --"


41 -- --- -
4f -Z7:- -;1

--Z' 4 -- :-"= -,. '- .







F--t
-r _t,-4 I
-: \<--- i -^ a -i-- -it--iLi-:t----I-- f -i:.




















131
... .. .... .... -- .. ... .... -..... -

ItT II -_i_,I- .-.Lm-
J -1 -_ f 1-. .'..
: --- '.- *: -i-.-: .. .. : .. .. .. j : .j '_





TT- rr---- -- ---t-,;,-^ # .-< --A-- +-- -7 -----::--ti.-.:-. --i!.: -<-,
--- ----.t-^- --l ..... l.l --.-- r- _-T I_. _- t l-"1__


.. .. ---. ,., ,.. ,S ;..


....-':'. -... .. --.. ---_---i -',.. X- :-- --- -! Xl-" -
- -- -3 :- -J- --



^ .L -_ __ -: ; .. .. ^- __- _..
!\:--:








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UNIVERSITY OF FLORIDA
DOCUMENTS DEPARTMENT
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P.O. BOX 117011
GAINESVILLE, FL 32611-7011 USA




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