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RESEARCH MEMORANDUM
THE ORIGIN AJSD DISTRIBUTION OF SUPERSONIC STORE
INTERFERENCE FROM MEASUREMENT O F INDIVIDUAL FORCES ON
SEVERAL WING-FUSELAGE-STORE CONFIGURATIONS
111. - SWEPT-WING FIGHTER-BOMBER CONFIGIEUTION WITH
LARGE Aim SMALL STORES. MACE NUMBER, 1.61
NATIONAL -4DVISOM COMMITI'FJZ FOR AERONAWICS
TI33 O R I G I N AMI DISTRIBWION OF SUPERSONIC STORE
S m WIPr'G-FESEUGE-STO-E3 CONFIGURATIONS
By N o r m F. S m i t h and E m r y W. Carlson
1' A supersonic wind-tunnel investigation of the or igin and distribiz- t i on of store Fnterference 32s been performed i n the Langley 4- by 4-foot supersonic presswe tunnel a t a Mach num3er of 1.61 i n which segazate 2orces on e store, a fuselage, a sves-L wing, and a swept-h%gx-fuselege combinztion were measured. The s tore was sepmately sting-noanted on i t s own six-coxponent i n t e r m 1 bala-n-ce an& was treversed through a wide systennztic r a s e of spanw-ise, chordwise, and vertical sosftions. This report presents b t e on s configmation which simla%ed e fighter-bomber ei-1m-e wi-th e large and a s~zll external store.
The interference effects xeasured for the fighter-bomber con_figaa- t i on were similar in character and mgnitude t o those reported greviously f o r a heavy-bom5er corq"igvrztion h&ving the sane swept wing. Hence, the -vrirg is shown t o be the predominact corcFnent i n the production of inter- ference, with t'le fuselage secondLry. Tne differences in i r terference which nzre xeaswed can be explai-n-ed i? general or, the basis of the analysLs and force 5redsdown information presented herein d i n NACA Research Memo- r z ~ d u ~ s L55".3a and LS5E26a.
INTRODUCTiON
Reference 1 descr ibes in detei l an experinental investigation in
data or? stores interference vhich is general in nature md which provides R t&e Langley 4- by &-foot supersonic pressure t - m e 1 aimed a-i su;3plying
.
ar improved understandlpg of the soxrce of isterferences. The investi- gazion consists of masuremat of indlvidual forces mc morxents ( s i x com- pozelr-ts) on vericus sting-xounted stores i_n_ the vicini ty of severs1 fuse- lage, w i p s , &nd wix-f-xelege conainatiors. Icdiv+du.zl forces md noments (foxr corqonents) were rxw;rea on the wFng an5 fuselage combinatioss.
Re2erences 1 ard 2 present the force information a'otainefi a t a Xech cljmber ol" 1.61 on a swe?t-wing heavy-bomber-type airplm-e and a large store (or nacelle). Tke ?resent repcrt presents sixilar force infcrm- t io r - a t M = 1.61 on a swept-wirg fighter-boxber configuration with a large and a small s-lore. The ds."Le. are presecteci wit'! a very limited analysis in order to expedite gublicatiol1.
CL
c,
Lnag coefficient of wing or wing-fuselage combination indicated
l i f t coefficient of wing or wiry;-fuselage coxbination as noted
by subscrists, - L i f t
ss
pitchirig-zorzt coefficient of wirp; or wing-fuselage combine-
.L don as roted by subscri2t'SY Pi tchirg xo~.ea% qsc
drzg coefficient of store, - Drag qF
base drag coefficierit or" store, - P B ~ F A
l i f t coeff ic ier t of-s-core,
pitekicg-morezt coefficient
L i f t - qF
of store, Pitching 2oment
qFZ
d A
S
F
pBS
b/2
2
X
Y
z
c
B
side-force coef2icien-b 02 store, Side Force
SF
yawirg-zoy-ent coef2icient or" store, Yzwing moxent qFZ
t o t a l 1iTt coefficient of complete cowiguration (wing-fuselage
clus store) based on wing area, C% + C L ~ F
rnean aerodp-mic chord of erg, 6.58 in.
mea or" s tore base
t o t a l are= of w i n g semispan, 0.5 sq f t
r~x-h-xm f ron ta l are& of s to re
dynmic pressure, Ib/sa_ ft
pressure coefficient on store base,
ning semispm, 12 in.
s tore length
P - Po 90
chorciwise posit ion of store midpcint, xeas-zed Trom sxbitrazry point 0.652 in. behind fuselage nose (see f ig . I), in.
spmwise posit ion of store cester lice, measured fron fuselage cerher line, in.
ver t ica l pos i t ion of store center line, neasured from wing chord plane, positive do-mxnrd, in.
cotangent of Mach mgle, / z T
Subscripts :
0 f ree stre&T
W wing
he wing-fuselage combiration
S store
t total, for conplete con?igwe$ion ( w ~ a g fuselage plus store)
The xodels an2 general mzngeme-llt of the tes t se tu3 are shown i n figure 1. Figure 2 shorn photographs or" t he mde l s md boundary-layer bTypass F1at.e. Coxplete dimensions of the xoiiels 2se given i n f igure 1 and ta-cles I and ST. Reference 1 aescribes in t ietail the xodels, eqLip- nent and t e s t netkods. Tbe m C e L investigated herein expioyed the same swept wing -vhicX was used io referemes 1 and 2. -4 fuselage of grea€er diarr,e%er and lower overall f ineness ratio was designed (using the Sears- €iaacB shape of r e f . 3) t o prodace E: midrirg c c n f i g m e t i o n t n i c a l cf the propori;ions of a fignter-bom3er a in la r -e . (Although e?' lower overell f i resese re t ic , ;he figkter-bomber Scselage has a nose and afterbody of higner fir-mess ra t lo tnan $he heavy bomber. ) The models 05 the f ighter- boz3er cocligxratior of the present -ces-Ls and the hemy-bonber cor.figura- tic11 of r e f e r e x e s 1 a d 2 m e compared in f igure 3. It w i l l be noted tha% the two ?no&els (includ5ng s tores) are a c t - a l l y of dWfererLt scale when referred $0 %he size of the correspon5ing full-scale airplmes. The resu l t s of t e s t s of these twa mo&els pay therefcre be conpzed to obtain so1r-e inforxation 03 the effects of ckmging fuselage shape and size, o r CES be considered as resexrch data on bifferent-scale models of different tyges of a i rp lmes .
It shoulC also be noted il? coxparirg the %wo corfigurations that the fighter-boniDer was & cldwlng config-Dation (flg. 3) while the heavy bmber was e high-wi:._g configuratioc dtil the w i ~ ~ loczted a t 25 percer,t or' %he fuselage dianeter &bow tile fuselage center lise.
Along with 5k.e large store ased i n the reference reports, 6. smeller georretrizally slmilar store (see f ig . 2(b) m.d table I) wzs icvestigated for EL range of s tore gosi t ions in %he v ic in i ty of %he Xing.
A l l tes5s were rm with boundary-layer transition fixed on a l l sur- faces as descrT5e5 in refererce 1. The x - ~ l e of attack of the wing- fGselagc cozbinatiol- was vm-led from 00 t o bo, wit:- %he store rexaining
z
a t a = 0'. The relative accxzacies of the dz%Le in t h i s repor-l are t'ne s m e as those l is ted in references 1 and 2, and are give2 in tke following
I table :
x, in. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .f0.025 y, in. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20.05 z , in. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . t0.05
9, . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . w.010
Cns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -10.005
s, deg . . . . . . . . . . . . . . . . . . . . . . . . . . . . W.2
Wing-fuselzge : 'I
CD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B.0005 CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43.005 Cm . . . . . . . . . . . . . . . . . . . . . . . . . . . . . w.002 a , d e g . . . . . . . . . . . . . . . . . . . . . . . . . . . . W.1
i
The t e s t s %-ere perforxed i n the Langley 4- by 4-foot supersonic p re s sme t ume l at a Mach rtmber of 1.61 correspondhg to a Reynolds num- ber per foot or" b . 2 x lo6.
RESULTS AJlD DISCUSSiON
2asic Data
Isolated s tore m-d Fiing-f-cselsge data.- The fcrces a d moments on t'Ee isolated s tore are ?resented in references 1 an6 2. The data f o r the isoizted sw?pt xi~g and For the isolzted fign-kr-bomber wi-llg--fusel.zge coKbination are presented in f i g z e 4. (The forces on the isolzted f ighter- bomber fuselege were not reamred.)
Chordvise plots of rorze coefficients. - The basic data for the lmge store in the presence of the wi-r?g-fuselzge oombinztion &re presented in f i g w e s 5 t o 10. Data f o r the wing-fmel-e combimtion in the presence
fuselage plus store corzigurations are given iz fig-ares 14 and 13. Basic a of t k e l uge s to re a r e g iven i n f i gu res 11 t o 13. Drag and l i f t of winz-
data for the large store in the presence of the wing alone ar_d f o r the wing a1or;e i n t he presence or' the large store will be fo.A?d il? rel'er- ences 1 and 2. Bo data have beer_ obtained for the s tore in tlhe presence of the fighter-bomber fuselage alone.
The data are presellted ir! the form of g l a t s of coef f ic ien ts agahs t a chordwise-position pwmeter vhich is 6, I"unctFo--. of tile posit ion of t'ne miiipoint of tile store. Offset vertical an& korizcstal scales are used as descri'oed i n &etail in reference 1. Tecknique for p lo t t ing tks data pre- vents crossing of the cwves =?a perr i te fairirs of the chordwise vaxia- dons of coefficiects as a "f&?ily,ll tnere'cy obtaicing a nore accurate f a i r i r g of %he tes t po ic t s . On eac?. f igure is shcwn a sketch of the con- figuration Ifivoived. Tne spawise .%a& chor&wise positions a t whicn mees- urercents were cbteized are icdicated by the apsropriate s-ymbol on the gr id .
2.
The store and ving-flzselage drag date. presented have been corrected t o corressorrd t o a base 2ress-ure equal t o free-streaT- static pressure. The 3ase 6rag coefficierkts I"or t ie s tore are presented ir, figure 6. The store pitchirg-rnorxent m d yawing-nonent data are presel-rted with refer- ence to the s tore zose irr % h e basic data f igmes.
Curves f o r wing-fuselage forces (figs. 11 t o 15) are show- dashed betwee2 tes t points for x = 6 ar& x = 12 because ol" the presence of store st ing interference o r wing-fuselage forces a+, these store positions. This interference w s also present a t x = 18 5.3 references 1 and 2 but was elirr?i:;ated in the gresext tes ts by u5ilizing a different s t ing a t x = IS.
Presentea in figures 16 t o 24 are the basic da%a for the small s tore i n tke presence of the Wing-iXseiage combirration an& for the wing-Ihselege coz3inatior i? the 2resence of the small store . Drag ana l i f t of wing- fuselage plus store config-nztions are give= in figures 2 j m ~ d 26. The exister-ce of only three data pcints f o r each chordwise plot rakes fairing of the c-zves diZficult er,d soxewhat wbi t ra ry . The fair ings shown are based on experieme geFned ir_ fairicg rare conplete plots for the large s ta re c d tize r e su l t of comparisxs cf the data fo r the srnall anri the la rge s tore ( to be presented in a la te r sec t ion) .
h a l y s i s
Eeflrscces 1, 2, h?ii 4 kave presec-kd znalyses of the data f o r the heavy-bmker configwation, including ccntow mappirg of the forces, con- zribckion or' corqonents to interferences md the erfect of vmiozs param- e ters such as a-ngle of attack an& store vertical height. Ir order to expedite yLblicatim of the data presented kereIn, no such ar?,alysis has been grepzred. Usi l"g the basic data plcts presented, however, the s&Te so r t of ma lys i s can be prepared as desired.
L
m Tie malysis presented herein vi11 be l h i t e d t o some comparisons
of the forces 02 both store and -dng-fizselage for the heavy-bornber (from
sons of forces measured fo r tlrle flghter-bomber configuration with a l m g e and a srrall s tore .
f re fs . 1 anci 2) and the fighter-boxber co?Tigu-ations an& soxe compri-
Coxprison of forces 011 lmge s tore ilr presence of heavy- and fighter- bonber coc3iguration.- The drag, lift, el?d side force of t he s to re i n t he presence of tiie swept-wing alone (from re fs . 1 anz 2) , tne fighter-bomber and heqy-%o&er conyiguratione are show- in f iguzes 27 t o 30.
It QZS g o h t e d o a t i_n_ reference 1 that the pea4 of the drag inter- ferences produced by the w i n g were reduced by the (heavy-bomber) Pae lage because t'ne interference pressure fields ol" the wing arlO'fuselage tezd t o opsose oze anotcer. In general, adding the fighter-bonber Zuselage is seen fro2 I'igu-re 27 to sbLla r ly reduce the interferences produced by the w i n g , alt%ou&n t o a lesser extent. Figure 28 has been p repzed -Lo show nore clexrly these eTfects. The contribution of the fighter-boxber
heevy-borrber ?uselage except for some of the more forwasd store positio_n-s m d except f o r y = 3.0, where t h e l a g e r diameter of the fighter-bomber
nentioned smaller interfereg-ce drags on t b e store are e. cozsequence of the smaller pressure gredients produced by the greater Tineless ratio of the f ighter-boxber fuselee 2ose azd afterbody. Tkse interference effects would not be expected t o r e r a i n smaller at lower (pzr t ic-dar ly t ransonic) Nach nmiaers bece-cse of she greater fusela.ge frontal arez involved.
4 fuse lwe t o store drag is seen t o be generally less than K i s t of the
f fuselage produces closer proximity bet-men fuse1-e and. store . The afore-
The curves for s tore lift (fig. 29) zre i n very close agreement. A s pointed out in the discussion of ~ o d e l breakdown d&ta in references 1 m d 2, t k e s t o r e l i f t i-n-terferences are due almost e n t i r e l y t o t'ne -flip<.
The differences prodxed by the two fusel-es would therefore 5e expected t o be small.
As wo~LLd be expected, the effect of fu sehge col.figu-ra-liol? on s tore s ide Torce (fig. 9) is small for s tore posLtions towzrd the dr!! tLp: bu t qu i te lmge for s tore positions zear the fuselage. Reference 2 shows t h e t aciding the fuse lege cont r ibu tes s ign i f ica t s tore s ide force per t ic - CLarly f o r <he icbosrd store positLons.
Coxpuison of forces 02 heavy- azd fighter-bozber configurations in presence or" large s to re .- The wb-g-fuselzge lift and drag aad t o t a l con- figmation (wirg-fmelage plus store) l iSt r-rd in the presence cf t h e l a g e s t o r e a r e sho-m i n figwces 31 t o 33. The l i f t cmves ( f ig . 33) are e l l essent ie l ly of the saxe s h g e a&, in genera l , L i t t l e Fq~or t an t
is zoted. a difference Setveen the interferences incurfed by the two configurations
Examirm.tion of the &zgs for tke t m i s o h t e d wing-faselege com- b i n e t i x s ( P i g . 9 of r e f . 1 an5 f ig . 4 of ?resent report) shows t h a t the drag coefficient f o r the fLghtsr-bo:r;ber I s as2roximtely 0.0012 higher (based 311 the sm-e xirg area) %han tha t for the heavy bomber, prlncipally as s, reszit of %he l c g e r Tzselage fron5al =-ea of the forxer. This dif- ference mist be t d ien i3to accomt i n coxpzic4 the interference of the large store on the tTJo wing-fsselage configwatiocs, since for equel illtsrference the Zlghter-bolf'er m d neavy-boy-ber curves ( f i g . 31) would Se segara-ted by e cosstant ixrexer.,t 02' O.COl2. Figure 32 shows the increxmtal drag prodme& by the store for the two corx?igwations. It w i l l be seen thet tile drag ircurred by the fighter-borfcer co_Y.figuration i s l e s s in the regicn of the ckzg geak (which hes beel shown pevlous ly t o be due p r i m r l l y t o storz-vilng in%erference). This fact p i n t s t o decreesej. .&verse interference or' the sto-rz on t h i s fuselage. Immediately &he& of' *his region t'ze &rag iricwred by Yne fighter-bonber configura- t i o c is generally higher. This fact points to decreased beneficial inter- ference of the stcre on this intsrferences thus i-n-dicated gra6ml swfece slope of tne heavy-botker Pxelage) vhfcn jezted f roctal mea on which
A s a cor,sequence of the
~
fuselage in t h i s region. The decreases in =e believed t o Se a consequence of the xore fighter-bonber fuselage (compzred with the consequently preser;ts a samller l oca l prc- the store press-me field can a c t .
higher wing-fuselage anti store drags over the rmges j-st discussed, the t o t a l drzgs of the cocqlete (wirq-fuselage plns store) figh5er-boxber ccnfiguration are shorn- i n figure 31 to be higher thar. for the heavy-bomber configuration cver the entire range of store poai'iions .
Ccnparisor, of forces on Imge md snlai.1 s to re i n presence of Tighter- bomber co:?fig"a%ion. - Dr&g, l i f t , and. sXe-force caefficients for the smll and la:-ge s tores in the p resexe of the fighter-bomber configmation s r e corqered i n Zlguze 34. Althoug5 t'sere i s a resenbkrxe between tine cmves for srmll an& lzrge s tores , sme skl:?iLag is i n ev5dence and very nluch Larger changes in forces z e ger-erally measured for the small store.
T h i s saxe phmorne2o-r i s 2o"mted ou t in re fe reme 4 for t h e same s tores ir t3r-e pesence of the! heavy-bocfaer cocfigmat2on. These e f fec ts a re ex7lained by the fact tzat %he smzll score can be more caxsletely s u b merged i - a region i n vhizh force is gerLerz;-le& (due t o pressure gradient 33: flow deviatic:: or Soth) i n cne Zirection. The i w g e store, on the otner nm2, T;eE& t o exterd tbxrmgh sevsral such regions so t'nat lower peak values or' force coefficients result . A cletailed discussion a d aqalysls of the f L m f i e lds from the stzxlpoi:nrt of drag i s presented in rsf'crence 1 znA frox the stan5>cirit oi the otner forces in reference 2.
--.e 3% peaks tex5 %o be nerrower m-d the gra6ients becoxe somewhat lazger.
Compzison of forces on figkter-bocher configmatic2 5n presence of large arrd small store. - The 1ir"t acd 6rag of the xing-luselage con- bination i s S i i D C - i- fS:s-e 35 'to be influenced t o E lesser clegree by
3 the smll store than by the larger s tore . The horizontal sh5ft which is evident between the two curves i s & r e s u l t of the displacement of the store end i t s pressure f ie ld &de to a change i?" store length. The smaller m i m ~ u interference effects of the small s tore me the r e s u l t of decreased extent OZ t he store Dressme field.
J
CONCLUSIONS
The res ld ts of a supersonic win&-tumel investigekioz at e Mach EUT- ber or" 1.61 i n which separzte forces were measured on a swept w i n g fighter- bonber configuration and on two sizes of externzl s tores for & very wide rmge of store positiocs srovi&e the following conclllsions, based on a l b i t e d analysis of the date:
1. The interference efZects of the fighter-bomber on the store, as well as the s tore on the fighter-bomber, were s i ~ ~ l a r in chwzcter t o those reported previously for a bemy-bonber-store co_nfiguration using the same svept wing and store. r(
r 2. The differences iz interference which ere neas-med can be explai-n-ed in general on the 32sis of the anslysis znd force breekdown inl"or~2tion presented herein end In NACA Research Memorazidum L55KL3z and ~ 3 5 ~ 2 6 a .
3. The d ~ a g interferences (both favorable and unfavorable) produced on the s tore by the fuselege eppeas, i n general, t o be smller for the f ighter-bomber configlzratioa thazin- ?or Yne b&s,vy-bomber collfiguztion as e r e su l t of reduced presswe grsdients produced by the higher fineness rat-I-o fighter-bomber fuselage nose and te i l sections. Similcrly, the dreg interferences produced on the fuselage by the s tore are generally snel ler as e result of smller slopes of the fkselege suface upon which bhe interference pressures c%?- act . L
4. The small s tore incurred larger rnqirxm interference forces (irr. coefficient Tom) thzn did t h e l u g e s t o r e . The m a x i m u m interferences produced on the wisg-fuselage combkation by the small store were gen- e ra l ly smller t h a ~ those groduced by -Lee large store.
Lapgley Aeroneutical Laboreto-q, Na-LiOnEl f!dvisory Corimiktee for Aeronau+,ics,
k ~ g l e y Field, Va., July 15, 1955.
2. Smith, Xorman 3’. , all5 Carlsoz, Harry W. : The Origill a::d Distribution of S-cpersocic Store Interference -Prsn MeasureEeil-k of Individual Forces on Several Wir~-Fxselege-Store ConZigwaticns. 11. - Swept- Wi::g Xeavy-MniGer ConfigzatLon Vith Le_rge Store. Lateral Forces azd P i t d i i n g Mome=ts; Mach Xumker, 1.51. ?MCA €?I4 L55326a, 1955.
t i o n Variables on Store Lc&s at Supersocic Speeds. NACA 31 i55EO5, 1355.
......................... a . e. a 0 . . o m . 0 .
a a . 0 . 0 .... 0 . . m a NACA EN L5ji301 :$1 0 . ...... ............ ....................... 0.0 .om0 0.0
c
?
Fuselege : M a i m m i dime-ler. in . . . . . . . . . . . . . . . . . . . . . 3.942 Elz~inum fronta l mea (serricircle). sa_ ft . . . . . . . . . . 0.0424 Szse dia ie te r . in . . . . . . . . . . . . . . . . . . . . . . 2.&k Base mea (semicircle). sa_ f t . . . . . . . . . . . . . . . . 0.0226 Overall. length. i n . . . . . . . . . . . . . . . . . . . . . . 37.452 Nose f ineness ra t io . . . . . . . . . . . . . . . . . . . . . 6.1
Overall fineness r c t i o . . . . . . . . . . . . . . . . . . . 'I M-terbody Tineness rr;tio . . . . . . . . . . . . . . . . . . 3.4 9.5
i STeGt Wins : SenisDan. i n . . . . . . . . . . . . . . . . . . . . . . Mean aerodynamic chord. i n . . . . . . . . . . . . . . . kea. sedspan. sa_ I"t . . . . . . . . . . . . . . . . . Sk-eep (c/4). deg . . . . . . . . . . . . . . . . . . . Aspect r a t i o . . . . . . . . . . . . . . . . . . . . . TEper r e t i o . . . . . . . . . . . . . . . . . . . . . . CeEter l i c e chord. i n . . . . . . . . . . . . . . . . . Sectlon . . . . . . . . . . . . . . . . . . . . . . . . .
. . . 12 . . . 6.780 . . . 0.500 . . . 45 . . . 1.: . . . 0 - 3 . . . 9-23 NACA 65~-006
Store : M a x i m m diaTeter. in . . . . . . . . . . . . . . . . Maximm fron-lel area. sq f-t . . . . . . . . . . . . Base d h z e t e r . i n . . . . . . . . . . . . . . . . . Base =ea. sq f t . . . . . . . . . . . . . . . . . . Overall length. i n . . . . . . . . . . . . . . . . . Nose fineness ratio . . . . . . . . . . . . . . . . Afterboay Tineness ra*io . . . . . . . . . . . . . Overall fineness r&io . . . . . . . . . . . . . .
Small Large 1.1 1.5
0.0066 0.0123 0.704 0.96 0.0027 0.005
8.8 12.0 3 3
1.82 1.82 8 8
-0.632
1.061 1.317 2 * 77s 3.635 L. . 491 5 3k7 6.204
.2Q4
7.060 7.921 8.778 9.634 lO.k?S 11.347 12.203
13.921
15.633 16.4.30 17.346
13.061:
14.777
0 . OCO .271 .45c .6m. - 736 .857 .968
L. 070 1.164 1.251
1.407 1.477 1.541 1.620 1.634 L.7OLL 1.749 1.789 1.826. 1. 878 1.887
1- 333
x, ir,.
- 18.2~7 19.064 19.g20 20 - 777 21.633 22.489 23 - 345 24.20'7 25.063 25.920 26.774 27.632 28.489 29.349 30.206 31.063 31 * 919 32.775 33.532 34 * 493 35 349 36.206 36 798
radius. in.
1.910 1 . 9 p 1.946 1.938 1.966 1.970 1.971 1- g7 1.960 1.949 1.933 1.914 1.891 1. e64 1.832 1.797 1 - 757 1.713 1.665 1.611 1- 553 1. QO 1.422
t of 4 Componenl s h i n quge balance and model center of & w h N
Store - support s b g
-..!.arqe sTore (extreme spanwlse ( chordwise posillons shotml
"2, Slore vertical position in inches
Notcs : I. Store nose and a f te rbody a re og ive bod ies of
r e v o l u t i o n . C e n t e r s e c t i o n I S c y l i n d r i c a l .
Wing dimensions Semi -span 12 Sweep I 4 50
2 . S m a l I . s t o r e i s 1 . 1 i n c h e s d i a a e t e r , g e o m e t r i c a l l y A s p e c t r a t i o 4
3. F u s e l a g e i s S e a r s - Iiaack shape o f r e f e r e n c e 3. $- Chord 9 . 2 3 I . A l l d i m e n s i o n s i n i n c h e s . S e c t i o n 65A-006
- 9
s lml l a r t o l a r g e s t o r e . T a p e r r a t i o 0 . 3
Figure 1.- Layout of models showing dimensions of components and ranges of store positions investigated.
H
\j; 8 0 I"
e . a a e a o e a
1
i
i
"i
L-87526 (a) Models nomted on support slate.
Figure 2.- Phot0grep.h of models. Boundary-layer transition s t r i p s not shown.
Figure 2. - Concluded.
Figure 3 . - Comparison of' fighter-bomber fuselage of present report with heavy-bomber fuselage of references 1 and 2.
E 3
o fighter- bomber wing-fusekge swept-wmg alone (refsland2)
m
n e
Figure 4.- Lift, drag, and pitching-moment characteristics of the isolated swept wing and isolated fighter-bomber wing-fuselage combination. M = 1.61.
E P
" " ." . ". .
K U
.40
.35
.30 2 5
20
.I 5
.I 0
05
a 0 0
u 0 -.05 P 0 -.I 0
b o 0 0
0 0
v 0 .20
A 0 .I5
0 0 .IO
0 .05 0 0 0
-.O 5
-10
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise position parameter, x --By , in.
(a> z = 1.15 inches; a = 0'.
Figure 5.- Drug of large s to re i n presence of wing-fuselage combination. (Drag corrected f o r base pressure. ) M = 1.61.
Y,'n. ~1 3.0
u 4.2
v 5.4
b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
0 12.6
15.0
0 18.0
u t-l UI X B
c b
e 8
.40 .3 5
.30 -25 .20
.I 5
.I 0
05
a 0 0 P 0 -.05
p 0 -.I 0 h' 0
0 0
n o
v 0 .20
A 0 . I5
0 0 .IO
0 0 .05
0 0 0
-.O 5 - ~n
b r
. I " - -20 -I 6 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwisc position parameter, x-By, in.
(b z = 1.67 inches; a = 00.
Figure 5. - Continued..
y,in. a 3.0
u 4.2
v 5.4
b 6.6
u 7.8
0 9.0
v 10.2
A 11.4
0 12.6 15.0
0 18,O
.40
.3 5
30 25
20
.I 5
. I 0
Q" x) 5
- a 0 0 u
-E 0 -.05
%i P 0 -10
+ K
0 ;F
0 0
v 0 .20
A 0 .I5
0 0 .IO
0 0 .05 0 0 0
-05
-.I 0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise position parameter, x -By, in.
( c ) z = 2.09 inches; a = o , 0
Figure 5. - Continued.
Ll
U
V
b
0
0
V
A
0
0
0
Y, In. 3.0 4.2
5.4
6.6
7.8
9.0
10.2 11.4
12.6
I50
18.0
.40
.3 5
.30
.25
.20
. I 5
. I 0
0" 05 0 - 0 0 0
v 0 .20
A 0 -15
0 0 .IO
0 0 .05
0 0 0 -.O 5
I n -.I u
-20 -16 -12 - -8 -4 0 4 8 12 16 20 24 28 32
Chordwise positlon pornmeter, x -By, in.
(a) z = 2.09 inches; u = bo.
Figure 5. - Concluded.
Y, In. a 3.0
p 4.2
v 5.4
b 6.6
0 7.8
4 9.0
v 10.2
A 11.4
0 12.6
n 15.0
0 18.0
Z E
+ c !! Y y. Y- Q 0 V
,s Q
cn
.40
.35
.30 25
.20
.I 5
1 .I 0
.05
0 0 0
0-05
F o-.Io a 0
0 0
0 0
v 0 .20 A 0 . I5
0 0 .IO
II 0 .05
0 0 0
-.05
-.I 0 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position pornmeter, x-py, in
(a) Z = 1.15 inches; a = 0 . 0
y, in. 3.0
u 4.2
v 5.4
b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
0 12.6
15.0
0 18.0
Figure 6.- Base drag of la rge s tore i n presence of wing-fusel-age combi- nation. M = 1.61.
..... . . a..aa .... . . ....
I
.40 -35
r( c
" - " .
c .I
0" d
e C
0 9! i;
5 0
.30 25
.20
.I 5
n .I 0 , .05
a o o a 0 "05
v 0 -.IO
a 0
0 0
n o v 0 20
A 0 -15
0 0 .IO
b 05
0 0 0
-05 -.I 0 .. -
-20 -16 -12 -8 -4 0 4 0 12 16 20 24 28 32 Chordwisc positlon paturneter, x-By, in.
(b) z = 1.67 inches; a = Oo.
Figure 6. - Continued.
Y, In a 3.0
9 4.2
v 5.4
b 6.6
o 7.8
0 9.0
P 10.2
A II.'l
0 12.6
15.0 0 18.0
a *
a . mmeam
.40
.3 5
.30
.2 5
.20
.I 5 .IO
.05
e 0 0 0
E p 0 -.05
m" W D
P 0
1 v 0 -.IO ul U e L O
A 0 .I5 0 0 .IO
0 0 .05
0 0 0 -.05
-.I 0
-20 -16 -12 -8 -4 0 4 8 I2 16 20 24 28 32
Chordwise position parameter, x -& , in.
(c) z = 2.09 inches; a = 0'.
Figure 6. - Continued.
Y, In a 3.0
9 4.2
v 5.4 b 6.6
0 7.8
o 9.0
v 10.2
A 11.4
0 12.6
0 15.0
0 18.0
F wl UI x z
4 P
.40
.3 5
.30
.2 5
.20
#I 5
1 . I 0
.05
0 0 0
CI 0 -,05
v 0 -.IO
a 0
0 0
n o
v 0 .20
A 0 .I5
0 0 .IO
0 0 -05
0 0 0
-.05
-.I 0
-20 -16 -12 -8 -4 0 4 8 I2 16 20 24 28 32 Chordwise position parameter, x -By, in.
(a) z = 2.09 inches; a = 4".
Figure 6. - Concluded.
Y, in 3.0
4.2
5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
Z
F UI L" UI X e
m a a a a w a b b
.4
.3
2
I
a 0 0 J* D 0 -.I
- v 0 -.2 V
4-
.- 5 L O Y-
5 0 0 s +- 0 0 k - g!
#J A 0 . 3
v 0 .4
0 0 .2
0 0 . I
0 0 0
-.I
-. 2
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise posltlon parameter, x - f i t In.
y, in. 3.0
42
5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
!2 (a) z = 1.13 inches; a = 0'.
Figure 7. - Lift of large store in presence of wing-fuselage combination. M = 1.61.
u1 t' VI 5: 0 P
"
0 3 .)
*- .I- -
.4
.3
.2
.I
0 0 0
u 0 -.I
v 0 "2 b o
0 0
n o
v 0 .4
A 0 .3
0 0 2
0 0 .I
0 0 0
-.I
-3 .- -20 -16 -12 -8 -4 0 4 8 I2 16 20 24 28 32
Chordwlse position porometer, x-By , In.
(b) z = 1.67 inches; u = 0'.
Figure 7. - Continued.
Y, In. 0 3.0
4.2
P 5.4
b 6.6
0 7.8
9.0
v 10.2
A 11.4
0 12.6
15.0
0 l8lO
2 8 cn
a 0
u o v o a 0
0 0
0 0 0 0
4 0
0 0
Chdwise positlon pammeter, x-fiy, in.
Y, in 3.0
4.2
5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
( c ) z = 2.09 inches; a = 0'.
Figure '7. - Continued.
1 I
" ". - # c
m m m o m
m m m
..
.4
.3
.2
. I
a 0 0
u 0 -.I Y 0 -.2
a 0
0 0
n o
v 0 .4
A 0 .3
0 0 .2
0 0 . I
0 0 0
-.I -7 .-
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position pammeter, x-fly, in
(a) z = 2.09 inches; a = 4'.
Figure 7.- Concluded.
Y, In a 3.0
U 4.2
v 5.4
b 6.6
0 7.8
a 9.0
v 10.2
A 11.4
0 12.6
0 15.0
0 18.0
I' b 0 b 0
b b b b b O b a b
b b
t0.Y -0..
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chwdwise positlon patumeter, x-Py, in.
d
D
V
b
0
0
V
A
0
0
0
y,in. 3.0
4.2
5.4
6.6 7.8
9.0
IO 2
11.4
12.6
I5 0
18 0
Figure 8.- Pitching moment of large store i n presence of wing-fuselage combination. (Center of moments is store nose. ) M = 1.61.
# I
g 0 0 . 2
0 0 . 1
0 0 0
-.I
-. 2
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise posltlon parameter x -By in.
(b) z = 1.67 inches; a = 0'.
Figure 8. - Continued.
ylin. 3.0
4.2
5 4
6.6
78
9.0
IO 2
11.4
12.6
15.0
I8 0
b b b b b b o b
b b
b b
b b b b b b b
+ E 0 E
E F t .- 0
Q
.4
.3
.2 .I
a 0 0 0 0 -.I
I 0 -.2
L O
0 0
0 0
v 0 .4
A 0 .3 0 0 .2
n 0 . I
0 0 0
- I - 3
L
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise posltion pornmeter, x-fiy, in.
( c ) z = 2.09 inches; a = 0'.
Figure 8. - Continued.
y,in.
a 3.0
u 4.2
v 5.4 b 66
0 7.8
0 9.0
v 10.2
A 11.4 0 12.6
15.0
0 180
c 1 1 a
"
.4 3
2
. I
f a 0 o +- ci 0 - . I 5 P I 0 "2 8 a 0 'c *- aJ
+ 0 0 E n o p '0.4 .- 5 A 0 . 3 'E g 0 0 . 2 z
0 0 * I
0 0 0
-.I
-. 2
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise poshon parameter, x 'fly , in.
(a) z = 2.09 inches; a = 11. . Figure 8. - Concluded.
0
. .4
.3
.2
.I
a 0 0 u 0 - 1
p 0 -2 b o 0 0
0 0
v 0 .4
A 0 .3 0 0 2
u 0 . I
0 0 0
-.I
-.2
-20 -16 -12 -8 -4 0 4 8 I2 16 20 24 28 32 Chordwise posltion parameter, x -pY , in.
(a) z = 1.15 inches; u = Oo.
Figure 9.- Side force of large store in presence of wing-fuselage conibi- nation. M = 1.. 61.
Y, In. a 3.0
u 4.2
v 5.4
b 6.6
0 7.8
n 9.0
v 10.2 A 11.4
0 12.6
0 15.0
0 18.0
. "
m e m m m
". " " -
N
I .4
3
.2
.I
0 0 0
P 0-1
v 0 -2
L O
0 0
0 0
v 0 .4
A 0 .3
0 0 .2
0 0 .I
0 0 0 -.I -.2 ~
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise posltlon patumeter, x-By, in
(b) z = 1.67 inches; a = 00.
Figure 9. - Continued.
Y, In. 3.0
4.2
5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
UI l+ Ul
P
..*a a a
...a ..... a .....
..a
a
. . a a .
. . a a .
a . . . a . . a
a .
a . ..... a . ...a I)
a . a .
a
a . ..... a .
.4
.3
.2
. I
a o o u 0 :I
v 0 -.2
a 0
0 0
0 0
v o 4
A 0 .3
0 0 .2
0 . I
0 0 0
-. I
-.2
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise positlon parameter, x -B, in.
Y, in 3.0
4.2
5.4 6.6
7.8
9.0
10.2
I I .4
12.6
15.0
18.0
0 o m 0 .
o o a o a
4 , f t " -
._ _" ""
.
-0 al
u)
.4
.3
.2
.I
n o 0
u 0 -.I
F 0 - 2
a 0
0 0
0 0
v 0 .4 A 0 .3
0 0 .2
0 0 .I
0 0 0
-.I
"2 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise posltlon parameter, x-By, In.
(d) z = 2.09 inches; a = 11.'.
Figure 9.- Concluded.
Yl in 3.0
4.2
5.4
6.6
7 8
9.0
10.2
11.4
12.6
15.0
18.0
: 0:
c C
E E
.4
.3
.2
.I
n o 0
u 0 -.I
v 0 -.2
a 0
0 0
0 0
v o . 4
A 0 .3
0 0 .2
n 0 .I
0 0 0
-.I
-. 2
-20 -16 -I2 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise positlon parameter, x -by, In.
(a) z = 1.13 inches; a = 0'.
Figure 10.- Yawing moment of large store in presence of wing-fuselage cod inn t ion . (Center o f moments is store nose. 1 M = 1.61.
c I
n
U
P
h
0
0
V
A
0
U
0
Y, I l l
3.0
4 2
5 4
6.6
7.8
9.0
10.2
I I .4
12.6
15.0
18.0
I *
s"
+ C a E
P E 0 A
ui 6
.4
.3
.2
.I
a o o u 0 -.I v 0 -.2 L O
0 0
0 0
Q 0 . 4
4. 0 .3
0 0 2
0 .I
0 0 0 -.I
-3
a
ci
V
.- -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise posltion parameter, x-By, In.
( b ) z = 1.67 inches; a = 0'.
'Figure 10. - Continued.
Y, 3.0
4.2
54
6.6
7.8
9.0
10.2 11.4
12.6
15.0
I60
4
3
.2
cm .I
" a 0 0
+ c 0 0
0 0
8 0 0 . 2 P
0 .I
0 0 0 -.I
-. 2 - 20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chdwise positlon pornmeter, x-by, in.
( c ) z = 2.09 inches; a,.- 0'.
Figure 10. - Continued.
Y,i" a 3.0
U 4.2
54 b 6.6
0 7.8
0 9.0 v 10.2
A 11.4
0 12.6
15.0
0 18.0
!-
I 1
J w a o o
g 0 0 . 2 g
0 0 .I
0 0 0
-.I
-. 2
I 1
""
B I I
.20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwisc positlon pammeter, x-By, in.
(a) z = 2.09 inches; u = 4'.
Figure 10. - Concluded.
y, in. LI 3.0
4.2
v 5.4
b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
0 12.6
15.0
0 18,O
er,
7J e
V
b
0
0
V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
y, in. 3.0 4.2 5.4 66 7.8 9.0
10.2 11.4 12.6 15.0 18.0
Chordwise positlon parameter, x-&, in.
(a> z = 1.15 inches; a = 0'.
F i w e 11. - Drag of wing-fuselage cornbi-nation i n presence of large store. (Drag corrected for Tuselege base pressure. ) M = 1.61.
0 0 0 0 0 0 0 0 0 0 0
Chordwtse position parameter, x-By, in.
( c > z = 2.09 inches; a = Oo.
Figure 11.- Continued.
Y, In. 3.0 4.2 5.4 6.6 78 9.0
10.2 11.4 12.6 15.0 18.0
NACA
.040
.038 -036 .034 .032 .030 .02 8 .026 .024 .02 2 -0 20 .O 18 .016 .014 .012 .ot 0 .008 .006 .004 -00 2 0
0 -.004 h' 0 0 0 0 o .OIO v 0 .008 A 0 .006 0 0 .004
0 .002 0 0 0
-.002 "004 -zU -16 -12 -8 -4 0 4 8 I2 16 20 24 28
Chordwise position parameter, x-By, in.
Figure 11.- Concluded.
y, in. 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
L
+ - a W
P
b
0
13
V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.28
.24
.20
.I 6
.I 2
.O 8
.04
0
-.O 4
.08
.O 4
0
-.O 4 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise poslilon parameter, x-By , in.
A
0
0
0
y, in. 3.0 4.2
5.4 6.6
7.8 9.0
10.2
I I .4
12.6
15.0
18.0
(b) z = 1.67 inches; a = Oo.
Fi,c;u_re 12. - Continued.
a 0
V
b
U
n V
A
0 a 0
.24
20
.I 6
. I 2
.08
.04
0 0 0 0 "04 0 0 0 0 08 0 0 .04 0 0 0
-04, - L ?O -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter, x -By, in.
( c ) z = 2.09 inches; a = oO.
Figure 12.- Continued.
Kin. a 3.0
D 4.2
v 5.4
b 6.6
IJ 7.8 9.0
v 10.2
A 11.4
0 12.6
0 15.0
0 18.0
7Q
c
a U
V
b
0
n V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
28
.24
.20
16
. I 2
.08
.04
0
-.04
.08
.04
0
a
Q
V
b
U
n
V
A
0
0
0
y, in. 3.0
4.2
5.4 6.6
7.8
9.0
10.2
I I S 12.6
15.0
18.0
Chordwise position parameter, x-By, in.
(d ) z = 2.09 inches; a = 4’.
FiSTe 12. - Corxlrrded.
.20
. I 6
.08
.O 4
a 0 o a 0 P 0 -04 L O 0 0 0 0 v 0 .08 A 0 0 0 .04 0 0 0 0 0
y,in.
LI 3.0 CI 4.2 v 5.4 B 6.6 0 7.8 Q 9.0' v 10.2 A 11.4 0 12.6
15.0 0 18.0
-.O 4 -20 -16 -12 -8 -4 0 4 8 12 I6 20 24 28
Chordwise position parameter, x -By, in.
Figure 13. - ?itching rnorrient of wing-f-sela e combination in presence of large store. (center of moments is e$& of wing. ) = 1.01.
LC B
d
U
P b
0
n V
A
0
0
0 0 0 0 0 '0 0 0 0 0 0
20
. I 6
.I 2
08
.04
0
-.O 4
-0 8
.O 4
0
-04- -C
Chordwise position parameter, x-py, in.
d
' U
V
b
0
0
v
A
0 0
0
y, in. 3.0 42 5.4 66 7.8 9.0 10.2 11.4 12.6 15.0 18.0
(b) z = 1.67 inches; a = 0 0 . Figure 13.- Continued.
4..
6 E
5 P .- c CI
I5
U
V
b
0
a P
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.20
. I 6
.I 2
08
.O 4
0
-04
.08
.O 4
0
-.O 4
Chordwise positlon 'parameter, x -By, in.
K in. a 3.0 u 42 v 5.4 b 6.6 0 7.8 c) 9.0 v 102 A 1 1 4 0 12.6 0 15.0 0 18.0
6
(c) z = 2.09 inches; a, = 0'.
Figure 13.- Continued.
Ll
U
V b
U
0
V
A
0
0
.20
.I 6
.I 2
.08
.O 4
0 0 0 0 -.04 0 0 0 0 08 0 0 .04 0 0 0
-.O 4
Chordwlse position porameter+x-gy, in.
y, i n. 3.0 4.2 54 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
(a) z = 2.09 ixhes ; a = 4O.
Figme 13.- Concluded.
0 0 0 0 0 0 0 0 0 0 0
.040
.036
,032
.028
.024
.020
.O I 6
.012
.008
.004
0
-.004
.008
.004
0
-.004
Chordwise position parameter, x - B y , in.
d
P
F
b
0
0
V
A
0
0
Y, in 3.0 4.2 5.4 6.6 7.8 90 10.2 II 4 12 6 15.0 18.0
(a) z = 1.15 Fnches; a = Oo.
Fig-ne -4.- Total drag cf the corrplete corfiguration (wing-fuselage plus l a rge s to re ). (Drags corrected f o r bese pressures. ) M = 1.61.
- 3
a U
V
h
0
Q
V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
ChordJvise position parameter, x+y, in.
a U
P
b
O
n V
A
0 0
0
y, in.
3.0 4.2 5.4 6.6 7.8 90
10.2 11.4 12.6 15.0 18.0
(b z = 1.67 inches; a = 00.
Figure 14. - Continued.
d
9
F
b
0
n V
A
0 a 0
0 0 0 0 0 0 0 0 0 0 0
.040
,036
.032
.02a
.02 4
.020
.O I 6
.o I 2
.008
.004
0
-004
.008
.O 04
0
-.004 -2 0 -16 -12 :f8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter, x -By, in.
(2) z = 2.09 inches; a I Oo.
Figure 14.- Continued.
Y, In. 3.0 42 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
8Q
..
,
0 d
cn V e - 0 E
a U
I
b
0
n V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.040
.036
.032
.02 8
.024
.020
.O I 6
.012
008
.oo 4
0
-.004
.008
,004
0
-.004 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter, x -by, in.
(a) z = 2.09 inches; G = 4'.
Figure 14.- Concluded.
a U
1
b
0
0
V
A
0 0
0
y, in. 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
.30
.28 -26 .24 .2 2 20 18 16
c -1 u .I 4 c- al
Y- .c
S .I 2 o .I 0 al .O 8 8
06 - Y- .04
c2 g a o o r: Tl 0 -.02 0 + 0 -.04 e $ h 0 g o o
.-
c
- 0 +
c
u 0 0 V 0 .08 A 0 .OE 0 0 .04 0 0 02 0 0 0
"0 2 -04
-2
Figce 13.
EO -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter, x -By in.
(a) z = 1.15 inches; a = Oo.
- Total lift cf the c o q l e t e (wing-fuselage plus large corzigzat ion. M = 1.61.
yyin. a 3.0 Q 4.2 v 5.4 b 6.6 0 7.8 0 9.0 v 10.2 A 11.4 0 12.6
15.0 0 18.0
s to re )
c
y,in. a 3.0 u 4.2 P 5.4 b 6.6 0 78 n 9.0 P 102 A 11.4 0 12.6
150 o 18.0
c
d
U
I
b
0
0
V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
08
.04
0
-.04
.08
.04
0
-no
y, In a 3.0 CI 4.2
5.4 b 6.6 CI 7.8 0 9.0 v 10,2 A 11.4 0 12.6 n 15.0 0 18.0
- . -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter, x-By , in.
Figure 1-5. - Continued.
. 0 f I
- U s t != 0 c
S m ii= c 0 V
.- e
a U
V
b
0
n V
A
0 R
0
0 0 0 0 0 0 0 0 0 0 0
.2 8
.2 4
.20
. I 6
.I 2
.08
.04
0
-.04
.08
.O 4
0
-.O 4 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position paramefer , x -By, in.
a U
V
b
0
a V
A
0 0
0
Y,in 3.0 4.2 5.4 6.6 Z8 9.0 10.2 11.4 12.6 15.0 18.0
(dl z = 2.09 inches; a = 4'.
Siglire 15. - Cozcluded.
0 0"
rn '0 e
.40
.35
.30 25
.20
15
.I 0
.O 5
0 0 0
q 0 -.05
P 0 -.IO L O
0 0
0 0 v 0 .20
A 0 .I5
0 0 .IO
0 .05
0 0 0
-.O 5 - ~n
.I " -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position pammeter, x-by, in.
(a) z = 1.15 inches; a = 0'.
Figure 1.6.- Drag of small store i n presence of wing-fuselage combination. (Drag corrected fo r base pressure. ) M = 1.61.
Y LI 3.0
q 4.2
I7 5.4
b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
0 12.6
[3 15.0
0 18.0
e e e e
20 :
e e
f
I b
rn '0 e
. ..
I d
.40 .3 5
.30 .25
.20 .I 5
. I 0
05
a 0 0
KI 0 -.05
v 0 -.IO L O
0 0 0 0
v 0 .20
A 0 .I5
0 0 .IO 0 0 .05
0 0 0
-.O 5 - .I 0
-20 -16 -12 -8 -4 0 4 . B 12 16 20 24 28 32 Chordwise position parameter, x -pY , in.
(b) z = 1.6'7 inches; a = 0 . Figure 16. - Continued.
0
a
U
V
b
U
n
V
A
0
0
Y 3.0
4.2
5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
u1 L" UI X 0 1 2
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chardwlse posltlon parameter, x-By, in.
( c ) z = 2.03 inches; CL = 0'.
Figure 16. - Continued.
Y a 3.0
p 4.2
v 5.4
b 6.6
u 7.8
0 9.0
v 10.2
A 11.4 0 12.6
0 15.0
0 18.0
I I
t3
-0 e
.40
-35
.30
.25
.20
.I 5
.I 0 I .O 5
a 0 0 D 0 -.05
0 - . I O
L O
0 0
0 0
v 0 .20 * 0 .I5 0 0 .IO
0 .05
0 0 0 -,0 5
-.I 0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise position parameter, x - B y , In.
(d) z = 2.09 i.nches; a = 4'.
Figure 1.6. - Concluded.
I
y, in. a 3.0
D 4.2
v 5.4
b 6.6
0 7.8
IY 9.0
v 10.2
A 11.4
0 12.6
15,O
0 18,O
b r
e e a e a e a m a
e
e . e e e e a a m
"" .- -
I
.40
.35
.30
.25
.20 . I 5
0 .I 0
.05
0 0 0 9 0 -.05
v 0 -.IO a 0 0 0
0 0 v 0 .20
A 0 -15 0 0 .IO
0 0 .05 0 0 0
705 ~ ~n -.I v -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position pumrneter, x-by, in.
Figure 17.- Base drag of small store in presence of' wing-fuselagc comhi- nation. M = 1.61.
y, in. CI 3.0
U 4.2
v 5.4
6.6
7.8
0 9.0
v 10.2
4 11.4
0 12.6
0 15.0
0 18.0
e
.40
.3 5
.30
.25
.20
.I 5
.I 0
.05 m" n 0
s: 0 0
a 0
fj v 0 .20
A 0 . I5
0 0 .IO
0 .05
0 0 0
-,05
0 9
6
-.I 0 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise position parameter, x-By, in.
(h ) e = 1.67 inches; a = 0'.
Figure 17. - Continued.
y, in.
3.0
4.2
5.4
6.6
7.8
9.0
10.2
I I .4
12.6
15.0
18.0 b e b b b b b b b
b b b b b
"_
" . ..
I
.40
.3 5
.30
.25
-20
. I 5
.IO m" on -05 .. E 0 0 0 er
5 CI O -.05
0
" 0 -.IO
x 0 0 x n o e R v 0 .20
A 0 . I5
0 0 .IO
0 0 0 5
0 0 0 -05
-.I 0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise position parameter I x -by I in.
I I
(c) z = 2.09 inches; a, = 0'.
Figure 17. - Continued.
I I
d
D
V
b
U
n
V
A
0
0
0
y,in. 3.0
4.2 5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
1 I
z F
I I I 1
n a? V
c c s b F 0
0
al b 3i
a o
0 0
P O
a 0
0 0 n o v o
A 0
0 0
n o 0 0
.40
.35
.30 25
.20
.I 5
.I 0
.05
0
-.05
-.I 0
.20
.I 5
.IO
.O 5 0
-.05
-.I 0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise position parameter, x -By in
(a) z = 2.09 inches; u = 11'.
Figure 1'1. - Concluded.
a
0
V
h
0
n
V
A
0
0
0
yJn.
3.0
4.2
5.4
6.6
7.8
9.0
10,2
I I .4
12.6
15.0
18.0
b b b b b b
b b b b
b b b b b
b b
"" . ... ""
I
1
n o
0 0 F o
a 0
0 0
n o v o
0 0
n o
0 0
y, in.
3.0
u 4.2
I 5.4 b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
0 12.6
0 15.0
0 18.0
-20 -16 -12 -8 -4 0 4 a I2 16 20 24 28 32 Chordwise position parameter, x-By, in.
Figure 1.8.- L i f t of sr0a:ll store i n presence of wing-fuselage combi.nation. M = 1.61.
I I
I
I L I I
!E c
.4
.3
.2
. I
0
-.I
-. 2
.4
.3
.2
.I
0
-.I
-. 2
I 1
Y, in. a 3.0
0 4.2
v 5.4
b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
6 12.6
II 15.0
0 18.0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position parameter, x -fly, in.
(b) z = 1.67 inches; u = Oo.
Figure 18. - Continued.
...a a a
...a ..... a
* . ....a a .
....a a . a .
a . ...a. a . *.... . a m . a * a .
.4
.3
.2
. I
a 0 0
Kl 0 -.I
v 0 -.2
a 0
0 0
n o
v 0 .4
A 0 .3
0 0 .2
0 .I 0 0 0
-. I - 7
a
Q
P
b
0
n
V
A
0
[3
0
I
”
.- -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position parameter, x-By , in.
( c ) z = 2.09 inches; a = 0’.
Pityre 18. - Continued.
I I
y, in. 3.0
4.2
5.4
6.6
7.8
9.0
10.2
I I .4 12.6
15.0
I8 0
I 1
e e
e m m m m
emme e e
emme
.. -
I I
.4
.3
.2
.I
0 0 0
_I* u 0 -.I - P 0 -.2 0
t c
.- 2 a 0
8 0 0
+ 0 0
Y- Y-
0
- f! v 0 .4
A O . 3
0 0 .2 0 .I
0 0 0 -.I
-. 2
y, in. 30
4.2
5.4
6.6
78
9.0
10.2
11.4
12.6
15.0
18.0
4 : a .
:'
e... a . . . a e . .
a .
e . ....a a .
a*... -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwrse position parameter, x -fly, in.
(dl z = 2.09 inches; a = 11 0 . Pigwe 1.8. - Concluded.
0 Z o o o
v 0 .4
A 0 .3
0 0 .2 0 0 .I
0 0 0
-.I
-.2
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwlse position parameter, x -pV , In.
(a) z = 1.15 inches; a = 0'.
Pigure 19. - Pitching moment ot' smll store i n presence of wing-fllselage combination. (Center of moments is s tore nose. ) M = 1.61..
y, in.
3.0
4.2
5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
H
tn UI X 0 P
.4
.3
.2
. I
0 C a o o
+- u 0 :I
‘E v 0 -.2 s IC I&- Q 8 a 0
+ 0 0
g 0 0 E F v o . 4 .- g A O . 3 c
6 4 0 . 2 ii 0 . I
0 0 0
-.I
-* 2
a
CJ
V
ti
D
n
V
A
0
0
-20 -16 -12 -8 -4 0 4 0 12 16 20 24 28 32 Chordwise position parameter, x -fly , in.
(b ) z = 1.67 inches; a = Oo.
Figure 19. - Continued.
Y, in. 3.0
4.2
5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
I
4
.3
.2
I
0 i o 0 o
+- cl 0 - I
'3 v 0 -2 5 Y- IC
$j L O
+ 0 0
O 0 0 E E
2 s! 0 0 . 2
u, 0 0 . I
0 0 0 - I
d
U
V
b
0
n
V
A
0
I3
0
-. 2 -20 -16 -12 -8 -4 0 4 a 12 16 20 24 28 32
Chordwise positlon pamrneter, x-By, in.
( c ) z = 2.09 jnches; a = Oo.
Figure 19. - Continued.
t i
-_ " . "
I
y, in. 3.0
4.2
5.4
6.6
7.8
9.0
10.2
I I .4
12.6
15.0
18.0
O C e *
oommm
E P
5.
1
:a
1 a
.4
.3
.2
. I
0 0 0
u 0 -.I
v 0 -.2
a 0
0 0
0 0 , v 0 .4 A 0 .3
0 0 .2
El 0 .I
0 0 0 -.I
72
-20 -16 -12 -8 -4 0 4 8 I2 16 20 24 28 32 Chordwise position parameter, x -f ly, in.
y,in. n 3.0
CI 4.2
v 5.4
b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
Q 12.6
15.0
0 18.0
(a) z = 2.09 inches; a = 4 . Figwe 19. - Concluded.
0
u1 L" u1 II: 0 P
e . ...a. a .
.a**. m o o :2: .ai.* . a a .
a..
0 0 . I
0 0 0
-.I
-.2
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwlse position parameter, x -/3y, in.
Y, in A 3.0
9 4.2
5.4
h 6.6
0 7.8
0 9.0
v 10.2
A 11.4
0 12.6
15.0
0 18.0
(a) z = 1.13 inches; a = 0 . 0
Figure 20.- Side force of small. s t o r e i n presence of wing-fuselage com- bination. M = 1.61.
7 .
I I
t O
,, u 0 -.I
0 0 .I
0 0 0
-. I -.2 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position parorneter, x-by, In.
(b) z = 1.67 inches; a = 0'.
Figure 20. - Continued.
1
Y, In a 3.0
P 4.2
v 5.4
b 6.6
D 7.8
9.0
v 10.2
A 11.4
0 12.6
0 15.0
0 18.0
"_ . "_ .
-4
.3
.2
.I
0 > m d O 0
.$ P 0 -.2 t c ,. u 0 - . I
ii= .I- L," o 0 0 0 .I- 0 0 -P v o . 4
6 A 0 . 3
0
VI
3i 0 0 . 2
0 0 .I
0 0 0
".I
-.2 ~
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position parameter, x-fly, in.
y~ in. a 3.0
4.2
v 5.4
b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
0 12.6
0 15.0
Q 18.0
( c ) z = 2.09 inches; CY, = 0'.
Figure 20. - Continued.
"
8 I 1
I I
0 0 0
-.I
-.2
y, In. a 3.0
Q 4.2 r7 5.4
b 6.6
0 7.8
a 9.0
10.2
4 11.4
0 12.6
0 15.0
0 18.0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 0 .
Chordwise position parameter, x -By , in.
(d ) z = 2.09 inches; a = 4'.
Figure 20. - Concluded.
" "
.. a 0
0 0
r o L O
0 0
0 0
v o A 0
0 0
0 0
0 0
.4
.3
.2
.I
0
-.I
-.2
4
.3
.2
.I
0
-.I
-. 2
Chordwise position pomrneter, x-By, in.
y, in. n 3.0
0 4.2
v 5.4
b 6.6
0 7.8
n 9.0
v 10.2
A 11.4 0 12.6
0 15.0
Q 18.0
(a) z = 1.1.5 inches; a = 0'.
Figure 21.- Yawing moment of small store i n presence of wing-fuselage conibination. (Center of moments is store nose. ) M = 1.61.
0 .I
0 0 0
-.I
-9
y, in. A 3.0
Q 4.2
P 5.4
b 6.6
0 7.8
0 9.0
v 10.2
A 11.4
0 12.6
0 15.0
0 18.0
a a a b e a a *
amaa
.- -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 * a
**ma* e a mama.
a *
Chordwise position parameter, x-By, in.
(b) z = 1.67 inches; a = 0'. b e
e
a m a a a a e e a
a a e Figure 21. - Continued. eamea
: b$ saeam a a
a*.
* b
c 5
.4
.3
.2
.I
0 ci 0 -.I
v 0 -2
L O
0 0
n o
v o . 4
A 0 .3
0 0 .2 n o .I
0 0 0 - I
-. 2
a
Q
V
b
0
0
V
A
0
0
0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32
Chordwise position parameter, x -By , in.
( c ) z = 2.09 inches; a = Oo.
Figure 21. - Continued.
I f
y, in. 30
4.2
5.4
6.6
7.8
9.0
10.2
11.4
12.6
15.0
18.0
.4
.3
.2
.I
J c l o 0
E, u 0 -.I v 0-2 a 0
.-
a
0 0 *I
0 0 0
-,I
-. 2
Y, in a 3.0
U 4.2 v 5.4
h 6.6
0 7.8 0 9.0
v 10.2
A 11.4
0 12.6
0 15.0
0 18.0
b o bC0.b b e mbm.0
O b b b
0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 32 Chordwise position parameter, x - B y , in.
Figure 21.- Concluded.
. "
0 0 0 0 0 0 0 0 0 0 0
.040
.036
.032
.02 8
.024
.o2o
.O I 6
.012
-00 8
.004
0
-.004
.008
.004
0
-.004 - Chordwise position parameter, x -By , in.
(e) z = 1.15 inches; a = 0”.
K in d 3.0 9 4.2
5.4 b 6.6 Q 7.8 n 9.0 v 10 2 A 11.4 0 12.6 Q 15.0 0 18.0
Figure 22.- Drag of wing-xhselage combine5ion i n p re sexe of’ small store . (Drags corrected for faselage base pressures. ) M = 1.61.
LC L
op
0 0 0 0 0 0 0 0 0 0 0
.040
.036
.032
.028
-024
-0 20
.O I 6
-01 2
.008
-004
0
-004
.008
.004
0
-.004 - Chordwise position parameter, x-By , in.
a U
V
b
0
n V
A
0 0
0
y, in. 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
(b) z = 1.67 inches; CL = Oo.
Figure 22.- Continued.
’c B P
V
m V e
.040
.OS6
.032
.02 8
.024
.020
.016
.012
.008
.004
0
-.004
.ooa
.004
0
-.004 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter, x-By, in.
y, in. d 3.0 u 42 v 5.4 b 6.6 0 7.8 n 9.0 v 10.2 A 11.4 0 12.6 a 15.0 0 18.0
c
2Q
W
U e
0 0 0 0 0 0' 0 0 0 0 0
.040
.OS6
.03 2
.028
.024
-020
.O I 6
.012
.OO 8
.004
0
-.004
.008
.004
0
-.004
Figare 22. - Conclude&.
a U
V
b
0
0
V
A
0 D
0
Y, in 3.0 4.2 5.4 6.6 7.8 9.0
10.2 11.4 12.6 15.0 18.0
-20 -16 -12 -8 -4 0 4 8 I2 16 20 24 28 Chordwise position parameter, x-By, in.
(a> z = 2.09 inches; u = 4'.
.2 8
.24
20
.I 6
.I 2
.C 8
.04
0
-.04
.08
04
0
-04 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Y, In. a 3.0 u 42 v 5.4
6.6 7.8
a 9.0 v 10.2 A 11.4 0 12.6 0 15.0 0 180
Chordwise posltion parameter, x-py, in.
(a) z = 1.15 inches; a = 03.
Figure 23.- Lift cf wing-fuselage combinetiolz In presence of small store. !4 = 1.51.
0 0 0 0 0 0. 0 0 0 0 0
.2 8
.24
20
.t 6
.I2
.08
.04
0
-.O 4
08
.04
0
-.O 4
Chordwise position parameter, x-By, in.
(b) z = 1.67 inches; a = oO.
Figme 23. - ContimJed.
y, in. d 3.0 U 4.2 v 5.4 b 6.6 0 7.8 0 9.0
10.2 A 11.4 0 12.6
15.0 0 18.0
LT L 0 J
..
d
U
V
b
0
0
V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.28
24
20
. I 6
.I 2
.08
.O 4
0
- 04
.oa
.04
0
-.O 4
a U
V
b
0
a V
A
0 0
0
y, in. 3.0 4.2 5.4 6.6 7.8 90 10.2 11.4 12.6 15.0 18.0
.20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter x -By in.
(c) z = 2-09 inches; a = Oo.
Figlrre 23. - Continued.
NACA RH ~ 5 5 ~ 0 1
.c b
u -1 ..
0 0 0 0 0 0 0 0 0 0 0
2 8
.24
.20
.I 6
.I 2
.O 8
.04
0
-.04
.08
.O 4
0
-.O 4 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position poramefer, x-By, in.
a 0
F
b
0
0
P
A
0 0
0
y, in. 3.0 4.2 5.4 6.6 7 8 9.0 10.2 11.4 12.6 15.0 18.0
(a> z = 2.09 inches; OL = 4 0
F i g x e 23. - Conclu6ed.
a U
P
b
D D
V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.20 . I 8 . I 6 . I 4 .I 2 .I 0 .08 06 .04 02 0
"02 - 04
08 06 04 .o 2 0
-.02
Y, In. 3.0 4.2 5.4 6.6 7.8 9.0 (0.2 11.4 12.6 150 18.0
r b
0 E
20
.I 6
.I 2
.O 8
.O 4
0 0 0 P O V 0 -.04 h O 0 0 n o v 0 08 A 0
0 0 .04 0 0 0 0 0
-.O 4
Chordwise position parameter, x-By, in.
Y¶ d
U
P
b
0
0
P
A
0
0
in. 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 L 2.6 15.0 18.0
(3) z = 1.67 inches; a = 00.
Figure 24. - ContiDued.
.
.I- L 0 E
a P
V
b
0
0
V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.20
.I 6
.I 2
08
.04
0
-.04
.08
04
0
-.04 -2
y, in.
3.0 4.2 5.4 66 7.8 9.0 10.2 11.4 12.6 15.0 18.0
!O -16 -12 -8 -4 0 4 8 12 16 20 24 28 Chordwise position parameter, x -By , in.
4
Y- L 0 E ..
.20
.I 6
.I 2
.O 8
.O 4
0
-.O 4
.O 8
.O 4
0
-.04
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parcmeter, x-By, in.
(dl z = 2.09 inches; a, = ko.
Figme 24. - Coxlizded.
d
U
V
b
U
CL
V
A
0 0
0
y. in. 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
a B
V
b
0
n 0
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.040
.036
.032
.02 8
.024
020
.O I6
.012
.008
.004
0
-.004
.008
.004
0
-.004 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise posltion parameter, x-By, in.
(a> z = 1.15 inches; c. = G . 0
y, in.
3.0 4.2 5.4 6.6 7.8 9.0
10.2 11.4 12.6 150 18.0
Figdre 25.- T o t a l drag of the complete configuration (wing-Pmelage plus smli store }. (Drags corrected f o r base pressures. ) Y = 1.51. 0
m '0 e
a 9
v b
0
n V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.040
.036
.032
.02 8
.024
.o 20
.O I 6
.012
.OO 8
.004
0
-004
.O 08
.O 04
0
-.004 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter, x-By I in.
(b) z = 1.67 inches; a = Oo.
Fig-are 25.- Continued.
a U
V
b
0
n V
A
0 U
0
9, In.
3.0 4.2 5.4 6.6 7.8 90 10.2 11.4 12.6 15.0 I 8.0
f
d
U
V
h
U
n V
A
0 U
0
0 0 0 0 0 0 0 0 0 0 0
.040
.036
.032
.02 8
.024
.020
.016
.012
.008
.004
0
- 004
.008
.004
0
-.004 -
Y, In. 3.0 4.2 5.4 6.6 7. a 9.0 10.2 11.4 12.6 15.0 18.0
20 -16 -12 -8 -4 0 4 8 12 I6 20 24 28 Chordwise position parameter, x -By, in.
( c > z = 2-09 inches; a = cO.
Figme 25. - Contimed.
NACA RN ~ 5 5 ~ 0 1
m U e
a U
P
h 0
a I
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.040
.036
.032
.028
.024
.020
-016
.012
.008
-00 4
0
"004
.008
.O 04
0
~004, -1
4
L
Ll
U
F
b
0
n V
A
0 0
0
y, in. 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 I 5.0 18.0
2 0 -16 -12 -8 -4 0 4 8 12 16 20 24 28 Chordwise position parameter, x-fiy, in.
(dl z = 2.09 inches; OL = 4 . Figure 25. - Concluded.
0
c
Y c 0 i;: .c
8 0
d 0
P
b
V
0
V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.20
.24
.20
. I 6
.I 2
.08
.O 4
0
-.04
.08
.O 4
0
-.04
d
P
V
b
0
0
V
A
0
0
-20 -16 -12 -8 -4 0 4 8 12 16 20 24 28 Chordwise position parameter, x-By, in.
Y 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
0 i
a U
I
b
0
n V
A
0 0
0
0 0 0 0 0 0 0 0 0 0 0
.28
.24
.20
.I 6
.I 2
.08
.04
0
-.04
.08
.04
0
-.04 -1
x in 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 Lao
!O -16 -12 -8 -4 0 4 8 12 16 20 24 28 Chordwise position parameter, x-By , in.
t
0 0 0 0 0 0 0 0 0 0 0
.28
.24
.20
.I 6
. I 2
.08
.04
0
“04
.08
.O 4
0
4 4 _ . -20 -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise positio? porarneter, x-By, in.
(c) z = 2.Cg inches; a = 0’.
Figure 25. - Continued.
y, in.
3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
0 J-
a U
v b
W
n V
A
0 El
0
0 0 0 0 0 0 0 0 0 0 0
.28
.24
.20
. I 6
.I 2
.08
.O+
0
-.04
.08
.O 4
0
-.O 4- -c !O -16 -12 -8 -4 0 4 8 12 16 20 24 28
Chordwise position parameter, x-By, in.
(d) z = 2.09 inches; a, = bo.
F i g a e 26. - Concluded.
4
U
v b
U n
V
A
0
0
y, in. 3.0 4.2 5.4 6.6 7.8 9.0 10.2 11.4 12.6 15.0 18.0
C q In presence of o w~ng alone (ref.1) 0 fighter h & r n heavy bomber (ref.1)
Chctdwise position, x, in.
i 20 24 28""32 36
chordwise positim,x,in.
Figure 27.- Comparison of drag of large store i n presence of swept wing alone and heavy-bomber and fighter-bomber conf'j.gurations. z = I. 17 inches; a = 00. CD, of isolated store is 0.234.
r I
L I
"
A C DS
o Fighter bomber 0 Heavy bomber
. I -
0
y=3.0 in. -.I I
~ ~ 5 . 4 in,
"I-".."
-I-
~ ~ 1 0 . 2 in. 12 16 20 24 28 32 36
" -
Chordwise position, x, in. Chordwise position, x, in.
Figure 28. - ConLribution of f'usel-age (in presence of wing) t o inter.l"crcnce drag on large ogive-cylinder store. Cg, i n presence of wing-fuselage minus CD, i n presence of wing, from :rJ.gure.27.
i
chordwise posltlon , x , in. Chwdwise position, x, in.
Figure 29. - Comparison of E f t of. large store i n presence of swept, wing alone and heavy-bomber and fighter-bomber configuratlons. z = 1.15 inches; 0: = 00.
..... . ..... .... . . . ....
r I 1
Cys in presence of 0 wmg alone (rd.2) o fighler -bomber 0 heavy bomber(tef.2)
6
I w
3"
Chordwise positlpn , x , In.
Figure 30.- Comparison of alone and heavy-bomber a = 0'.
Chordwise position , x , In.
side force of large store in presence of swept-wing and fighter-bomber configurations. z = 1.15 inches;
Teal Wing-fuselage o Fichter borrber o Flghter bomber I P ! v y bomber(ref.1) Heavy bomber (ref.1)
0 4 8 12 16 20 24 28 32 36
h r d w i s e posltlon , x , in. Chordw~se posltm,x,in.
Figure 31.- Comarison of wing-Paelage drag and total configuration (wing-faselsge plus store ) drag f o r heavy-bomber and fighter-bomber configurations with large store. a = Do; z = 1.15 inches.
b 1
.008
.004
0 ”
-.004
y=3.0 in. -008
o Fighter bomber 0 Heavy Ff
y=5.4 in.
Chordwise positm, x, in. Chordwise position, x, in
Figure 32. - 1nter:t‘ercnce drag of wing-fuselage combinations produced by large ogive-cylinder store. CnWf (from f ig . 31) minus C D ~ Of
isolated wing-fuselage.
s . emmoo m m
7btal Wmg-fuselage 0 Fighter bomber o Fqhter bomber
b Heavy bomber(refs. I and 2) Heavy bomber (refs,
Chordwise position. x .in.
I and 2)
Chordwise position, x ,in.
Figure 33. - Conparison or wing-f'usdage l i f t and total configurat ion (wing- fuselage plus s t o r e ) l i f t for hcavy-bomber and fighter-bomber configura- t ions with large s to re . u = Oo; z = 1.15 inches.
. _”
c L
” .
I a
large store 4
small store + y3.0in. y = 5.4in. y=ZBin.
1 La”’
s g t!$
I C
ti ’*I8 21 24 27 30 33 18 21 24 27 30 33
\1
y40.2in.
18 21 24 27 30 33 Chmhviso poit ian, x, in.
Figure 34. - Comparison of forces on large and smal.1 stores in presence of fighter-bomber configuration. a = 0’; z = 1.15 inches.
"
In presence of: l6qe store -Q-
small store -0-
v-5.4 In. y-7.8 In.
18 21 24 27 30 93
Y.10.2 Ill.
c h a r l w i s e position, x, in.
Figure 33.- Comparison of forces on fighter-bomber configuration in presence of large and small stores. a = 0'; z = 1.15 inches.
e m m m m m m a m
t
