unclassified ad number - dtic.mil · na'j&d report 4053 rii wind -tunnel investigation 0f...
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UNCLASSIFIED
AD NUMBER
AD 491 184
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FROM CONFIDENTIAL
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USNOL ltr; August 29, 1974.
THIS PAGE IS UNCLASSIFIED
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AD NUMBER
AD-491 184
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Approved for public release;
distribution is unlimited.
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DoDD 5230.24, para f.3.b.; August 29, 1974.
THIS PAGE IS UNCLASSIFIED
NA'j&D REPORT 4053
rii WIND -TUNNEL INVESTIGATION 0F VARIOUS CONFIGURATIONAL.
d', • MOOIFICATIONS OF THE LOW--DRAG BOMB (U)
I FILE COPY
ASTIAAtLIN@TGON HALL STATION
A1LI3NGOWO 12. VIDOINIA
Attms TIM 55
22 JULY I9M
4 AnANCI
Uo S. NAVAL O DIAUCE RATO'YWHIMT OAK, 7ARTLAND
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NAVORD Report 40:3
Aeroballistic Research Report ey5
WIND-TUNNEL INVESTIGATION OF VARIOUS CONFiGURATIONALMODIPICtTIONS O THE L.J'W-DRAG BOMB
Prepared by:
Prod J. DeMeritteHarry Gauzza -,
t the resu,'.-'" axi Inveesigationin the NOL 4C x 41' cm Aeroballistlca b nn4: No. 1 to study thestatic stability and drag of the low-drag ... rmb at subso;,1c and
".supersonic speeds. The foilowirg uests were made:
(a) Xtudy of configurstJotal charges designed to &educethe yaw of the bomb,
*(b) ýrag 4Y the 25O-rvund bomb with &;upporting lugs (W.=81bomb),3"
(c) Atability of an 8-fin bomb with reduced fin span toimprove the ground clearance problem.
U. S. NAVA. ORDNANCE LABORATORY
WHITE OAK, MAM'YLAND
i
CC.'VT DENrIAL
NAVCRD ;Aport 4053 22 Ju.L, 9i58
Th.'s !-estlgation was perforw..ad at the request ot the Bureauof Ordnance (reference (a)) under Task Number A3d-453-1-5u.The report covers recent wind-tunnel tests In the NOL 40 x 40 cmAeroballtatics Tunnel No. 1. Additional work has been done inthe NCA ftring rangeo, th.e Naticnal Bureau of Standards wind-tunnel. and the Cornell transon!C wind-tunnel under the direct•onof the NwOL staff.
Prevlv,.s NOL rop•crts on the aerodynamics of the low-drag seriescan te found .'n t-.fere:,.res (b) thiugh (f).
MELL A. PETERSONCOatjin, USNCcnmander
R. KENNETH LOBWBy direction
1I
C~fI DENTIAL
C' 11FI> 9.NTIAI.NAV,' ,hero't LCV3
,'- I YNTS
Page
Introm uct ion . . . . . . . . .. . . . . . . . . ..
List of ý:'mbols . . . . . . . . . .. . . . . . . . . . .
,~~s• on2
Induced . I rcgra- and Large Fin Program ..... 4
Reduced Fin Sar. Frogram . . . . . . . . . . . . . 5
Fffect of Lugs Prcgrar ............. . 5
• •;Zeas, -&.'ances,and Data Reduction . . . . . . 5ronclusicns . . . . . . . . .. .. ... b
References. . ..... ....... . . . . . . . . . . .7
ii'CCNI'I D• N T £I.
' :F1 -,FNT I AT..,V ,-P-ort 40ý:73
ILLU3TJiATICNS
Fl.urc. :. fhoto3 rarh of *.ht- Fasic 1.odel (No Fin -;.nt)ýigure P.hctorr-: ,. cf 'h* -asic "ode! ith 2 Le,;ree
rin ;-nt•!,T, ure " . hotogratt. cf *he !McJel -'.th l.f.L7 d Fin Span
(P•ear ics.itlon.)Figurp.. Sketch of h ',o4ei witt l.LL7 d and 1.607 d
(iRvar PoFition), Fin 4pan (Tall moved aftO .2P3 incahes)
Figure 5. Photograrh of the :,'odel with 2.05 d Fin SpanFigure t. 5ketch c: the Model uith 2.C5 d Fin SpanFi'ure 7. Fhotogrhph of the Moel with Large Nose VanesFigure 3. Phctograrh of the Model with Small Nose Vanes?.1 urc . k..kctch o' th', -ode4 Showing Nose Vanesýi.-ure 1.. Plhotograrh of the Model with 1.40 d Fin 3pan
and Ch of the 2.IC d Fin Span Model(Large Chcrd)
idure 11. `ket'-h :f the Large Fin Chord Model?i; ure 12. ýhotogrr:rh of the 6 Fin ModelFi,:ur.-- :j. ;,otop.ra;ri of the Fnd Flate ModelIIgure 1. ihotograrh of the Porous Lox Model
Figure 15. i'hotogra~h of the iclid ý oy Shroud ModelFigure It.t K'ctora:h of the 1/2 Tip Chor.. Solia Lox
shroud ModblFi4ue 17. sketch of trie :olid loy ,Jhroud, 1/2 Tip
.L.urI Lox O'hroud, iorous Boy hroud,Fnd ilates and L Fin Arran4erent
Figure 1. ,o roera:h of '.ie Fody Alone ModelFigure 1-9. Phctogra;h sf the ." Fin Modelfigure r" 0 . i!.otogra;.h of the 8 Fin Mouel with Full
Circular ShroudFiure .1. ihnrdgra.Eh of the 8 Fin Model with 1/2
Circ.lar jhroudFigure 2'. Sketch of the Fin Mojel Showing Full
and 1/? Clrc..lar 5,hrrnudsFigure 23. Fhotograh of the 150 Found Low-TlraC Lomb
Mo'uel with LugsFigure 24. Sketch of !he 250 Pound Low-Drag E,.mb with
LugsFigure 25. NOL >i'gn CcnventionFieure 2C. Yaw lI1story o' an Actual low-Drag LLmb Dropfig.'re 27. Yaw IHistory ContinuedFigure 28. Alotted Cocff'cient Data (CN, Ca Cy, C,.ttiru 55. and (4 vs e ) for Indueg Rolil Investigation
Figure 5f. ýIotted Coeff':,ient L.ita (CN and C I vs ; )and 57. for 3 Fin "onfiguration
P . Vrr I,.' T.6I'W? a
- K sr±r. ~~' aLb!1ily 'i.1th and~ u.:or-t~ng Lurs
* ' l otted Cce~ficlont :ata (CI; vs Mach NT.)
fcr t!%e 2.:pz-riscrn of ko~t *J th and
;I-ct..zr r~~on *he 1.0 J. Span 8 Fin
F~gr& . arogruirh: of ý;o!p~rsons of Zonftituratior.-
~ C. Tested .'n ýt.e :ndLced Rollinp '-c=ert
ro6:-.
~~~~~~~i --. . -1- • ,• , • • , ' , X - -k ,• • : • -•.......... . .u . . . .; -.1 . .......
CUNFIDEWTIALNAVOAD rieport 4053
WIND TUNNEL INVESTIOATION C? VARIuU-6 CONFIGURIATIONALMLD;FIC;.T:(NS CP THE LOW-D.FA, BOMB
I NTORDCTION
1. Thls rep-rt describes Invest.gat .ons carried vut ..Ld srles " 1,-w-dr.Lg b,.mbs of the U. S. Navy, In the wind-tunnels at the Naval Ordnance Laburatory. These bombs havea snape dvelopod by Douglas Aircraft. The four low-dragbombs of this series are the 250 pound bomb, Mk 81; the500 pound bomb, Mk 82; the 1000 pound bomb, Mk 83; and the2000 pound bomb, 1%c 814.
2. The tests made inve'ved:
a. An investigation of the configurational changesto reduce the Irtuced yawing 1onnt and rolling mnomnt ofthe bomb and imxpr-ve the dyna-is characte.-Istics.
b. Drag of the 250 oound bomb with suspension lugs.
c. Invest*_-ation of the stabllity of configurationw~th fin span ec.'al to the maximu body diameter.
3. The low-draC to-ib with two-degree fin cant is believedto be one of the "est bombs develope.4 . T'1e erratic flightmentioned in this re;*rt applies to .- "y , small percentageof the bombs drc.,pod.
Symbolis
A area ,&Xzlm-a) of the body (sq. In.)C.rC. center of gravity (42.5 per cent length from
the nose)CDo drag ecifficient at zero angle of attack (FD)
CD drag coefficient (?D) q-x
CN normal force coefficient (?AN)
Cy side force ooefficient
"0 rolling moment coefficient (•)
C t yawine mosent cooff1cient
qAd
CONPI DENTIAL
c3. Dox?::;TI AfNAVC.fD .ýeport 4(JO3
C; €pitci~ng rr mer.t coefficlent ((MG_) referred to
C.. qAd:d model d:&neter In4•• .•
SFD I.-I ( lb)F1,; z~occmal fo-.rce (lb)
P. s:d,-* force (0b)model lergth (see model sketches).ptc.nirg moment (IrVnlb)
M yawr n moment (In/ilb)"• r'L':g momen-t lir/ib)
q dynamc: pressu:n (psi) see Table 1A:e Reynolds number (based on model length)
(see Table I)ag.'.e uf atzack (deg.)
DiscuJ3In
4. -.".e 3tudy of configuratiornal changes of the low-dragbomb was a resul: of recurrinl indications of ;nsLdoIllty ofItLe bomb duarln drorps. I,. Early In the drop tests of the bombs It became obvious
.hat the bomb was yawir.ng badly. It appeared probable that thepitch freque:.cy and the roll frequency were becoming equalit ab3L' -,r.e 3ce,:e r ,ue.dn and that tne bomb wda- l;cklngint. resoo.ance. 'r.tially the ftn cant was zero degree with.1 vta::ufactur.:4g t, lerat.ce ,.f . degree. Calculati4;n.hwed that accideital f1r, cant within this tolerauce could
produce surftclent roll to cause resonance. Hence it w-ac"eP.'ded to car:t the fit, two degrees and thus produce a roll... ctch would Le t,,o large to result Ln resonance. This a ,nge.p•eared to -u.. the trouble with the low-drag bombs.
u. Several years later, however, d,-Igr dive-bombirg teets,large yaw eaza!•eared ,r. a few of the drops. Figures 26 and2.' present tne yaw hi3tory of a drop made at Chincoteagun,VIrgIn.'a. The figures show the oomuw be&InnIrg to damp thenundamý a::d later damp aa;hn. The Key to the problem appearsto Ue the ril-iocx-ln. The z'vll history shows that the rollra'.e of the tomb Increaie3 from zero to about one cycle perseco:.d, thiet "locks it." and the bomb continues to roll unltovaL1y.Whle rwlilti: at th"s rate the bomb is Ira A rzajorance condi.tion.The yaw .r.creaies ur.tl a lirge a',gle la reached. Wid-tunneltests at the Natlonai Bureau if 3•tandardz ahow that large roll-jr4; moments are Crejet,:t at large angles of attack. These large
CO'ý 7 DENTI ALNAVO•?D >-port LL05 3
moments cause increase in rcll rate, breaking out of resonance,.and 7.n approach to a steady state rolltrng frequency of 7 to ICcycles per second. While the .-oll rate is ±n.qira the yawI decreases raoldly ard the bomb falls sattsfactarily.
j 7. The condition for roll-lock-in Is
3
L 4 L 0
where;
L Rolllng moment due to fin cant
L Roll damping moment
:nduced rollir; moment
Winr-tunnel teats show that the induced rolling moment causesthe roll-lock-Ln. Possible cures for roll-lock-in appear toe r.. reduce the induced rolling moment
b. Inorease the fin span
i When roll-lock-.n occurs, tho low drag bomb experiences whatIs known as "Catastrophic Mrowth r- Yaw" at resornane due toyawing moment. To cure thi,:
a. reduce yawing momentSb. Increase fin spanco Increase damping moment
* d. reduce rutation arm
Wen it was first learned that the bomb was yawing badly,studies were made to determine if the trouble was rescnanceor Mag;zus instability. Calculation of the damping rate ofthi pre;se3ional and nutational arms showed that the presentbomb was prooably not experiencing Magnus instabllity)but If* the steady state rolling velocity was increased by more ftncant, Magnus instability could occur. Therefore, Increasingfin cant In hopes of preventing "leck-.In" did not appearfeasibli. Since the bomb experlenc22 difficulty at largeangles of attack, two methods appeared promising in preventingthe er-atic flight. One method was to increase the fin spanand chord to increase the pitch daaping and tne other methodwas to investigate fin shape$ which have low induced rollingmoments and low yawlig nmemnts.
3('7 NF I DEN 'I AL
im m • am immMINE
CCNFI DENT: AL
"nduced Koll Frog.ar. t.id Lvrge Fin Program
"T'. e Cc ', w¼ . f',u2at r,,z w.re :'epo:'ted ;r, thistest p.-C;am. "rx': &.. uratloi;s are :'eported In, referencese d, d f.
Ad tas;. I.cA-dr.'•g bc:b (no fin caz.t) Figures 1,242) ' der-ee r-n cant Figure 2l.0u, d span tall Flgure 4
(d) 2.Q, d span tall Figures 5,6ýe? large ncsc vares Figures 7,9kf) 3mai! nose vanes F1igures d,9(•) i.to d a span (tall moved rearward Figures 3,4
20.2.2_3 Inches)16,) end plate Figures 13,17•) box shroud Figures 15,11
dJ) 1/2 box shroud Figures lb,Ilk K) porous box 3hroud Figures 14,17kl) o fin model Fgu-res 12,17(m) long chord (1.4 d span and chord Figures 10,11
of 2.U5 d span model)(ri) body alone Figure 18
9. The conf.gurations were all tested at a Mach number of 0.91 oru.95 a ra.n roIl orlentatlon cf 22.5 deg:ees. In additionsome configurations were tested at fin orientations of zero.4- -. and 4ý dogrees and at Yach numbers of C.80 and 1.57 or1.58. FPIures ul, u2, and 03 show, In barograph form, a com-parlson of the various configurations. It should be pointedout tnat the nose vanes were placed in such a position, due tomodel zoniLLUctlon, that ; loss of stabtlity resulted. If theraries had been placed on the center of gravity or aft of thecenttr vf gravity this would nut have occurred. The porous boxshroud was selected as a configuration because it was believedtnat the solid box shroud would be unstable at transonic andsupersonic Mach numbers. However, tne solid box snroud con-'iguration was stable at the Mach numbers tes.ed. Photographsarid scetches of all tne models are snown in Figures 1 through 18.Flgu.-:s 4-o tnrough 55 are plot of nurnal force, •itchingmoment, rolling moment., side force arnd yawing momer,; versusangle of attacx.
10. The effects or the 1,.ducel rvJl.Ang moment. were Investi-gated by free-spin tests at the batlonal Buareau .,f Standardson a numuer uf modifications '• t.ne fl..s such as twLst, tangent,sweep and at t:e Nav.iL o:,dna:.ce LatoLa*ury usitg configurationswhicn are altered --,;ve r:&a.ca.Ly (ref. fr.
4
C '!PTDFNTIAL
C-NF DEN!TALj ,NAVC:;D .,epo:-• •'>
Reduced Fin Span Program
.I- ? ;. t.aseen some. nr."eres'. In reducin.; the frn spanvf" tne ... :' bomb. This would aid the ground and air-
lanr.e cle.rance proolens. Tests were made (reference (d))of an. eignt-fln !ýomb wi t h a fin span of wne diameLei-. TheCTrJX.gurat-orn was un3table. Later ar. attempt was radc tostan'llze the configurat.on using one-half and oze-dlametercncr-d Snrouds. Photographs and aketches of the configurationsare shown to Figures 1) through 22. The shrcuds stabilized:he bomb at the supersonic speeda but at the transonic speedsthe bomb was still unstable. Fig-res 56 and 57 show the dataobtained for these c:oriflgurationa.
Effect of Lugs Program
12. Tests were made of the Mk 81 (250 pound bomb) withmounting lugs. The stability datca for the lug configurationare shown In Figures 58 and 59. Note that this lug seems t.'cause a very slight change In trim as would be expected. Thedrag coefficient was greatly increased as can be seen inFigure uO. The drag coefficient with lugs compared favorablywith free-flight drop data obtained informally from the Bureauof Ordnance. Photographs and sketches of this configurationare shown In Figures 23 and 24.
Models, Balances, and Data Peduction
13. All the models and balances were designed and manufacturedby the Naval Ordnance Laboratory. The models were manufacturedof steel and are shown In photographs and sketches in riguresI through 24. The data were obtained uslrig a)six-componentstrain-gage balance (5-16) (see reference(g)
14. The data were recorded. usir the automatic data recordingsystem explained in reference (h), "T1m raw data are recordedinto IBM cards and the data are then reduced to coefficientform by IBM machines using the data reduction equatiorns given.n reference (I).
13. Test conditions are glven in Table 1. All angles ofattack were corrected for the static ceflectlon of the *.ala:ncesting due to the aerodynamic loads. An index of the plotteddata is presented in Table 2. The NOL sign convention isshown in Figure 25.
5
CONFI DENTIAL
I
:1W"c,..: i'v* ~ t 4V I1* cnc .S ion sI
Fiur-s;nd 63 s.,ow t", etffct of -;rn& AurationA-,9! -n t!-e *it,-n~nv mr--nt, yawllng momrent, m ind nuceid:c~ :. ~.c-'-~ '.!a nri umboar of aiT-roxim itely ,.o andionrrm~e I , heý configurations' with large increases
~n I>*.m~m~t arg .. c~esosin the inouced r-ollin~g~1Q~r~ :. ',~iir.':~.cxnant ire corkriguratIons %.nich should-- rf r:7 z: . t!. I 2tv thian 6h asi~z low drag bomb.
'. :.c . t Is irtend-,d iss a rrogress refort on th.eworn, ,One )n ~ o-~'~bomb in 'the N01. wind turn-nis. TorkisCn :Lt Ir, u~ ~ t.o-.I CL :.' .. u"Iei k~ti tile liz.-uued rlir.~nt rtZem Z~tec. . bengmaae by N-.L rersonnpi at
;~ lonl.Burauof Stazioards to stucly the induced rolLingLOV-nt- ;Anua t 'ornpil Apronaulical Laboratory to de!tr:.AnetI.- Itransoni-' aproaynamics Of tr% Ibxisting Loob, and firingsboi-.ig mado in :t'. :,OL firing range to obtain more in-for-
t I~ lo0-h-rag bcb..
6C F , : T A
CO NF IDEN:T AiNI;AVOP.D Repo-v. ,,%.:3
P'efeere::.
(a) Gri v:I n, T. - 4 1..,I-l'.unne± K.equest. W'!kWR 26•o ,Conf.
J. ) 'To ba 111 S.tJ1,' 1 n, v e 3 ...... t !aton oi' the E.v-1Q9rnb •.t Subs,.mic Speeds," NAVOCD Report 2814 (Conf.) l•53
(c) L•:.g, *..F., "Free Fi1gnh nvestigato.n of the Stabilit'yand Drui vf aie UX-i.. Ge;,eral Purpose E&me," NOAV•?D heport
1 :•o ( confr.);lju) 3'd) , ng, J. E., ."Lcw Yaw Wata or the Low Drag Bomb (EX-Io)
at Transon: . Speeds (U. 'M ,1..), NAVID ?,eport 4e?2" Con'.) '
,e) F'per, W. D., "Static Stability Charac.eridaLics of theEX-1O -4w Drag Bomb," NAVORD Report 4jO3 (Conf.) 1057
,r) DeMeri:te, F. J., Sauzza, H., Shantz, I., "MiscellaneousW'nd-Tunnel Tests on the Low Drag Bomb." NAVORD deport ,,02,(Conf.) 1950
•g) N~.oLaides, 1. D., "On the Flight of Ballistic Missiles,"
BuOrd Balilstic Technical Note Number 1, 195o (Conf.)kh) Nicola-des, J D., and MacAllIster, L. C., "A R'vlew of
4ercbali.stIc Range Besearch on Winged and/or •innedMlsslles"' MuC~rd Ballistic Technical Note Number 5, 1954
%i) ;uIcolaldes, J. D., 'Pirst Primer of Bomb fillistics,"£ Orx TechnIcal Note 20 (Unclass.) 1955
(J; Shantz, I.,. Gilbert, B. D., and White, C. E., "NOL Wind-Tunnel Internal Strain-Gage Balance System," NAVORD,.epcrt 29,• (Unclass.) 19D3"% G"ilbert, B. D., "Automatic Data Processving System (ADAPS) -For the Supersonic v,'Ind-'1unnela," NAVORD Repcrt 2di3,%..iciass. ) I953
(1) DpMerltte, P. J., Gilbert, S. D., and White, C. E.,"Contract Wr•d-Tunnel Testing," NAVORD Report 35b2 (Unclass.)
7rO'lFJ )'';%TI AI.
NAVh T- por ot 4!
l'Ab. F ITFL;T CCN:;'TX.N.lj
YA N. rsi Pi.EY.NOL'S NLYEFP.Y1
5.2
0.95 9L5
CC.
'A I-." NTAA
%AWO*-: R~eport -~3
TA1ThE 2FIN F*Of>TA;A
-'4~~Y _____CH NO. FIG. No.
-zy ~1 *C.8 28, 29,?-sic 0.8 28,9 29
20 'ra i n ,nrc.8 28, 29720 fin _:nt 062,220 fCn M.. 0.8 28, 29
?0 rn -.int o.~ .8 032 0 fncant 150. 0, 31
U .R~7 d s~an 0 C.8 32, 33I.L'27i d Sran 22 .5 .032, 23
Ea0:". 8 32, 33
2 2.".5 0.95 34. 3f. 22. .9 1, 35* !arge chcrd 22.5 0. -91 3'., 35
Easic 22.5 0.95 34t, 35* 1.t7R d sr~an 22.5 C-95 36, 37
1.'U7/R d ::-an 22G .91 3,32 d sper 22509 36, 37
22. C9. 36. 37
Porous box shrcud 22.;, 0.91 38,9 39Solid box shrouc 27.) 0.91 38, 391/2 :ox shroud 22.5 0.91 38, 39Bas ic 250.'?5 ?8,1 39Fnd ;lAtp 22-.5 0.91 41C, '1+
iavpvan@ 22 .: 0.95 1+0, '.16mall vAne 2,-.5 o.95 40', '1+Ea7,ic 22.5 0.95 0'0, '.1
End .lbte C 0.91 .29 '-3Lasic C 0.91 4.29 '31.tiL7 d zrain 0 0.91 4.2,
Lavp*.ri0 1+ '2, L- 3Small va, r.e C C.95 144w 45Large vane 0 C-95 " 4 3+5
CCNF~IV?~ TrIAL
C-:FIDEYTIAL;ierort 'I053
rAnLF .2 (Contd)Tu PLOTTFD DATA
"FIN COIFNTATIONC. ,N OF ~h Fl S MACH NO, FIG. NO
6 Fin C 0.95 1+6, 1+7t Fin 15 0.95 46, 47basic 0 0.91 4 6, 471/2 5oX shroud 00 0.91 I48, 1+9Porous Eox shroud 4'5 0.91 48, 49Solid BOx shroud 45 0.91 4+3 h9ba sl O."b, c'.t Fin C 1.58 50 51-,0 cant
1.58 50, 51Body alone 1.58 50, 51
pasI ca 22.. 1.57 52, 320 cant d12.s n.58 •2, -53l-U7R d scan 22.5 1.)7 52, 53Porous Box 22.5 1.57 52, 53Solid Zox 22.5 1.57 52, 23Fnd Pl1'e 22.5 1.57 5%, 55Basic -+22.5 •.7 5, 55C Fin 15 1.58 , 55Small vane 22?,i 1.8 2., 55
ree vane . 22.5 1.58 51+, 555 Fin, full shr'oud C C.94 568 Fin, hAlf shroud ,1) C.93 563 Fin 0 C.35 56.Fin C 0.91 5658 Fin, full shroud 0 1.58 57J 'in, half .f;hrcud 0 1.58 IFin 0 1.58 57.Fin 0 1.58 572500 EF8mb with Lug 0 0091+ Sd250m Eomt 'ith:ut jug 0 0.994 582504 Eomt with Lug 0 1.58 592500 bomb without Lug 0 1.5d 59
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CONFIDENTIALNAVORD REPORT 4053
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