,e

NASA.__I'echnical Memorandum 72661,VOl.V

(NASA-TM-72661) SPACP, SIt0TTL_ ORBITI_R N79-28137TRIMMED CENTER-OP-ORA_'ZTy EXTENSION STOD¥oVOL1]MI_ 5: RFP2CTS OP CO_PX_0_ATION

MOD'IFECATION$ ON T[IR AERODltNANXC Ollcla._CflARAC_4_BZ_TXCS._OF TIlE IA_A/8 ORBITER _T G3/02 29437

f L

, SPACESHUTTLEORBITERTRIMMED. CENTER-OF-GRAVITYEXTENSIONSTUDY.

VOLU_/EV - EFFECTSOFCONFIGURATION ,MODIFICATIONSONTEEAERODYNAMICCHARACTERISTICSOFTHE140A/BORBITERAT N_CH NUMBERSOF2.5, 3.95 AND4.6

¢

! W. PelhamPhi.llips

and RogerH. FournierI.t

JUNE1979

NISA *Aeronauticsand

National \<"n I'_'- __,_Space Administration

Langley ResmlrchCenterHampton,Virginia23(365

; ................ 979019966

https://ntrs.nasa.gov/search.jsp?R=19790019966 2020-03-07T05:31:18+00:00Z

SPACESHUTTLEORBITERTRIMHEDCENTER-OF-GRAVITYEXTENSIONSTUDY=VOLUMEV " EFFECTSOFCONFIGURATIONMODIFICATIONSONTHE

AERODYNAMICCHARACTERISTICSOFTHE140A/BORBITERAT MACHNUMBERSOF2.5, 3.95 AND4.6

4

by W. PelhamPhtlltp_ and RogerH. FournterLangleyResearchCenter

_U_IARYI

Supersonicaerodynamictestswereconductedinthe LangleyUnltaryPlanWindTunnelto determinetheeffectsof wing filletana canaramodificationson the longitudlnaland lateral-direct40nalcharacteristicsof a-]4OA/BSpaceShuttleOrbiterconfiguration.

The slgnlf_canteffectof themodificationswas to reducethe staticlongitudinalstability.The modificationsalsoprovidedslightstabiltz_J1gincrementsIn Clrectlonalstabilityat highanglesof attack.

All of the modificationsmovedthe trimmedcenter-of-gravlty1ocatlonforwardrelatlveto the baselineconfiguration,and'theincrementsdecreasedwithincreasingMachnumber. The largestforwardcenter-of-qravltyincrementwas obtainedfor thelargecanardwhichprovideda 2.5 percentof lengthextensionof theorbitercenter-of-gravltyenvelope.

INTRODUCTION

The longitudinalcenter-of-gravltyrangeof theSpaceShuttleOrbiterfortrimmedf11ghtduringentry,approach,and landlngIs quite11mlted.

Thlsputsa considerableconstrainton thea11owablemassdlstr!butlonofshuttlepayloads.In an effortto extendtheorbitercenterof gravityenvelope, a study was undertaken at the Langley ResearChCenter to determine tthe feasibilityof developlngslmple,"bolt-on"modifications.ModificationswhichwerestudiedincludedchangesIn fuselagenoseshapeandwingfilletplanformand the additionof flxedcanardsurfacestSystemsdeslgnanalyseswereundertakento determinetheWeightpenalties(ref.I),and aerodynamicheatingtestsand analysesprovidedinformationon the impactof themodificationson thermalprotectionsystemrequirements(ref.2). Wind-tunnel

" force andmomenttests were conductedacross the speed range to assesstheeffectiveness of the modifications in extending,the center-of-gravityenvelopeandthe influenceof themodificationson flightcharacteristics.Hypersonicaerodynamiccharacteristicsof themodificationsare presentedin references3 and 4, and transoniccharacteristicsIn reference5.

The purposeof thlspaperis to presenttheeffectsof planformfilletandcanardmodificationson the aerodynamiccharacteristicsof the 140A/B

1979019966-TSA03

7 orbttOr configuration at Mach numbers from 2,5 to 4.6. Thts Mach numberrange tsof stgntftcance since the most forward center-of-gravity locationfor the Space Shuttle Orbiter configuration is defined by the longitudinal

I trtm capability at a Mach number of approximately 5=. The investigation wasconducted in the htgh Machnumber test section of the Langley Unitary PlanWtnd Tunnel at Mach nu_tbers of 2,5j 3,95 and 4,6 for a Reynolds number of2.2 x 10" based on fuselage reference l_n_jth. The anglo-of-attack rangeextended from approximately -10 to 310 at sideslip angles of 0° and 5°,

SYMBOLS

The aerodynamicdata are presentedabout the body Systemof axeswith only the lift-drag ratios presented about the Stability axes. Allthe aerodynamicdata containedhereinwere nondlmenslonaIi:edusing thebaselinemodel values for w_ng referencearea, span, and mean aerodynamicchord. The moment referencepoint _s locatedat 65 percentof the fuselagereferencelength (i.e.,21.38 cm (8.42 in.)) aft of the model nose, Valuesare given in both S! and US CustomaryUnits. When two symbolsare listedfor an aerodynamiccoefficient,the second s_,holappliesto the computerizedtabulationo_ coefficientsIn-theappendix.

A aspect_atio

b wing span, 23.79 cm (9.37 in.)

mean aerodynamicchord, 12.06 cm (4.75 in.)

CA,CA axla1_forcecoefficient,axial-fpr-ce-q_,Sref

CD,CD drag coefficient dTa-o-fg-rc-e' qooSref

if1-_force

CL I i ft coefficient, -!_,'SrefCL,

C_,CBL telling-momentcoefficient,r°l]-in-_-m°-nLe-n-t% Sref b

C;_ _--_J _ : 0°, 50; per degree

Cm,CLM pitching-momentcoefficient pitc!li_r!_)}!o$))e)p.t' q,,,Sref c

CN,CN normal-force coefficient, .n°_alq=-Sreff°rce

yawing momentCn,CYN yawlng-m_entcoefficient,-q_sr_--_-

IACnl 50

• CnB i,_],_-'_-,B = 0°, ; perdegreesideforce ,;

Cy,CY _de_force-co_£f-tc_.nt,_ !!

CyB _--_--) B = 0°, 50; perdegree

L/D Iift-dragratio

_ref fuselagereferencelength,32.77cm (12._0in.)

M Macbnumber

q= free-streamdynamicpressure,Newtonspermeter2 (Ib/ft2)

R_ free-streamReynoldsnumberbased.on_ref

Sref wingreferencearea,0.02m2 (0.27ft2)

Xo,Yo modelstations,cm (in.)

angleof attack,deg

B sldeslioanale,deg ....

" body:flapdeflectionangle(posltlvefortrailingedge6BF down), deg. •

li _e elevondeflectionangle(positivefor trailingedgedown),deg.

!.

3

1979019966-TSA05

split-rudderflareangle(positivef_r tr_a_L11ngedges_SB deflectedoutboard),deg,

ModelConfigurationComponents:

il BIWVSoEF basellne140A/Borbiterconfiguration

BI baselin_,.fuselageforebody

_. smallcanardwi_hflat-plateairfoilsectio_C3

C4 largecanardw_tthflat-plateairfoilsections

E base1:Inee-]even

F baselinebodyflap

. SO baselineplanformfillet

S2 filletmodificationhavingplanformgeometrysimilarto astrake

V baselineverticaltail

W basel_newing (outboardpanel)havinga leading-edgesweepof 45v

APPARATUSANDTESTS

Model

Geometric detatls of the modelused in the wind-tunnel investigation

are shownin figure 1 and table I with modelphotographstn figure 2. Thebaseltne configuration (fig. l(a)) was an 0.01 scale modelof the RockwellInternational 140A/BSpaceShuttle Orbiter configuration described inreference 3. Themod@lhad a removableforebody and removablecomponentsin the wing planfom etllet region which allowed geometrymodifications.Themodifications shownin figures l(b) and l(c) consisted of onewingplanfom ftllet configuration, S2, and two canard configurations, C3

4

m

• 1979019966-TSA06

and C4. All configurations a_ the present Investigation IncOrporated asplit-rudder flare an_le of 55 .

The leadtng edge of the S2 ftllqt mdlftcatton pPoduceda planfom• shapevery stmt!ar _o a strake _t_. l{b)). Ftllet S2 had a leading-edge

sweepanglo of 67.4 exte, dtng outboard to Yn • 3.584 cm _nd xo. 12.929 cm.At thts potnt the fillet loadtn_-odqe sweepincreased to 85", and theeffective fillet Intersection wtth _he outboard wtng panel was the sameasfor the basellne ftllet (SO) !nterscctton. The stream_tse sections of thismodified fillet were fatted with the outboard wing panel znd had leading-edge

I radii Identical to those of the baseltne fillet, SO.

Canards C3 and C4 (fig. l(c))had _lat-plate sections with.Pounded -l_adtng edgesand sharp tra11_ng odaes, The leadtng edge-sweepangles forcanards C3 and C4 were 55.0_ anb54.7 _, respectively. The trailingedgesof canards C3 and C4 were fon_ed by Circular-arc-segments having

} radtt, o£.5.245 m and 6.217 cm, respectively.

Tests

t The Investigation was conductedtn the htgh Machnumber-test section ofthe Langley Un_taw Plan WindTunnel (ref. 6) at Machnumbersof 2.5, 3.9_and4.6. Free stream Reynoldsnumber(basedon _uselage reference length)for the investigation wasoapproxtmatel_2,2 x lOb. Test angles of attackwere varied free1 about -1 to 31° at 0_' and 5_ of sideslip. An internallymountedsix-componentstrain gage balance was used to measureaerodynamicforces andmomentsacting on the model. Corrections have beenapplied tO theangles of attack and sideslip to account for sttm_-and balance deflectionsproducedby aerodynamicloads on the model.

Transition strips Were located behind the leadtng edgesOf all model

componentsusing stngly SpacedCarborundumgrains having a nomtnal grain !tdiameterof 0.061cm. The streamwlselocationsOf the transitionstrips _!were 3.05c,i behindthe fuselagenoseand 1.02cm behindthe leadlng _iedgesof thewing planformflllets,canards,wing,and vertlcaltail. w

RESULTSAND DISCUSSION

Aerodynamicdataobtalnedinthe presentstudyape tabulatedby Punnumberin the appendixwhichalsoIntludesa DataSet/RunNumberCollationSummary(tableII)to expeditethe locationof data(or a particularconfigurationand testcondition.

LongltudinalAerodynamicCharacteristics

The longitudinalaerodynamiccharacteristicsforthe baselineorbiterconfiguration,BIWVSDEF,are shownin figure3 fortwo setsof control

= and _e = I0_, _BF= 16.3_.deflections: _e = "40", _BF "11.7(_

5

1979019966-TSA07

Effacts of the various configuration modtftcal:tonsa,re presented tnfigures 4 to 6 and m_y be indexed ,s follows:

Effect of Im_tf-tcatten Ftgure

S2 ftllet ¢

C3 ca_aed 5

P C4 canard 6

Effect of I_lanfoPm,f,tllet_reshaD1nq.- Beplactngthe baseline planform

i ftllet, 5o, Wlt'h'pl.anformfillet 5_ (fi_J. 4) producedsltgh.t increases in• CN. accompaniedby st_jntftcant redui:ttons tn lo, gt.tudtna! stability.levelsover the Machnumoerrange of the Investigation. Also notea were slightlyincreased L/D values attributable to p_l__fQrmfillet S2'

Effects of canards.- Additton of the two canards Ca and Ca (figs. 5and O, respectively) aiso producedsignificant destabtltttng shifts in thepttchtngn-momentcoefficient with C4, the large-canard, producing the largestincrement. Lift-to-drag ratio tncremerktsdue to both canardswere insignifi-cant at a Machnumberof 2.5. The C_ canard pPovt_edslightly increasedL/D values at angles of attack from _pproxtmately 9_ to 24_at the higher_lachnumbersinvestigated for _e = 10°, _BF = 16.3°. The large canard Caproducedslight Increases in L/D at M= 3.95 and 4.6 for moderateangles"of attack for both the negative and posttfve longitudinal control deflectioncondtttons tnvestt gated.

The addition of canard. C3 resulted in aerodynamiccharacteristics," similarto thosenotedfortheconfigurationwi.ththe S2 filletmodification.

The selectionof one of thesetwomodificationsshouldthereforedependonotherconsiderationssuchas aerodynamicJqeatingand effectson aerodynamicsat otherspeeds,

Effects of mdiftcattons Onforward c.g. trim capability.- The effectsof the modifications t_" ehe 140A/B orbiter configuration In terms of center

) of gravity(c.g.)forwa. _ovementare summarized_n tableIll. The c.g.' locations herein were determined for nomtnal angles of attack _epresentattve

I of entryfllghtconditions.To achieveconservativeforwardc.g.limitswiththe controlsset at thelrmaximumnose-uptrimconditions(_e= -40o,_BF = -11.7o) the nominalanglesof attackwere incremented+-4° and aACm marginof -0.015was used. Forthe analyslsOf the aft c.g.trim

coAditions (_e- 10o, _BF = 16.3°) a ACre marg|nwas not requiredsincethe controls are not s t at the maximumvalues.

All modifications shifted the trimmed c.g. locations forward with theincrements decreasing with increasing ;,lachnumber. The large canardmodiftgatton, C4, p_ovtdedthe largest c,g. shift (2.5 percetlt of bodylength) at M -4.6. The S2 planform fillet modification was alsoconsidered effective with a2.0 percent increment at M = 4.6. The smallC3 c_nardmodificationresultedin a forwardincrementof 1.0percentatM = 4.6.

6

...... ".... 1979019966-TSA08

Lateral-131recCtonal AerodynamCc-Charactertset cs• iIt

The ¢ffects of planfom ¢!11et modification S2 and canards C3and C4 on the late.ral-dtrect_lonal a(trodynamtccharacteristics of thebasolt,e configuration _tth % • -40" _d _B_ " -11.7 ° (forward trtmcondition) are prssentod tn figut_ 7 and f|gurer8 for the aft thin condition.zn general, the ftllot and canardmodtftccttons Increased the directionalstability at tile moderate-to-high angles of attack t.nvesCtgatedwtth the "lncre_nts decreasing wtth increasing Machnumber. Slight Increases tn ipositiveeffectivedliledra](-Ct(_)attributableto the fi-]letmodification _;and canardadditionsoccurredat M - 2.G andmoderateanglesof attack. _,The controlsettingshadmi_4malimpacton thaf,o..]ateral-direction_Jtrends. _,

la

SUMMARYOF-RESULTS ,,

d Tests were conductedtn the Langley Unitary Plan WindTunnel toetemtne the effects of wtng planfom ft 1let modtft cat1ons on the

longitudinal and lateral-directional c_aractertsttcs, of a 140A/BSpaceShuttle Orbiter configuration. Results are summarizedas follows.

1. Thesignificant effect of. the. wing fillet modification, S2,a,d the canards C3 and C4 was to destabilize pttching moments. Themodifications also producedsltght stabtttztng increments tn d.trecttonalstability at high angles of _tack.

2. The most forward center-of-gravity locations for the modifiedconfigurations were aheadof those for the baseline 140A/B configuration,and the increment decreasedwith increasing Machnumber. The largestforward c.g. increment was obtained for the large C4 canard modtftcatt_)nwhich provtded.a 2.5 percent of length extenston. _

o

___.... i9790199GG-TSA09

8

...................... 1979019966-TSA10

I: TABLEI.- MODELGEOMETRYPt

p.

Theorottca1 wtng=

i Area, planfOrm, m2 (ft2).......... • , . • . . . 0.02499 (0.?._90)• Ar_a, Q1Qvon, m2 (ft 2) o . . . . . . . . . . . . . . . 0.001951 (.0210)b:

_ Span, ¢m (tn.) • . , . • . . . . , . . . • • ° . . • , . 23.792 (9.367)Chord, centerltne root, cm(in.).. • . . . . , . . • • , 17.B07 (0.892)

Chord, tip, ¢m (tn.) .... • • , • • • . • ... • • • 3.501 (1.378)

Taper ratio . • . • . • • • • • . • • . • • • • • . . • . • • • • • 0.20

Aspect ratio . • • • . • • • • • • • .-. • • • • • -. • . • --_ • • 2.265

Leading-edgesweepangle, deg . . . . . . • • • • . • • . • • • • ._45.0

Trailing,edge sweepangle, deg . . . . . . .o. • • • • • . • • • • • -10.0

Dihedral angle, deg . . . . . . . . . . ............ 3.5 !

Incidence angle, deg (yo = 5.056 ¢m) . . . . .. • . • • • • • • • • 0.5

Twist angle, deg . . . . o • • . • • • • • • • • • • • • • • • • • • 3.0

Atrfoil sectton, ttp. . . . . • • • • • • • • • • • • • • 0012-64 modified

xo, wing leadtng edge, plane of syntnetry . • • • • • • • • 21.234 (8.360)

Wingplanfo_ fillet SO, baseline:

Leading-edgesweepangle, deg . • • . • • • • • • • • • • • • • • • 80.9

I. xo, wing leading-edge (theoretical) Intersection cm tin•). 25.984 (10.230)

i Wingplanformfillet S2" ILeadlng-edgesweepangle(forwardportion),deg . . . . • • • • • • 67.4

i Leading-edgesweepangle (aft portion), deg . ° . . • . • . 85.0 :t

1xo, intersection of forward and aft ftllet leadtng edges,on (in.). ° • • • . • • • • • • • • • • • • • • • • • 1;_.929 (5.09G)

1Xo, intersection of aft filletand.theoret_.Cal,wing,cm (in.). . . . . . • • • . . . . . . . . . . 25.984(10.230)

9

.... TSA11............... , ,,, ,. , .: "--".. 9790199661

t

,: TABLEI.- CONCLUDED

CanardC3s

I Exposeda_ea, _ (ft _) , . . . . . . . . . . . . . 0.001241(0.013363)Le_dtn(i-edgesweepanBle, deg . . . . . . . . . . . 64.7

Conal'dUdZ

mZ (_t2) (0 0_7380)Exposedarea, . . .-.-.-......... 0.002544 .

Lead|ng-edgesweepangle, de9 . . . , . . . . . , . 54.7

Vevttcal tat i: ill

Area(theorettcal), m2 (ft2)........... 0.003839(0.041325) i!i

Leading-edge-sweepangle, deg . . . . . . . . . . . 45.0

Rootchord(theorett,:aE), cm (tn.) . . . . . . . . 6.820 (2.688)

Ttp chord(_heorettc¢l_), cm (tn.) . . . . . . . ; 9-_55 (1.085)

Span, m (tn.).................. 8.019 (3.157)

Fuselage:

Haxtmumcross-sectionalarea, m2 (2__)_=..... 0.003595(.0387)

Length, cm (tn.)................. 32.774 (12.903)

Hax_mumwtdth,.cm.(tn.) . . . . . . . . . . . . . 6.797 (2.676)

10

1979019966-TSA12

u_

(_dr "= _ t 6qdqJ

1979019966-TSA13

L

1979019966-TSA14

2,""

1979019966-TSB01

5.654cm(2.226in)

I .Xo• 5.969cr_12.350in)

*1

CanardC3 (Co_figurationBIW.VSoC3EF)

X0 • B,470cm(5.303in) /

Section

t 6,406cm(2,522in) / _' XO,.-5.969cm(2.350in) _ 't

I \Xo. 18.771cm(7.NOin)

.1i

CanardC4 (ConfigurationB1WVSoC4EF)

(c) CanardsC3 andC4

FigureI.- Concluded.

• _ _...... -- _ ................... -- .,, .... , IIHI III IIIIIII ...............

1979019966-TSB02

21

': 1

LI..

tJ) =

_2

*t" t_4-_ 0

0 '

"0 m

4_L

*_P"J O

I

-g d

lf,l,ll'l:_()DUOl{{I{,I'I,_,()1_''{'h,,O/ilOl2qALPAGE IHP(),)I'

lg7gOlgg66-TSB03

'W

1979019966-TSB04

t_¢xl taJ

if) CxJtf_

40

0'1_ °t.,,,

U '

ta_.

[¢I_PRODUCIBILITY OF Till,'

ORIGINAL PAGE IS POOE

1979019966-TSB05

! Figure 3.- Longitudinalaerodynamiccharacteristics for the baseltne conftguratto'BIWVSoEF.(SSB- 550

. , , nll

_?;.:':_.::_;,_:,_.'_,r.... 1979019966-T SB06

2

I _._- ++o_ -'__

6o,dQg8BF,

_1 _ _0'' 0 -4o -;u-I 1:1 1o 16.3

0 " i

o 2 .,,, °+0

r II 1

" I . -" ' i:'{ 11 ++! :

14 ' J !

• ....................................iii ! • i . _.: ........: I+.__.: ......

Iiilili, ,. _ i ] ".: " : ; • " j ' : -';iiT:i +.'

iill_mv _llll ' ' " '+ . p i , , • .

CA.- .... '. .... ;i_..

.06 L ' ............. i J--_,........tI ! '. i

• , ; .............. ,+. !.. .

.04 + I I' • '* ++'.+"i "

_ZJI ,

, I

_ i i i ii j iiiii i i "1

- 4 0 4 8 12 16 20 24 28 •32a,deg

(a) H = 2.5 Concluded.

FtgUre3.- Continued. i]

1979019966-TSB07

:52

1979019966-TSB12

I;• ,

0-- so °40 ._u.a @{ c_ s2 .40 .Iu

_, $a 20 16,_L & S2 10 16,0

1

._. ; _t_.

.18 , i ;,, i !

•14 .._.

|

_. .12 i 'i

t .08 .................................... _......

.I_,t

CA ..............

.OB .................................i

.. J

•04 ............ ,...............

•02 ........i

|

t

04- (3 4 B 12 16 20 24 ',')8 132

a,deg(a) M = 2.5 Concluded.

I

i_ Figur_4.- Contlnued.

_'=*"'_*-_.... 1979019966-TSB13

1979019966-TSB14

1979019966-TSC01

1979019966-TSC03

1979019966-TSC05

$

"'16-.2 o .2 ' ,4 .... ,6 .8 I.o t.2

(c) M = 4.6 CN

Figure5.- Continued.

_,- .... LI......

1979019966-TSC07

1979019966-TSC08

32

2(I .....

i

t I ' • " 1" " ;':'"m)

i

i

!t

I' I

16 , .................i

iD *, | iL

I 8 ............:.................. ' Cana¢_6e4,deg6BF,degt

" ................ '" ' 0 OFF "40 "1],.7

4 .... _ '. I::I C4 -40. -1L7+.' I : Ii I _ _,. OFF tO 16.3.

: : ! A C4. lO 16.30

' ! .! i

......................... !.:...............,_....... .OB ! '

..".............. ',..... F ,".....

:I!.............. _ ............ t--:-

ii III I i

i

Cm ......I

-.04 .....

1• -.08!

i

-,IG '-.4 :2 0 .2 . .4 ,6 ,B 1.0 1.2 1,4

(a) M = 2.5 GN

Figure6.- Effectof canard C4 on the longitudinalaerodynamic

_:.. characteristicsforconfigurationBIWVSoEF,_SB = 550

19790199BB-TSCIO

o

- I n in i n I I ml i

-4 0 4 8 12 16 20 24 28 ,32Ca) H- 2.5 Concluded._'degFtgure6.- Continued.

_9790_9966-T$0_

.IQ'• i ]

.08 ................. I

c, ......:_, i iiii_iI_.... ,iIi•06 ......

i

•04 ...... : ............ , .......... '...... I. ' .L-.__ ....... Jt

m

;::)2

I

Iiiii ii i iii i i i i i1_1 ii i i i i ii iiii

- 4 0 4 8 . 12 16 20 24 2e 32(b) H= 3.95 Concluded.a,deg

FtguPe6.- Continued.

1979019966-TSC13

_" _ ..... _:_.............................................. 1979019966-IBG 14

,

¢

........ ' ....."" _" ......im i I-.".I.: I '::;I.i;:.b _..I_:_,..I..,.• , , , I . I , I m:., ,

• _ |,, M ,

-- " i iiii i i ii iii I I iiiii I

l% ' . , , Ii

...... ; "': "" ' .... :".,!' :"' F:" : ":::_:-':,i :i:........I

....... ' , .l._.....,.......L...--.L........... _'T:..] ' i 1i ..: _ i., I,, : , . ; • m.=_.,,,,,,Canard i..:....., .......... ._.... .; ' ;_...,.....t;...,: 0 $0 0eF............. ,,' : _ , i : , '. :: . i

.002 _,m,_ • , .... ' .......,.......... --t-..... i ..... : i ...... !---'I _---_2 url. .;" ' I ' :' ""° I ' 'i: _'_----A...__ .' " I.._.. _0 so_._c3

": oi'.......!''I" ....so c,Cnl3 , , I '_ - ',-'__'_: ' .:!I::.I,...I

, .................................. |...................................... _......... I....................... . _ . , . ,,._.

b . , t I ' I..... , _ _• I.._:.] :, "2L, ,,_n','.':l.:.002 / I , I . .., :...,,._ ,_..._ ,.,_,,I........ :............. :'_""".............. '...... :".................. :.... ".'T:.":" ,."-'-':.* ..'-_'.............

..... i

• n , ' i ,'1

, . "I ' ' [ . '. ' I. _ I ' ' "

1"4 0 4 8 12 16 20 24 28 )2

!(a)M=z.5_Igure7.- Effectof fllletand canardmodificationson the lateral-dlrectloBa]

characteristicsof configurationBIWVSoEF. 6e " "40°" 6BF " "11"7°' and

6SB" 550.

....... ".......... 1979019966-TSD02

ii : ':++........ ';+_+.......

/!

' 1 _ ] icyp i , ' ,

-,02+; I I_1

., w i;, I I)..... , .......... I . .: ! I, ."i ......, +-

I ', ' t I ." ' , i Fillet,"' ' I' ' ' 'i"+'. ' ' Canard......... , + , _ 0 So OFF

•002. + .i........................... _.-.+ ....... , I::1 SII OFF',i

o.__: ; A j,So c, Icnp

." ".002 , ! , :, ,_ i I .: . ; i ":I ,...... I_"" "" -!......................... :+" :'.'_', .......i-'-.-+l=-"_ .... 1..:" 1 . . . . l I ' o ' . • . :' . ...... '" "

• . i I , . i I , . I i : ; ' ..,' I .:':,/ ,. I, .

,,i_.,,'_' .... .,,., . , : ,;,I, ! _ ._:!.t :iU:. '.:l;';:,:,;;l!!li'_,,'':"!:_"'_ .... _":'" _!";" .., .') , "; ,,!,;. ',

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-a 4 8 12 1_ 20 24 P.8 32c_deg

Ftgure 7.- Continued.

| +

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, (a) M = 2.5 _,degt

Figure8.- Effect of filletand canardmodificationson the lateral-directional

•. characteristicsfor configurationBIWVSoEF. 6e = +lO°' 6BF = +16"3°' and

. % =55o.

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O,deg

(c) M = 4.6

Figure 8.- Concluded.,p+

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APPErlDIX

TabulatedDatai

Tho data presentedherein are identifiedin table II (Data Set/Run

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are also storedon tape in the Space ShuttloData System (DATAI_AN)arid

are identifi_ by shuttletest nunlbc,r LA-46Band data set i-de_tlfierletter_

HA. Access to the data may be (Ibtainedby wrlti_ to the followingaddress:

ChryslerCorporation,Space DivisionDept. 2910, P. O. Box 29200flewOr-leans,LA 701c_9

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