NASA Technical Memorandum 72661, VOL,IX

i °

!, ,

': SPACESHUTTLEORBITERTRIRRED

CENTER-OF-GRAVITYEXTENSIONSTUDY:

VOLUMEIX - EFFECTS• OF CONFIGURATION

: HODIFICATIONSON THE AERODYNAHIC

CHARACTERISTICSOI THE lqOA/B ORBITER IAT RACHNUMBERSOF 1.5, 2.0, AND2.5

(llASA-TB-?2661-VcI...9) 5PJICE SBOTTLZ O_EI_P. N65-1ESE6

TIiIZBBttD ClllT_R-C_-GIiAVIT¥ I]IZXNS.I:C_ STUDI.

VCLUMB 9: BFEBC'IS (,t CCaE.1GU_TION .... '

BODZ¥ICA_'ION50g IBm, AE_CD_EABIC Onclas

CtlAaaCCillZlSTIC50J TB_ 1,,0 a/e O_B_TEB a _. G3/G2 14,235

W. PELHARPHILLIPS ANDROGERH. FOURNIER

._i; JANUARY1985 r, _ .,_;._, ...,,,,

'{i.': ,',_ _ c_. :-,_,l

NationalAeronaul_csand

_:.: SpaceAclmm=strateon

: langleyRelNmmhCenter

,:: Hampton,V_rgmm23665

o.;,

" , o o ,
SPACF $tIUTTII_ ORf_lfgI! [I([HHFD _ NIII(-OK--_RAVTT¥ fXTI-NS[ON STUDYz

V()LUH_ IX--LI-FICIS Of CONt-IGIIRAII(IN HKII)IFICAfIONS ON THt_

AERODYNAHICCHARACTERISTICSOF FHE I_OA/B ORBITER

AT HACHNUNBERSOF 1.5 t 2,0 AND 2,$

by W. Pelham Phillip_ and Roger H, Fournler

Langley Research Center

SUHHARY

Wind-tunnel tests were conducted in the Langley Unitary Plan Wind

Tunnel to determine the effects of modiflcation_ designed to extend the

forward trimmed center-of-gravity envelope on the static longitudinal and

lateral-directional characteristics of an O.O1 scale_ 1_0 A/B Space Shuttle

Orbiter model at Hath numbers of 1.5, 2.O, and 2.5. The test Reynolds

numbe_ was 2.15 x 106, based on model fuselage reference length. The

angle-of-attack range was -1 ° to 32° for sideslip angles of O° and $°.

All the modifications, forward extended wing fillett a flat plate

canard, and a blended canard, provided significant reductions In

longitudinal stabiIity at all Hach numbers tested. The modifications also

tended to increase the directional stability at the higher angl,es of

attack and in most cases, provided some Increases in positive effective :

dihedraL,

r ,
INTRODUCTION

The longitudal center-of-gravity range of the Space Shuttle Orbiter

for trimmed flight during entry, approach, and landing is quite limited•

This puts a considerable constraint on the allowable mass distribution of

Shuttle payloads. In an effort to extend the orbiter center-of-gravity

envelope, a study was undertaken at the Langley Research Center to

determine the feasibility of developing simple, "bolt-on" modifications.

i Modifications which were studied included changes in fuselage nose i

shape and wing fillet planform and the addition of fixed canard surfaces.

Systems design analyses were undertaken to determine the weight penalties

(ref. 1), and aerodynamic heating tests and analyses provided Information

on the Impact of the modifications on thermal protection system

requirements (ref. 2). Wind-tunnel force and moment tests were conducted

across the speed ranqe to assess the effectiveness of the modifications on

ftiqht characteristics. Hypersonic aerodynamic characteristics of the

modification" "re presented In references 3 and #, and transonic

characteristics In reference 5.

1 The purpose of this paper is to present the effects of planform fillet

4 and canard modifications on the aerodynamic characteristics of the I#OA/B

_ orbiter configuration at Rach numbers from 1.5 to 2•5. The investigation

_li was conducted in the low Math number test section of the Langley Unitary

:!_ Plan Wind Tunnel at Hach numbers 1.5, 2.0 and 2•5 for a Reynolds number of

;ii 2 15 x 106 , based on fuselaqe reference length. The angle-of-attack range

P"C

;t extended from approximately -1" to 32" at sideslip angles of O° and 5".

2
SYMBOLS

• The longitudinal aerodynamic data are presented about the stability system

of axes, and the lateral directional data are presented about the body axes.

ALl of the aerodynamic data contained heeeln are non-dlmenslonalized using the

baseline model values for wing reference area, span, and mean aerodynamic

chord. The moment reference point Is located at 65 percent of the fuselage

reference length (i.e. 21.)8 cm (8.42 in,)) aft of the model nose. Values are

given in both SI and US OJstomary Units. When two symbols are listed for an

aerodynamic coefficient, the second applies to the computerized tabulation of

coefficients In the appendix.

aspect ratio

b wing span, 23.79 cm (9.37 in.)

c mean aerodynamic chord, 12.06 cm (4.75 in.)

_i CA, CA axial-force coefficient, Axial force

c_S

it:

;_ CD drag coefficient Drag force

_"l: Cl'' ) ....... % o,. S

_L:: CL, CL lift coefficient, Lift force

ol C_ CAL rolling-moment coefficient, Rolling moment 'i:_ , ......

• !

_ ,_ q=, Sb

'__!:_, C£e CAC__ , per degree

-:-'_i;

¢I.
Cm, CLM pitching-moment coefficient, Pttehin9 moment

q= S¢

CN, CN normal-force coeff[ctent, N°---r_ fP22_

%S

Cn, CYN yawing-moment coefficient, Yaw__.w_moment

q= Sb

/&Cn_ per degree

• Cn_ _-_-) 6=0°,5°

CY6 \-&-B--/ B=O,,5

LID Itft-drag ratio

9. _ fuselage reference length, 32.77 cm (12.90 in.)

_ M Mach number

_, q= free-stream dynamic pressure, Newtons per meter 2 (lb/ft 2)

RE free-stream Reynolds number based on £

S wing reference area, 0.025 m2 (0.269 ft2)

i

!

-i Xo' YO model stations, cm (in.)

1'

;t

a angle of attack, deg

_ _ _ -. _
_, B sideslip anqle, deq

i -!'

! _ ,-

i_ !: 6BF body-flap deflection angle (positive for trailing edge

_,_,:_ • down), deg

_,,: 6e elevon deflection angle (positive for trailing edge down),

. ,, deg.

!_ 6SB spilt-rudder flare angle (positive for trailing edges

_:_ Oeflected outboard), deg.

_.... Model Configuration Components:

_:,- r_IWVSoEF baseline 140 A/B orbiter configuration

_-. B1 baseline fuselage forebody

E:_::. Cg canard with flat-plate airfoil sections

_ C5 blended canard with contoured airfoil sections

o'':_ E baseline elevon

,_' F baseline body flap

...._. SO baseline planform fillet

'_i: S?. fillet modification having planform geometry similar to a

" ::i. strake

_: V baseline vertical tail

p_

' .... W baseline wing (outboard panel) having a leading-edge sweep

"-_' of _5 °

,!i ,tI 5

; J' j
APPARATUSAND TESTS

Hodel

Geometric details of the model used In the wind-tunnel Investigation are

shown In figure 1 and table 1, nd photographs of the model are shown In figure

2. The baseline configuration (fig. l(a)) was an O.01-scale model of the

RockwelI InternatlonaI 1;0 A/8 Space Shuttle Orbiter configuration described In

reference 3. The model had a removable for°body and removabIe components In the

wing planform ftIlet region which allowed geometry modifications. The

modifications shown In figures l(b), 1(o), and l(d) consisted of one wing

planform fillet configuration, $2, and two canard configurations, Ckand C5.

All configurations of the present Investigation Incorporated a split-rudder

flare angle of 55°.

The leading edge of the S2 fillet modification produced a planform shape

very similar to a strake (fig. l(b)). Fillet S2 had a leading-edge sweep

angle of 67.# ° that extended outboard to Yo = 3.58_ cm at xo = 12.929 cm.

At this point, the fillet !eadtnq-edge sweep Increased to 85° , and the effective

fillet Intersection with the uuthoard wing panel was the same as for the

baseline fillet (SO) Intersection. The streamwlse sections of this modified

fillet were faired with the outboard wing panel and had Ieadlng-edge radii

Identical to those of the baseIlne fillet, SO.

Canard C4 (fig. 1(c)) had a flat-pIate section with a rounded leading

edge and a sharp trailing edge. The leading-edge sweep angle was 5_.7 °. The

trailing edge was formed by a circular arc segmeltt having a radius of 6.217 cm.

The blended canardt C5 (fig. 1 (d)) was about the same size as canard Cq, but It

was contoured more reallstlcaIly for the actual flight environment where

aerodynamic heating effects must be considered.

6
Tests

The investigation was conducted In the low Hath number test section of the

Langley Unitary Plan Wind Tunnel (ref. 9) at Hach numbers of 1.5, 2,Or and 2,5.

Free-stream Reynolds numher for the Investigation was approximately 2.15 x 106,

based on fuselage reference length. Tests angles of attack were varied from _

about -1 ° to J2° at 0° and 5° of sideslip. An Internally mounted strain-gage

balance was used to measure aerodynamic forces and moments acting on the model.

Corrections have been applied to the angles of attack and sideslip to account ,,

for sting and balance deflections produced by aerodynamic loads on the model. ,

Transition strips approximately 0.16 cm wide were located behind the

leading edges of all model components using carborundum grains having a nominal

grain diameter of O.O27 cm. The streamwtse locations of the transition strips

were 3.O5 cm behind fuselage nose and 1.OZ on behind the leading edges of the

wing planform fillets, canards, wing, and vertical tall.

RESULTS AND DISCUSSION

i

Aerodynamic data obtained In the present study are tabulated by run number

in the appendix which also Includes a Data Set/Run Number Collation Summary

(table iI) to expedite the location of data for a particular configuration and

; test condition.

• Longitudinal Aerodynamic Characteristics

The IonqitudlnaI aerodynamic characteristics for the baseline orbiter

conflguatton, BIWVSoEF, are shown In figure 3 for three elevon deflections at

6RF = -11.7 ° and 6SB = 55°.
"m; t

,_. The effects of the various configuration modifications on the static h' '

_,: longitudal characteristics of the orbiter model are presented in figures _ to

_i_ 6• Replacinq the baseline fillet, $0, with the forward extended fillet, 52

- produced significant reductions in longituda] stability levels over the Mach

_ number range of this investigation (fig• ;) The model was still longitudinally

_ _ •

i_i_ stable in the nominal flight angle-of-attack range (10 < = < 13.2") at Hath 1.5,

_:i but it was unstable at the two higher Haeh numbers. With the e.g. moved to the

_'ii maximum forward hypersonic trim position, x/_=0.623, as taken from the table in

i_oi_-:: reference 6, the model was longitudinally stable in the nominal flight angle of

attack range at all three Hath numbers. The dashed line in figure ; represents

the Cm = 0 line rotated to reflect the maximum forward e.g. location.

Addltlon of the canards (figs. $ and 6) also produced significant

ceductlons in longitudinal stability at all Haoh numbers tested, but the model

ts stilt stable at Hath 1.5. Figures 5(a) and 6(a) show that the unstable break

i:

in the baseline model pitching moment curve at Hath 1.5 was eliminated by

Installing the canards. Reference 8 also shows this effect for the C_ canard at

)_.

a Hath number of 1.2. A comparison of the model longitudinal characteristics

_°i!," with the C_ and blended (C5) canards (fig. 7) indicates that the flat-plate

_:i: .canard produced larger positive pitching-moment increments than the blended

_ canard. Reference 5 also shows the same trend at Hach 6.0. Post-test

_' measurements indicated that, although the areas of the canards were nearly the

,:'," same, the estimated effective moment az_ of the blended canard was somewhat

,!,°

:,i shorter than that of the flat-plate canard, and this may explain some of the

: differences. The blended canard produced about the same negative stability

_:i::. contribution as the 52 fillet for the Hach number ranqe of these tests•

_:_i

" ,)
With the e.g. moved to the maximum forward position for hypersonic trim (dashed

zero-C m lines, ?tg_. 5 and 6) as taken from the table In reference _ (0._182

• ?or 04 and 0._3 for the hlended canard, assuming its contribution to be

equlvalant to that of S2), the model would be IongttudinaUy stable at all Nach

i,

numbers except for the blended canard at Haeh 2.5 (flq. 6(0)) where it is

; neutrally stable in the nominal flight angle-of-attack range.

Lateral-Directional Aerodynamic Characteristics

The static lateral-directional characteristics of the baseline model and

with the configuration modifications are presented in figures 8 to 12. Figure 9

:j shows that, in general, all of the modifications tended to. Increase the direc-

_'i1 tional stability of the baseline model over the higher angle-of-attack range at

--i all r4ach numbers investigated. The modifications also increased the positive

_) effective dihederal parameter, -C£8 , at Math numbers of 1.5 and 2.0, but a

_' slight reduction in this parameter occurred at Math 2.5.

: ..:i

,2_ Concluding Remarks

;=_< The results of an Investigation of the static aerodynamic characteristics

--_ of an 0.01 scale Space Shuttle Orbiter model at Mach numbers of 1.5, 2.0, and

_' 2.5, as affected by configuration modifications, showed that the extended

- fillet, flat-plate canard, and blended canard decreased the longitudinal

- stability at all Hach numbers tested. With the center of gravity moved to the

...... maximum forward hypersonic trim position, the model with the modifications was

., longitudinally stable at all Hach numbers tested, with the exception that the

model with the blended canard was neutrally stable at Naoh 2.5. The

,i

"i w modifications Increased the directional stability at high angles of attack at

::!) all ;tach numbers tested and increased the effective dihedral parameter at Math

" i

":i! numbers of 1.5 and 2.0.

i}/

q:;:

°>_. 9
REFERENCES

1. HacConoehtet Ian 0.; LeHessurier, Robert W.; and Walsht Robert F.=

Space Shuttle Orbiter Trimmed Center-of Gravity, Extension Study. Vol. V! -

System Design Studies. NASA TN X-72661, 1978.

?_. I}unavant, 3ames C.; Space Shuttle Orbiter Trimmed Center-of-Gravity

Extension Study. Vol. [I[- Impact of Retrofits for Center-of-Gravity

Extension on Orbiter Thermal Protection System. NASA TM X-72661, 1979.

3. Bernot, Peter T.: Space Shuttle Orbiter Trimmed Center-of-Gravity Extension

Study. Vol. I - Effects of Configuration Modifications on the Aerodynamic

Characteristics of the 1_0 A/B Orbiter at Hach 10.3. NASA TH X-72661, 1975.

4. Scallion, William I._ and Stone, David R.= Space Shuttle Orbiter Trimmed

Center-of-Gravity Extension Study. Vol. IV - Effects of Configuration

Modiftcattons on the Aerodynamic Characteristics of the 119B Orbiter at Hath

20.3. NASA TH X-72661, 1978.

5. Phillips, W. Pelham; Space Shuttle Orbiter Trimmed Center-of-Gravity

Extension Study. Voi.VIII - Effects of Configuration Modifications on the

: Aerodynamic Characteristics of the 1_0 A/B Orbiter at a Math Number of

' 5.97. NASA TM X-72661_ 198t+.

6. Phillips, W. Pelham_ and Fournter, Roger H.= Space Shuttle Orbiter Trimmed

_ Center-of-Gravity Extension Study. Vol. V - Effects of Configuration

_:: Modifications on the Aerodynamic Characteristics of the 140 A/B Orbiter at

L :

Mach Numbers of 2.5_ 3.95 and 4.G. NASA TM X-72661, 1979.

_ 7. Phltltps, W. Pelham; Space Shuttle Orbiter Trimmed Center-of-Gravity

Extension Study. Volume VTI - Effects of Configuration Modifications on the

Subsonic Aerodynamic Characteristics of the 1_0 A/B Orbiter at High Reynolds

Numbers. NASA TM X-72661, 1981.

_'

10
8. Ph!!iipap W. Pelham: Space Shuttle Orbiter Trimmed Center-of-Gravity

Extenalon Study, Yol. II - Effects of Configuration Hodtfieations on the

Aerodynamic Charaetartattea of the 1_0 A/fl Orbiter at Tranaontc Spoeds.

NASA TM X-726_1, 197_.

9. Schaefer, William T., 3r.: Characteristics uf Major Active Wind TunneXs at

the Langley Researeh Center. NASA TR X-1130_ 1965.

I

!,
UtW.d"r_ _._:

TABLE [. - MODELGEOMETRY

The,retreat wJng:

Area, planform, m2 (It 2) .......... . . . . . . 0.02_,99 (0.2690)

Area, eleven, m_ (ft 2) ....... . . . . ..... 0.001951 (.0210)

Span, cm (in.) .... . .......... . ..... 2J.792 (9.)67)

Chord, centerline root, cm (in.) ............ 17.507 (_.892)

Chord, tip, cm (in.) .................. 3.501 (1.378)

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

Aspect ratio ...................... 2.265

Leading-edge sweep angle, deg ............. _5.0

Trailing-edge sweep angle, deq ............. -10.0

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

Incidence angle, deg (Yo = 5.056 cm) .......... 0.5

Twist angle, deg .................... 3.0

Airfoil section, tip .................. 0012-_ modified

Xo, wing leading edge, plane of symmetry ....... 21.23_ (8.3G0)

Wing planform fillet SO, baseline =

i Leading - edge sweep anqle , deg • • . • • • • • • • • • • • • • • • 80• 9

i

i Xo, wing leading-edge (theoretical)

intersection cm (in.) ................. 25.98_ (10.230)

Wing pLeading lanform-edgfil e leswe t 52: ep angle (forward portion), deg .......... 67._

_=' Leading-edge sweep angle (aft portion), deg ............ 85.0

Xo, intersection of forward and aft fillet Leading edges,

C(_ (in • ) • q= • • • e . • e • • o • • e • • o o o • e 12• 929 (5 • 090)

I Xo, intersection of aft fillet and theoretical wing,

cm (in.) ...................... __5.98t_ (10.230)

t
TABLE [. - CONCLUDED

Canard C_:

Leading-edge sweep angle(ft 2) ........... . . 54.7

Exposed area, m2 (ft2) ................. O.OOZS44(O.OZ7388)

Blended Canard %

Exposed area, m2 (_t z) ................... 0.001839 (0.019798)

Leading-edge sweep angle, deg ............. 58..t5 .........................................

Vertical tail=

Area (theoretical), m2 (ft2) ............. 0.003859 (0.0#1525)

Leadlng-edge sweep angle, deg ............. _5.0

Root chord (theoretical), an (in.) .......... 6.820 (2.685)

Tlp chord (theoretical), cm (in.) ........... 2.755 (1.085)

Span, om (in.) ........................ 8.019 (5.157)

Fuselaqe=

Haxlmum cross-sectional area, m2 (ft 2) ........ 0.003595 (.0387)

Length, cm (in.) ................... 52.77_ (12.905)

Haxlmum width, cm (in.) ................ 6.797 (2.676) ii

I 13





-

_ 'r'''_'_'''__-,

OF POORQUALITY.
_ • I ,o, • L __°,

tO .o-_-_-_L__l. _ ' W-i ._.dr# _ ___.

•_ ,ii i :.:i:..: ! .1.L+,_..IAIt -IJ_/ I---i-d / _ _ :i

.TTSZ +,!

#_F'/-! I I • , • - .?:i

o ....... ,I I_ ,

.... [........ C"'-'_'_'" - " : --'_'_

-i -_I-_---_- ....... ".T--" -. iiii!i..1L;! " :_);I :iI .

, _--:i-.--_.-_- _:,:,!_;'' $i:illi! i!i;ii i!_ili !_ii

• "! , i " . - |: 2.!1

;_....... r.[.......i_-F..-_..._...:,?..; . -.;.,.i.r.,

' i ,I., :, 4:: _,_i,,_:

-ii. ,

..°t;{ 4....... l!!............ -..... ...............

,!

t

..o........ l _,.,_.,i............ !.....],,..,:•.,, ............. ,,,,.,,.,,,.,,.

-.4 ._l 0 .2 .4 .6 It i,O 12

" (a) M-I.5 GL

Figure 3. - Longieudinal aerodynamic characteristics

" for baseline 160 A/B configuration (B_SoEF) _BF.._I.7°;

.- esa.5_e

- 20

i

......... -- O0000001-TSBO

"I I "I" r-I,-I _I ;! , ,

L ....... =".......... I........ '-II_. .__._._

ze': : , _..l .... :.ill

24:

20t__,. ,

t''

, ..-_..]_, /___.. 4_,4_4. +._

- i , _,ja ! I I ! _ I ' I:_

12 --I-- -- ' .I, . i .: .......,...,

' I . i I _ • .:.,:T ":..'.::

•,dog , ....... i-....... :i,-,:-%!ii:i;:i

:__:._,:_.=_._.; ";i_, ,

'-_' :':;";."_.'_,!iil

! , r!l,!. .... : i i : :i .,:

_, o L - i!=J

-,_ _., ! .:I.. i i ,_l_!ii!,

_',!

i !H-T. ....... 4i ," ._ il

"_ ._e:': _L.L_L.,'.,.. , i ,.......

• i I . _!!_

....... i................... i I "i !...... :_,

,04 !.- -I.-

( ! ,, ,

0

• 4

:i.. -,04............... ' !.....' :,

1 ..... I, _ . i _ _.... ';i+

" ................................... ^.L;+,.,i ......, ,.,,a, J.. ,........_...... _ ,

"_ ., ' ' _I

l 0 ._ ,4 .6 .O 1.0 1.2 (b) H-2.0 GI.

_,_ ¥igur_. 3. - t:ont;i_'tued.

11 22 )+

"], •

P _'.... _.......!.....I..... I"'_-! ...._"T-"T", "_

_;...__,... ' __1, I, II

,- • -i ..... I...... tr_ ....

•_.I_77_F,_Li_" ./i_ 24 _--_-- .k

_0 i,_,-_--%4 ....... '----[...-_ %.L-_ L

"-_*-': .... k ....I--_---t--- [......... L..... _..... ,,-T'--I

.........I: -" :_:'

O o_x_E-_- _ ll i' i 1 : l

I I _ I i "1.....I''T----I"'_-"

'- f--Y .... o

n__ / ! , ! / / I ' . :

......... _.......... ;-- _........ -!...... ' ..... t..... ,.... _,

t i I • I ! I ' i

....! ....'

L _ ' _ I '

-

"!} _2 0 ,_ .4 .6 .8 I.O

(c) M=_-..5

"_ Figure 3. -Conttnued.

• i

mm .... _
' !:_'!'::'i"IK";7]:ii::.:]'L::: 7f_' :F "°

• * - ........ ;--V-T:IT-;..... :II__

,, LD_ z ! ....I,,o, ,, _[ _i.._

' _ i| '

..., ..:_ : ' : ' li

_::, .36

_" -,............. i--, ....

t ....

,_. 211

_,:.: _'il"" ".: : ll ".; i.....

.<_ ._E_I......... :_L.:: L.I,_

.._ --__!.. _...... :_,i_,,_, _ .,,

:: .00

,:f_ ,_, 0 .i_ .4 ._ .8 i.O

!'; (e) Concluded.

i*.i Figure 3. - Concluded.
? .......r................

:! - , I I /Z* '

::... ,6::....,' ....I........ !' 12_f +..........

121 i _

e,deg _.......,.................. ,. J j . I...... ,......................

- [ ,

4 0 i .*

::i. 4 i'-'["- '! "'

!!; .... ,o.,o

_-,;: ;::=[1 0 S2 -10

C! I . I ....

1

"' . . _ .__',.jMaximum forward

:_, 04 ..... [c.8. _tth S2

_,: o ....I...

lilli .... _t

l ) .........

cm :,...,.....;............ i _._

•;ii -.04I......_. .,...I.,,;.t , , ................................................ ,,_,_

, ..4 _2 0 .2 .4 .6 .B 1,0 t2

_" CL

(a)_=I..3

Figure 4. - Effect of fll,LetS_ on longltudJnal

:_; aerodvnamlc characteristics of_conflguration BI_'q,%EF.

' 6Bi,=- 11.7°; _SB=$5 °

£
......... 1 ....1........ '.. !...... "

i . I I

__"ta .........I ......! .....

- 4 ..... ,64

....... ! I

u

It ........... 60

(

, !

2 i......... ' _ ---

i

I....... ill

' Z.....:;...:_ i_]...::.._,: _: .

., .:-- -' .-;L: i ,44 0 S! ":

°2 .40

• - 36

. .._.... _. _._..... _..-_ _i:

. i : . .14

.......... ,16

............ -....... !............................. .I P-

................ :._.... ,-....'i. ............... ................... _........ ;.:.;..--:_...i_-

'_ i_....... .: ;............... •... 5....:i;

i *i ......... * .....

it '......' 1 1 i

........... i ........... , ...............

.... i ....,....... t ..... 0

•,4 _1 0 ,I ,4 ,t ,8 1,0 1,1

J (a)i;olii:ludlid.

,_ _t_ure 4, - Co.ti.ued, ,_


30





- o • , ._-'.,. , i:- . -

m

i

!

i"

i Ill

lJ' -1---i -'t-"........... ; _t _'i 2;l'lU l.;i</--- i''I"I-_ I- !:;_

!';, 'g _-"" ::r?-I-" !'.-!' i_""_

-J .,_ _ .__.I/__L__ . ,:,.,_,,,i_: ,I ,,

• ._i ', .I_ _ - I.'.-,,'_.

0 i , , ,,...........

. : ,# _ ::,,iI'_,l::l:.l_,_.l,_i.!:_;

"-q-" ---;'-' ..... /;i":' I r'l:--l"-I -" ,----.;F,,-_-"

4 _#F.... _ . './' /d _ ," ::_,-_!.!...__,

- I ' i " i-. .... _:_i

i i I ! ! : .'t •i.l..t:'._

0 : I .., .i ' ".....i ' I.:,

..::-:!:- ! I. :-' '".JY:I"J -I_. ,.i '"': • " ..::. .:: ! • ._: ". : • ::i Clnlrd I

." • 'r ........ 0 OU 0

:' , ' ' , ii i_ " L:.,

; _::....- .,: i., ...:: _.... _..'. "i ,._:,:' ::.-_: ;.!1. ;:-:i: _:::_'/_: _ t_1 -lO

:I: = _ __L, .I.:I"I,.,,.: ,., _I:;:I: .I: .-_ ,

", _I:'_'_:L:i_I:!I; i '__!1:"_ -i. -' i__"_* ___'_____: :_'_' ,_L__._IL_], I I..L I. I ,.I.,:,,,

-T--Tq I"!1::! I I .I .:1_l'_::;l:i _:i

.04--..4..-- _ -_ % '..__!

.... i i I..... ! " .,,..... I-i.-.-L .....-.i

• -.0 _.0 t.l '

:' ¢1.

(c) M-2. ,5

Figure 5. - Continued.

• 36


'::I ....... "'......... -_,....... ...... ,.-,...... ,i'_*I..... I_'_ _'"r_

-+___.............. , ,,.,"I...... 14_!_ .Te

- 111 ....,,, i,""ii .

' _"?' .I t i_ -'","_.-:.I

..... i.....I........... l'°'_........ --":_....I'--,"--%T-_. '. . ._.__ _ !..:

, i _]_ ..... !'7_......:i/i,_ ..

r-!' ,_.... _:-:-.,L..4 ......l--t_ -_

, O L I I,! I I i ' i "1"40 m"_ J,,m

o ....... i ._-i , . i_ --.---r--_! i ...... I-'_. i .=,44 13 0

"_ - I ' _1_

.:. .Tr-'-..... -I.-_ =. - ] -i..... . .. _

J. " :i.40

-' --I--''-"i--,i_l _ l ,.T-? --! ...... ! ..J.:..i

..... _,...._---t,-T--_. ....t "

, , ) ! ' i I t. • :

.... '............ i::I--''

, 'i •_- . _i__.... _=..__,,=i:-__._

........ '................. )r"iT-'".- -i.....i., ...!._

• - :'-' -i ,' _'_"

......... i.....:r-i-V,L!---"!-_'---_

.,.l_._. !-_ : -I _ !.-_ _)

.i _i"-:. i

i_, ........-7_ /!--.i_ i__ '" .---._

".i ( _,-' ..... _;/ .. !": !, -._--_._

_, " _ i : i I ._L._

° t .....'................ r.... ! I ! i .'

--'T-" I '"..... t ' ....-- " ..............._..... I ...... ' ..........'....._-- -

I ! _ ' d i t I ) :

_-T ' i ' ' ' ! , ',

' .............. I ): - I............... ' '................ ' ' ..... ' ....I ......'

......,........ I .................. _-...... ,-..-..I---L--- .04

.... _ I...... ,.... i....!......... _............ !-!-.'-_ .... I -- _ .... _ ,,' 0

,,4 ,_2 0 ,2 .4 ,6 _ 1,0 I_

(a) Concluded. C_

Fisure 6. - Continued.

39

........... _-_-'; '_t_-,_, _- . (_
2O

24

20!

16

1!°

-40Ue

O._-1o

24

20

16

12

8

4
43 ,D




48
49

oOZ ; .... -" .......... m : " _. ,_'-r ....

I

0

%

". 02 _ -"

,o ,

6e, deg .002 - -

0 o

-10

<> -20

0

¢np

- 002 ........... i

i

•002 ............................ :--.

CZ6 " . :

a_ ,i il

: ; 002

"'004-4 0 "4 "8 12 ' |5 20 24 "" 28 32

O,deg

(b) H-2.0

Figure 8. - Continued.

51
:.:,-

:: ".004., 0 4 8 ]2 16 20 24 28 32

_:: o,leg

' _ (c))t-2.5

"i

Ftsure 8. - Concluded.

iI -

•02 _.... r....

I I i l , ! .j

f I

0 ii l i ii i i i i

% _ i '

p

t

' ..02

Modification

i ' i 0 None

.ooz _ . , i.....o s2

• ' _. ' ' _, c5

Cn_ 0 I , : ' , _ " ' '"' iII .....Ii' I! " i

i .... } ............ " " • f

•002 .... _l .... : , . • . , I '

i

' i i: i Clp ' I i _ , '

l'" "i"" ," i I

i ; i I : _ ; I

-,002 .

! ; I ,

2 _

-4 0 4 6 12 15 20 N 28 12 )5

n; deg

(5) H=2.0

Ftsure 9. - Continued.

:il

.,_
/ 9.+. ........... "i'll -----*'-"[++ ++:;- ............. ++ .............
il 6e.dq.

' 0 .1o

"" ' ° ": r.....!i

cv_ o , i '

-.o2

(a) H-1..5 •

Ftsure 10. - Lateral-directional aerodynamic characteristics

for confisuration B1WVS2EF. 6BF--ll.7 ; _SB-55 _
o

6e. dq.

0 -lo

D -2o

•02 _ ' J f ; " I I

: ' t I

t

f

O,

Cyp

o

i I

I

:" _ 04 ....

_ h

;_ .002 .....

",002" .. ! i

; ".004 ... :

i

• .i .If

"_ cZP i

0 i i i

-002 i

-004-4 0 4 8 12 16 20 24 28 32

:. g,deg

' _ " " (b) H-2.0

i i FLsure lO. - ContLnued.

:i'

:i

!
6e. deg.

_,. ,:::) 40

_ n -2O

E

• '02F ! .... ' ' ........ I

; I ! t

J I I

o, ! ; 

:i:: CYl3

_" -- 0"-"-"0 -0 5 4:)-

- 02- 04 _000"-I_'--'"o:

_!.:

•002

_,: 0,

:.-. Cnl5

I.'-

;002

;_:- .00t ........ i

_ CID '

o

b'L .

-4 0 4 8 12 16 20 24 28 32

:: O,deg

i*_: (c) H-2.5

_I' FLgure 10. - Concluded•

F!-

5,",

!,
:O4

.002 • ! ....

. 0 I _ LI " .... *

Cnp -.002 .... - : I__

•

".004

: .002 .........

f

¢'!P _ '

i

i

I . i i

t

-4 0 4 8 ]2 ]6 20 24 28 )2

O,de9

Ca)M-Z.5

Fisure 11. - Lateral-dlrectlonal aerodynam2c ;haracteristics for

confisuratlon BIk_SoC4EF. _BF=-II.7"; 6SB'55"

59

..m

....... _°- .
, 6e,deg

0 o

r'l -1o

°,l ........ iI'

0 I + . I

Cyp , _ _:_..._o------o

..,02 o00oo'_ ,0 -o'-'-=--_ " -

;04

,002 ....

0

CnI)

-i" ...002

i

! ' t •

.OOZl . ..... , : !

, i .......i l ;

I

Ctp I ' : _' :+ Iz

O j I I I II II ] I I

o__..._ ....

;002" i

t

-_:: ",004

++ "4 0 4 11 ]Z 16 20 ?,4 28 _IZ

+:

o,deg

- (b) H-2.0

FtBure 11. - Continued.

'I

:il.

:I. +o

e

,e_ .=_1 ,i :_1+, - - :. (

................. i..... Jl!..........:t

62

°:................_.........................._+- ,,,_.._.._.°,,....._ .....L."..._,_,
i'i'

y..,

. ,° !

o

• 6e, _.

_.:. O -10.

•o2 D -2o ''_ '4

'?: 0 -- . , I

•_::.._ Cy_

;/

•' - 02 00000--o O O---,C 0- 9- --_

_:o•

% 04

ii

t:i,: -,004

- "_; '- i,

" ¢III I

-: -"_--i..__..._.

._ ",004

'.: -4 0 4 8 12 ,6 20 24 28 32 34

:_ ", de9

' ":: (b) M"2.0

i'i Flgure 12. - Continued.
. O2 I_'l !

I

I

Cvp 0 0

-.o2 ooo<>o--C o _ -o- ,

i

-.IN

•(X)2 _i

I

I

ii i ,, • i •

-. 11112 .

t

,002 ........

: I

_ ... I

Clp

-oo2J _ ,e o, _

;

_ ". 004"-4 0 4 8 i2 16 20 24 28 32

__t o_de9

(c) M-2.5

Figure 12. - Concluded.

.1

'l

: ;'_. 64
!:

"!i APPENDIX

_" TabuXated Data

e

,)

: The data presented herein are identified in table II (Data Set/Run Number

_-_: Collation Summary)by configuration and run number. These data are also sorted

_ on tape In the Space Shuttl.e Data HanagementSystem (DATAMAN)and are identified

: by Shuttle test numberLA-46A and data Set identifier letters RHG. Access to

:_!- the data may be obtained by writing to the following address:

Crysler Corporation, SpaDeDivision

:;_i Dept. 2910, P.O. Box 29200 .

_ NewOrleans, LA 70189

; I

1 '

!'!f t

t

_i,i i

1 

t

.!i

if"

.5 ,)



"IFIyIII_ lI _ f

t__ . ................

IL

_t m it II

_,__,__ __-.___.

(.1

hi _

_ ,_- .

'_ _ I I ! I _ I I t 4 I t I I I I I I _.

f:.' _'I I I I I _ l _ II i I ! I II

0

:*") i

),

.___

--_)'2Iitll 111

!:-!

m



73

-. +_ 4_ ++'"°°

I I IIIII _+ IIIIIII

!l|+++++++ i_+++++_+ -- _ + .,' .. m +.

_ _ -

_¢°,,,' ..... _ .... _, , _ _ ,L__......

+ + ........... +,+++++++++++

++ +t _

+

+_4 .... : ,,,, ....++' +

' _ |+ +++++++++ i

- ++_+_|+++i++ + "* *'**'**** _IIIIIIIIIIII ............

+ mmm+m++mm _++_m+mmmmmm

_iIIIiiiiiIII _IIIIIIIIIIII

+

"

+=++_+++ IIIII ++++_

imtIIIII ++'++'+!'+m.

I ! ililil ! _i It1111

lllll

+ • ; 75

.................. _-,,--++.,__+,,.,,.++,i_ - : .+ ..... :::::::-_. + ' +,,_+ . " +........ - ..... :++ --'_ ................. +
U, n

'," }

_i _ "'""'''" __'"_

......."'".......'""

_ -

'_:: i _°_°°_°°_ __ .....

IIIOI ¢ Illl

IIIII , I

:I

: 76

i

af i
. ._.._ .......

IIIll

°,_,,_; ,_. _ _ ...... _!.._.!._! , _ _ g _

e_ _ " _ jjljjlijjjOl _JlllllJJiJlt

o;:i_ _;;_ ....... .._ _.,,, _ .. ._..

_. . " _ % • _ .......
!! ,!!! '" ' 'iI i! i i i nl !!

n li _ u Ii

i

1i!11!|!_ 11ii||!!1iii _ ii ai . aweo Iolo_o eooo Illlllllllll

,!, 'ttftt l

e..........

- ;; _ ',,,,,,,,

_i_ii_--t - Ii ;;_ ........ _ ..... _ .._ IIII _

78

,, - . ,

8 ............ 8 ............

I

,!!i!!!!i!ii! ,!!!!!i!!i!!!

loci t..4ll

!i II!!I!'"'" "ii1I!'"""

i '?:.............. I : !! !!i "'"">""='" ° "'""'"'" "'" ° "" "

", "_i_ " _ ....

i_._._._-' i_._._._._._._._._._._._

NNNNNNNNNNNN

iii

_, 0O
' i _,_

ii !ii!!ii _ °!I_ i i ii |!_!!i_i_!_

-_,_ . _i '° °' _!_I!!_!__,,,, _i °' ° _i ,,., ! !i_!_! ..

i:_il _ ....... '"<"<<<'<<

;_ _ Q o o o

• .......... u¢¢tCttttttCt

• __ ___

+ - !!'i"g'iii" ° !!!'! !!!i l

;i _o o I o _ I o o o o _

• ........ _ o ?

I

,-, +!!!!1!!t!!!! +!!!!!!!II!!I

.... t___ t= ...........

IIIIIlll"

o_ 81
82

• ---f:-

S

I

_ OIilIIIIIf|| llllilOOlOOl

j ...... _ .... _ ........ 9...

IIIO ___*_ ___

_i _ ' "

_ _ "****'***'***oo! V_*;*.****.***IOOO

_ _ _ _._ _,_

_ ,_ .......... _ ............

o . _____=_ _ _-___ _ ._

e.ee ........... .*eeeeeeeeee e**4e_.e .: |__,__

1

88

1
;'IT iVY,_ . ....++._ %-i

IP

" _ _ ,,,,,,,,,,,, ,,,,,,,,,,,,

_i !!!_!'!!!!!_ !!!!_!!!!!!! 4

_ _ " _ "_ , • ,_ _ ........

L

_ _ee_e§[ _ e mssee i

i

_,. _ _ . _ _ _ _

++ i ++++++"+_+= +

.+_ IIII iiiiiii IIIIiiiiiiii

_

+_ +_+|+|t++ IIIIII tI +IIIIII + ,.I. +. _+ IIIII mm IIII mm

!

£+ ,

 illl..lll +

' 89

1

_!i ..

!

N. .................................... _ ....... =,. k
,or • _i! ,o,,_. __i ,,, ii;ii ii iiiiii

- _ _ .. _ .... | , e _ .....

n n I ii Ii

_ _,,,,,,,,,.,_

............ _ ......... ;;;

_ _ _............

lllll$1lllll

_e_eeee._eee* _e_ee,ee,_ee.

i __IIII ........ _ IIIII __|_!_

In In

90
i

.... _._. , , ° , '_--_i _

L

• • ee*eeee ee *eeeeeeee

fill _ Ill*

• _eeeeeeee eeeeeee*e_e

''_ _ -- Illl|llll|ll iillllllllil

, N

IIII Ill

,_ _ ¢ g ; g _ ¢ ¢ ; ¢ g (,, u ¢ ¢ ¢ ,. ¢ ¢ ¢ ¢ ¢ ¢ ¢ _

III

91

|!!1!!!!1!!1! |1!1!!!I!!iii

i1!1