a NASA CR- NATIONAL AERONAUTICS AND SPACE A D M ~ ~ J ~ ~ ~ ~ ~ ~ I ~ ~

/3+@ P (NASA-CB-1344C 9) R E S U L T S OF ~ N V E S T I G ~ T I C N S O N AN ~ . C ~ ~ - S < A L E 140A/B C O N F I G U K A l ' T t : N SPACE S H U T T L E V E H I C L E O P B z T i f i f l O D E L (34-P) IN H NASA/LANGLLy ( C h r y - j l a r C O r p . ) 75p HC $94.75 SSCL L L E

SPACE SHUTTLE

AEROTHERMODYNAMIC DATA REPORT

JOHNSON SPACE CENTER

HOUSTON, TEXAS

OBT6 UNagernent services

BPACE DIVIsK)(Y Q CHRYSLER CORPORATION

https://ntrs.nasa.gov/search.jsp?R=19740026208 2018-06-06T18:50:31+00:00Z

DATE: July, 1975

PUBLICATION CHANGE THE FOLLOWING CHANGES APPLY TO PUBLICATION: DMS-DR-2125

TITLE: Results of Invest igat ions on an 0.004-Scale l4OA/B Configuration

Space Shut t le Vehicle Orb i te r Model (34-0) i n the NASA/Langley Research

Center Hypersonic He1 ium Tunnel (OA88)

Change i s made t o subs t i tu te the

body length" f o r Reynolds number

are iii, 3, 11, and 12.

term "Reynolds number per

per foot." Affected pages

Prepared by: Operations--Maurice Moser, J r . 4 Reviewed by: G, G, McDonald, J. L. Glynn/ .

I) b'

- , ' L 9 Concurrence : Approved : Kemp, Ma ger

Data Management S q v i ces

PAGE 1 OF 1 -- DISTRIBUTION SAME AS FOR ABOVE PUBLICATION

DBTB AMNagemont services

CHRVSLER CORPORATION

September, 1974

DMS-DR-2125 NASA- CR- 1 34,409

RESULTS OF INVESTIGATIONS ON AN 0.004-SCALE

l4OA/B CONFIGURATION SPACE SHUTTLE VEHICLE

ORBITER MODEL (34-0)

I N THE NASAILANGLEY RESEARCH CENTER

HYPERSONIC HELIUM TUNNEL (OA88)

P. J. Hawthorne Shuttle Aero Sciences

Rockwell International Space Division

Prepared under NASA Contract Number NAS9-13247

Data Management Services Chrysler Corporation Space Division

New Orleans, La. 70189

for

Engineering Analysis Division

Johnson Space Center National Aeronautics ~ n d Space Adnrinistratfon

Houston, Texas

WIND TUNNEL TEST SPECIFICS:

Test Number: LaRC 22" He 7422 NASA Series Number: OA88 Model Number: 34-0 Test Dates: 12 through 28 December 1973 Occupancy Hours : 60

FACILITY COORDINATOR:

David R. Stone SSD, Hypersonic Analysis Sect ion Bldg. 1247-8, Room 1208 Ma i l Stop 163-A Langley Research Center Hampton, V i r g i n i a 23665

Phone: (804) 827-2483

PROJECT ENGINEERS:

P. J. Hawthorne David R. Stone Rockwell I n te rna t i ona l Langley Research Center Space D i v i s i on SSD, Hypersonic Analysis Sect ion Mai 1 Code AC07 Bldg. 1247-8, Room 1208 12214 Lakewood Blvd. Mai l Stop 163-A Downey , Cal i f o r n i a 90241 Hampton, V i r g i n i a 23665

Phone: (213) 922-2440 Phone : (804) 827-2483

DATA MANAGEMENT SERVICES:

Prepared by: Liaison-D. A. Sarver, M. J. Lanfranco Operations--Maurice Moser, Jr .

Reviewed by: G. 6. McDonald, J. L. G l y n n p .

Approved: /.;@.(, 1 , -,A- N'; D.' Kemp, Manager

concurrence: wM wider, anager

Data Management Services F1 ght Technology Branch

Chrysl e r Corporation Space D i v i s i on assumes no responsi b i 1 i t y f o r the data presented o ther than d i sp lay cha rac te r i s t i c s .

RESULTS OF INVESTIGATIONS ON AN 0.004-SCALE

140A/B CONFIGURATION SPACE SHUTTLE VEHICLE

ORBITER MODEL (34-0)

IN THE NASAILANGLEY RESEARCH CENTER

HYPERSONIC HELIUM TUNNEL (OA88)

BY

J. Hawthorne, Rockwell In ternat ional Space D iv is ion

ABSTRACT

This repor t documents data obtained during a wind tunnel t e s t o f an

0.004-scale 140A/B conf igurat ion SSV Orbi ter i n the NASAILangley Research

Center 22-inch Hypersonic He1 ium Tunnel . The t e s t was conducted during

December 1973; 60 occupancy hours were charged. A l l runs were conducted

a t a nominal Mach number o f 20 and a t Reynolds numbers o f 0.7, 1 .l, 2.0, 6 and 4.0 x 10 per body length.

The complete 140A/B model was tested w i t h various elevon se t t ings

and add i t i ona l l y i n wing of f /bodyf lap o f f conf igurat ion a t angles o f

at tack from 18 t o 54 degrees a t zero yaw.

Purpose o f t h i s t e s t was t o obta in high hypersonic long i tud ina l and

l a t e r a l -d i rect ional s tabi 1 i ty and contro l charac ter is t i cs o f the updated

SSV conf igurat ion.

iii

TABLE OF CONTENTS

ABSTRACT

INOEX OF HODEL FIGURES

INOEX OF DATA FIGURES

NOMENCLATURE

REMARKS

CONFIGURATIONS INVESTIGATED

TEST FACILITY DESCRIPTION

DATA RE W C T I ON

TABLES

I. TEST CONDITIONS

I I. DATASETIRUN NUF3ER COLLATION SUMMARY

I I I. MODEL DIMENSIOML DATA

IV. HYPERSONIC VISCQUS INTERACTION PARAMETERS

FIGURES

MODEL

Dk fA ?

APPENDIX

TABULATED SOURCE DATA

Page

iii

2

2

3

6

8

9

10

INDEX OF MODEL FIGURES

Figure T i t l e

1. A x i s sys terns.

2. 140A/B Orbi ter f o r t e s t OA88.

INDEX OF DATA FIGURES

T i t l e - Effec t o f Reynolds Number on Conf i gura t i on

Elevon = 0, HH-20 Balance

Elevon = -5, HH-20 Balance

Elevon = -5, HH-19 Balance

Elevon = 15, HH-20 Balance

Elevon Effectiveness, Re,L = 2.0 m i l l i o n

HH-20 Balance

E f fec t o f Reynolds Number on Body Alone

HH-20 Balance

Schedule o f Coef f ic ients Y 1 ot ted :

Page

2 3

24

Schedule o f Coef f i d e n t s P l o t t e d Pages

A) CAF, CAB, CN, CL, XCP/L, CLM, CDF, L/DF vs. ALPHA CN vs. CLM CL vs. CLM

SYMBOL - b

4 M

P

4

Re ,L

v

a

B JI 4 P

Ab .

b

c.g.

!m C

S

SUBSCRIPTS b 1 8 t . OD

PLOT SYMBOL -

CP

MACH

Q( N S f 1 Q( )

RE ,L

ALPHA

BETA

PSI

PHI

WEF

LRn

SREE'

MRP

XMRP

I[MRP

r n P

N a m l C L A R I R E General

EINITION

speed of sound; m/sec, f t / s e c

pressure coef f ic ien t ; (q - p,)/q

Mach number; ~ / e

pressure; ~ / m * , psf

dynamic p r e s s b e ; 1/2pv2, ~ / m ~ , psf

unit Reynolds number; based o n body length

veloc i ty ; m/sec, f t / s ec

angle af a t tack , degrees

angle of s i de s l i p , degrees

a n g l e of yew, degrees

angle of r o l l , degrees

m d s s densi ty; kg/m3, s lugs / f t3

Reference & C. G. Defini t ions

base srea; m2, it*

wing spen o r reference spen; m, it

center of g r av i t y

reference length o r wing mean aerodynamic chord; m, f t

wing aree o r reference area; m2, f t 2

moment reference po in t

moment reference point on X ax i s

moment reference po in t on Y ax i s

moment reference po in t on Z ax is

base l o c a l s t a t i c conditions t o t a l conditions f r e e stream

N-CLAWRE (Continued )

Body-Axis System

PLOT SYMBOL SYMBOL - - IrEFTNITION

no-1-f orce coefficient; force q s

axial-force coefficient; PS

side-force coefficieat; side force as

base-f orce coefficient; qs

'Ab(pb - PCO)/~S

C Ab

CAB

' ~ r CAF

c m CIM

forebody ax i a l force coefficient, CA - CAb

pitching-moment coefficient; i t ch in mamcnt -7kT

yawing-moment coefficient; Win * Cn CYN

CBL rolling-moment coefficient; moment q,%

Stability-Axis System

l i f t coefficient; lift qs C~ CL

C~ CD

C% CDB

% CDF

cy CY

Cm CIM

drag coefficient; drag qs

base-dreg coefficient; + forebody drag coefficient; CD - C%

side-f orce c a f f i c ien t ; qs

yawing-maaent coefficient; Win mQment *.

rolling-mamcnt coefficient; rlSb

l i f t - to -drag r a t i o ; q c D

l i f t t o forebody drag r a t i o ; cL/cDI

Symbol

Xcp'l B

P lo t Symbol

BDFLAP

ELEVON

RUDDER

SPDBRK

AILRON

ELEVTR

BALANC

NOMENCLATURE (Continued) Addit ional Nomenclature

De f in i t i on

long i tud ina l center o f pressure locat ion, f rac t i on o f body length

wing incidence angle, degrees

bodyflap de f lec t ion angle, degrees

elevon def lec t ion angle, degrees

rudder def 1 e c t i on angl e, degrees

speedbrake def lec t ion angle, degrees

ai leron, t o t a l a i l e ron def lect ion angle, degrees, ( l e f t a i l e ron - r i g h t ai leron)/Z.

elevator, surface de f l ec t i on angle, posi t i ve def 1 e c t i on t r a i 1 i ng edge down, degrees.

?arameter name t o document balance u t i l i z e d

t n tes t i ng , BALANC = 19 (LaRC HH-19), BALANC = 20 LaRC HH-20). see tab le 1.

REMARKS

Measurement o f the 34-0 model a t the Los Angeles D iv is ion of Rockwell

I n t e r n a t i ~ n a l revealed inaccuracies i n the conf igurat ion, which d ic ta ted

the use o f unique reference dimensions and areas t o reduce the raw " a : . ~

t o c c e f f i c i e n t form.

S ign i f i can t model e r ro rs revealed were as fol lows:

1. The overa l l length o f the model was 5.5 inches f u l l scale (FS)

too long. This e r r o r i s d i s t r i bu ted w i t h 1.0 inch a t the nose and 4.5

inches a t the rear o f the fuselage.

2. The elevon hinge 1 ine was located too f a r a f t , being 2.875

inches FS i n e r r o r a t the l e f t hand t i p and 1.0 inch FS a t the r i g h t hand

t i p f o r a net e r r o r o f approximately 2.0 inches.

3 . The leading edge c u f f s were staggered; the l e f t hand c u f f was

10 t o 20 inches f u l l scale a f t o f the cor rec t s ta t i on measured p a r a l l e l

t o the FRL and the r i g h t hand c u f f was near ly correct .

4. The elevon t r a i l i n g edges were located too f a r a f t , 6.56 inches

FS on the l e f t s ide and 8.46 inches FS on the r i g h t hand. When combined

w i th a properly located leading edge, t h i s y ie lds an oversized planform.

5. The balance center was located 3.0 inches FS iorward from i t s

nominal loca t ion a t s ta t i on 1073.7 instead o f 1076.7.

Analysis o f the er rors by the Rockwell Space D iv is ion Aerodynamics

Group has l e d t o the generation o f non-standard constants t o y i e l d data

which i s i n reasonable accord w i th those obtained i n other t es t i ng pro-

grams. These values and those o f the nominal Orb i te r are presented below:

REMARKS ( ~ o n c 1"ded)

Dimension

Wing area (S)

Wing span (b)

Mean aerodynamic chord (F)

MRC, Xo s ta t i on

Elevon area, per side

Elevon moment arm, f o r appl icat ion t o incremental data only (distance from MRC t o 0.25 elevon M.A.C.)

Nominal Orhi t e r ( f u l l s ~ d l e )

2690. ft2

936.68 i n

474.81 i n

1076.7 i n

Used f o r 34-0 model ( f u l l scale)

2741.8 ft2

936.68 i n

481 .648 i n

1081.39 i n

238.93 ft2

331.89 i n

Addi t ional ly , the elevon def lect ions were measured and a l i s t o f

%RUE was obtained. U t i l i z i n g these values f o r p l o t t i n g a lso improves

the agreement of the data w i t h those obtained from other sources.

Elevon Pane 1

l e f t r i g h t

l e f t r i g h t

l e f t r i g h t

1 e f t r i g h t

Nominal de

CONFIGURATIONS INVESTIGATED

During t e s t OA88, the 140AlB vehicle was tested i n f u l l up and wing

o f f cor~f igura t ions.

The fol lowing l e t t e r designations were used to denote components of

the 140A/B conf igurat ion:

Fuselage t o the outer mold l i n e contours o f drawing VL70-000143 incorporat ing an in tegra l canopy and blended i n t o the 1408 wing by drawing VL70-000200 I r i sed

Canopy t o VL70-000143 1 i nes

Elevon of planform and sect ion o f VL70-000200 wing w i th hinge 1 ine a t Xo = 13.87. The elevon gaps are not simulated

Center p i v o t bodyflap w i th hinge l i n e a t A = 1528.3 and planform as denoted on VL70-000145 drawing

Orb i ta l maneuvering system pods mautlied 0'1 the upper rear o f the fuse1 age w i th rocket engine nozzles simulat,ed, 1 ines per VL70- 000145

Rudder ut i l izc !d w i th V8 v e r t i c a l t a i l and shown on VL70-000146A

45" sweep leading edge s ing le center 1 ines mounted v e r t i c a l t a i 1 o f modified dlamond sect ion as per VL70-000146A

VL70-000200 I w i s e d wing: 1408 wing blended t o 140A body; wing i s of 81 "/45O sweep leading edge and i s 6 inches FS th icker a t the body than 140A; a i r f o i l i s modified NASA 0011.3 a t Y = 199, 0012.64 a t theoret ica l t i p ; = +0°30', dihedral = 3'30' a t TE; t i p i s defined by VL70-00~002

The tested configu at ions were denoted as:

1 40A/B ' a t f B26 C9 E26 F7 M7 R5 "8 ': 16

Body alone = BZ6 Cg M7 R5 V8

See the Remarks section f o r model anomal ies.

TEST FACILITY DESCRIPTION

The WSA/Langley Research Center 22-inch Hypersonic He1 ium Tunnel i s

a blowdown f a c i l i t y w i th a normal operational time of 30 seconds f o r aero-

dynamic force and m e n t tests. Studies are conducted i n the 22" diameter

t e s t sect ion a t Mach numbers o f 18 t o 22 a t stagnation pressures from 300

t o 2000 ps i and a t t o t a l temperatures from 480°R t o 960°R; these t e s t I -4:

condit ions a l low f o r a Reynolds number vd r ia t i on o f 0.7 x l o6 t o 11.5 X

106 per foot .

The tunnel i s a lso equipped w i th an Electron Beam Flow V isua l iza t ion

System which allows co lo r photographs w i t h depth o f f i e l d t o be made o f

the shock system.

Operational parameters o f the contoured nozzle f low charac ter is t i cs

are ava i l able i n NASA TN D-2489, 1964, Longitudinal Characteri s t i c s o f

Several Configurations a t Hypersonic Mach Numbers i n Conical and Con-

toured Nozzles, by Arrington, Joiner and Henderson.

DATA REDUCTION

The LaRC HH-19 and HH-20 balances were used t o measure Orb i te r forces

and moments a t four Reynolds numbers. Data were converted t o standard

NASA force and moment coe f f i c i en ts and are presented about a nominal

moment reference center i n both s t a b i l i t y and body ax is systems.

Addi t ional ly , the normal force center o f pressure i s presented as

where Xcp i s the long i tud ina l distance from the inner mold 1 i n e nose

s ta t i on (Xo = 238 inches f u l l scale) t o the center o f pressure.

Reference dimensions f o r t h i s t e s t were d i s t i n c t l y non-standard and

may be found w i th an explanation as t o t h e i r o r i g i n i n the Remarks section.

, ",

TABLE I.

TEST CONDITIONS

IDATE : Dec 73

REYNOLDS NUMBER MACH NUMBER

DYNAMIC PRESSURE STAGNATION TEMPERATUF (per body l eng th ) (pounds/sq. inch) (degrees Fahrenhe~t) -

18.1 0.75 x lo6 0.65 4 5

19.0 1.15 x lo6 0.94 45 20.3 2.05 x lo6 1.56 45 21.6 4.00 x lob 2.62 45

(nominal)

-

I BALANCE UT IL IZED: LaRC HH-19

CAPACITY: ACCURACY: COEFF IC IENT TOLERANCE:

N F 0.5% SF a 0.51 A F 0.7 lbf 0.5% PM 2.5 in I b f 0.5% -- RM 0.5 in Ibf 0.5%

COMMENTS: Utilized with 35" prebend HHT dogleg sting

Applies to datasets 13 through 16

TABLE 1 . - Concluded.

EST : OA88 I IDATE : Dee 73

TEST CONDITIONS

REYNOLDS NUMBER DYNAMIC PRESSURE STAGNATION TEMPERATUR MACH NUMBER (pounds/tq. inch) (degrees Fahrenheit)

BALANCE UTILIZED: LaRC HH-20

COMMENTS:

CAPACITY: ACCURACY: COEFFICIENT TOLERANCE:

PM 7.0 i n - l b f 0.5%

RM 1 . 5 i n - l b f 0.5%

YM 2.1 in - lb f 0.5%

U t i l i z e d w i t h 35' dogleg HHT

Applies t o datasets 1 through 12

*REVISED 1;/24/74

TABLE I 11. -MODEL DIMENSIONAL DATA

MODEL COMPONENT : -JQXLB&

GENERAL DESCRIPTION : 0

NOTE: B,c, is identical to & except underside of fuselage has been

refaired to accept W l l

C: -47. REUUSE 12

DIMENSIONS FULL SCALE MODEL SCALE

5 173 Li,161

*Length (OML: Fwd Sta Xo=235),In. 1293.3 *Length (IML: ~ u d ~ t a . ~0=238),1n,=,

Max Width (@ X, =1528.3), ~ n . 264.0

Max Depth (@ x0 = i464), In.

Fineness Ratio

Max. Cross-Sectional W.88

Wetted

Base

TABLE 11 1. - MODEL DIMENSIONAL DATA - Continued.

MODEL COMPONENT : CAmPY - Cn

GENERAL DESCRIPTION : U. -6.

0 . O O b MODEL DRAWIE: S S - A O O ~ ~ ~ , RELEASE L2

DRAWING NUMBER . VL70-000143A

DIMENSIONS :

+ Length

Mox Width (e xo =

Mox Depth (e xo =

Fineness Ratio

Areo

Mox. Cross-Sectional

Plan form

Wetted

Bose

FULL SCALE MODEL SCALE

TABLE 111. - IIODEL DIMENSIONAL DATP - Continued.

MODEL C O B P O N N T : 1 I

--

MODEL SCALE: 0.0040 MO-G: S S - A O O ~ ~ ~ . REWSE 6

DRAWING KCYRER: YL70-000?00. -~0608g, -006092

DIEENS IONS : FULL-SCALE

Area - Ft 2 210.0

Span (equivalent ) , In. 349.2

I n b ' d equivalent chord, I,,

Outb'd equivalent chord , 1n. ~~ R a t i o movable surface chord/

t o t a l surface chord

A t Inb 'd equiv. chord *

A t Outb'd equiv. chord

Sweep Back .Angles, degrees

Leading Edge

, Trailin& edge

Hinge1 lne o .no

* Area Moment ( Product of o.rea & c) , F t 3

+Mean Aerodp-mic Chord, In.

MODEL COMPONENT : - -- GENERAL DESCRIPTION : ean.fipurntlnn~ nrm +*r

MODEL SCALE: 0,004

DRAWING NUMBER '

DIMENSIONS : FULL SCALE MODEL SCALE

Length (Xu= 1520 to Xo = 1613),1~. 91.000* 0.172

Max Width, ~ n . - Mox Depth (B Xo = 1520), In. 23.000 0 $092

Fineness Ratio

Areo - Pt2

- Max. Cross-Sectional - Plonform 142.6 0.0023

Wetted

Bose 41.847 o .00067,

wPbdel dim. measured from model sta . 15.20

TABLE I 1 I. - MODEL DIMENSIONAL DATA - Continued.

MODEL COMPONENT : - M

GENERAL DFSCRIPTION , ~d~ &-

W ! . E * Q d l Q b - sS400147. RE&EASE 12

DRAWING NUMBER e; -

DIMENSIONS F U L L SCALE MODEL SCALE

Length (OMS n d Sta. Xo = 1233.0),& 1 2 7 . m 1.708

Max Width (@ Yo = 1450.0), In.

Max Depth (@ xo = 1493.0), In.

Fineness Ratio

Area

Max. Cro ss-Sectional

Plan form

Wetted

Base

TABLE 111. - tlODEL DIMENSIONAL DATA - Continued.

MODEL COXPONENT: - R, d

MODEL SCALE: 0.0040 4. {

DIKENSIONS: FULL-SCALE MODEL SCALF

Area - ~t~

Span (equjvalent ) , In. I n b ' d equivalent chord , In. 91.582' 0.366 Outb'd equivalent chord , In. 50. 833 0.203 <

Rat io movable surface chord/ t o t a l surface chora

A t Inb 'd equiv. chord 0.400 I

A t Outb'd equiv. chord 0.400 - 0 - k

Sweep Back .Angles, degrees

Leading Edge

T r a i l i ~ Bdze t

MODEL 3CArJ3: 0.0040

Area (meo) - Ft 2

Planf o m Span (Theo) - In. P.;pect Ratio Rate of Taper Taper Ratio Sweep-Beck Angles, Degrees.

kading Edge * Trailing Ed.@

0.25 Element Line

Chords : Root (Theo) YP 268.500 . 1.074

w Tip (Theo) 7I.P . 10~. 1~70 d?4- MIX --u%d!s a.199--- F ~ S . s b . of .25 MAC L!&AL W.P. of .25 MAC B.L. of .25 IYIC

hrlL; - 0.000 -Q.mQ-

Airfoil Section Leading Vedde .iwle - Deg. 10.000 10.000 trail in^; Wedge I:n@e - Dcg. 11,. qza_ Leading Edge ,,Fhdius ? .or)

r4.020- 0.008

Void Area 13.17 0 2 ' -

Blanketed i.rea

TABLE I I I. - RODEL DIKNSIONAL DATA - Concluded. I * , . *REVISED 4/24/74

WDEL 23WOYt,T: WING-Y , 1. ;

T Y C S A ' , DESCPPTXON:- &

NOTE: Identical to W,,#xcept a i r f o i l thicknees. Mhedral angle is along

TOTAL DATA i \ r e a - c ~ e o . ) Ft2

Planform Span (Theo In. Aspect Qatio Rate o f Taper Taper Ratio Dihedral Png?e, degrees I nc I dence A?g 1 e , degrees Aemdynami c Twi st, degrees Sweep Back Angles, degrees

Leading Edge Trai l i ng Edge 0.25 Element Line

chords: Root T h t ~ B.PwOoOw T ~ D , Theo BOPw MAC

t I #us, Sta. o f ,25 MAC

* W, P. of .25 MAC * B.L. of 2 5 MAC

EXPOSED DATA * Area (The01 Ft2 + ~pan,-(~h&) Xn. BPI08 + Aspect Ratio

Taper Ratio Chords

* Root BPI08 * Tfp 1.00 b

T

*MAC L

* Fuse S t a b O f m25 MAC * W.P. of .25 MAC * B.Lw of .25 MAC

A i r fo i l Section ( Aclaell Mod WA) XXXX-64

Root2 =

h t a for (1) o f (2) Sides Lead4ng Edge Cuff * Planforn et2

* Lcaalnp Edge Intersects Fur N. L. @ Sta + Leadl nr Edge Intersects Uing d Sta

21

RUN NUMBER MACH NO.

.- - - 20.3

21.6

19.0

- -

20.3

Zi. 6

20.3

19.0

19.0

20.3

21.6

20.3

19.0

18. 1

19.0

20.3

21.6

1

DYNAMIC PRESSURE

@W

1.5813

2.6170

0.9623

-

- 1.5703

2.6275

1.5977

0.9567

0.9614

1.5782

2.6236

1.5821

0.9708

0.6785

0.9792

1.5864

2.6466

--

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APPEND1 X

TABULATED SOURCE DATA

Tabulations of plotted data are available on request from Data Management Services

OR

IGW

AL

PA

GE

lb

OF P

OO

R Q

UA

LITY

PA

CE

2

(RQ

CW

jrl2

l f

25

IA

N 7

4

)

PA

RA

ME

TR

IC D

AT

A

b n p n : e j 3 ~ g $ ; # ; p L - g

I41 91 . . 4q?4 , , q ~ g ! P A

1 1 I 1 1 l 1 1 1 1 1 1 1 1 1

* a E I B ,

CLM

-.

M3

74

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I60

- .C

f.i1

18

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-.cxw

Vs

- .MS

%

-.013m

- .rG?s

:a - .D

!uQ

-.r5

4730

- .C.u

287

-.S

t71

0

- .'as%e

-.re

376

- . wa

s5

OR

I(X

VA

L PA

GE

IS

OF P

OOR

QU

ALI

TY

a.3

1m

=.I

N.

YW

P

= 1

.3~

38

ttuklS

I.9

Eb

. IN

CW

S

VlR

P

= .?

KE

G

INC

HE

S 3

.v.m

IN

CH

ES

Z

(IR

f =

.rSJT

IJ INCkES

.IflJ

.li S

CA

LE

CL*

- .Id4

40

- .C1

5224

- .?

I632

1 - .D

74?¶

- .5

84

26

-.

09

31

7

-. 10

55

4

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21

12

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1U

Ha

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49

6

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v33

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llQ

3

- . 18

63

3

-.IS

25

3

- .?+54

32

.CYJ

G

RID

lEW

T

INT

ER

VA

L =

-5

.m/

5."

U

OR

IGIN

AL

PAG

E I

S OF P

OO

R Q

UA

LITY

- W a e n *

N a , O A

k' m X p X a a ; % 3 2

TAB

UA

TLO

X

XR

CL

O

AT*

. L

LR

C z

m ra

zz ta

m1

6*-

80

LA

RC

22-I

NC

h

hE

.TU

. 7422 R

l-1

4'3

AlB

(W-1

9)

CL

M

. -.

Q1153

- .ti1531

-.?I1

230

-.o

15

m

- .01

741

-.%

el2

4

-.?12716

- .03048

-.rA

722

- .?i6

*4

-.?

17211

- .?

17985

- .'-a

349

- . K#-

i23?

1

OR

IGIN

AL PAGE IS

OF BOOR

QU

ALI

TY

.?S

t -

5.

m

.m

55

.wc

CAB

-.w

ill$

! - .

W.ilL

i9

-.?f.i

lll

-.M

11

9

-.W

12

4

-.W

13

4

- .'&

I47

- .Lii165

-. Wl

82

-.L

W198

-.w

:i13

- . 'Xi

2E

6

- .'X

i247

- .?#.-I?

%-.o

m e n W W Y

PPf LI..

WF

EU

CN

Cf

DA

TA

MC

?

= L

RC

C

= O

RC

?

= S

C4

LC

=

MACH

21 . 6'3

.3

21 .-

21 *=a

21 .u

.X,

21

.m*

21 .W

-Y<O

.M

CR

AD

IMT

IN

TE

RV

AL

=

-5.-

5.m

OR

IGIN

AL

PA

GE

IS

OF P

OO

R Q

UA

LITY