PB82-258765
Relation of Toughn~ss Teat Values to.Fatigue Cracking in Bridges
MisBOuri Univ., Colwabia
Prepared for
Pederal Highway AdainlstrationJefferson City, NO
Aug 81
1... .1111,7 ' .. e ,.a. oJ 7F1711 .IM ..tlSI
-
T~chnical I~cport Documentation Pog.1. R.porl No. r,.;."..;-.=. N;;:
-----_.__._- -----,3. Re-C:lplent \ C ,:'o'og NG !
FHWA/MO-78/2 PII! 25876 5 i,_._- I4. Ti.l. Ot'Id Subtill. S. Report Do'.
IRelation of Toughness Test Values to Fatigue August 1981Cracking in Bridges 6. P.rformlng 0"90nl r:otlcn Code
8. P.rforming O,gonization Reporf No.7. Au.ho,I.)
IJames W. Baldwin, Jr. and James A. Cooper9. P.rfo,m'ng O'goniaotion Nome and Addr.,. 10. wo.~ Un,. No. CTRAIS)
Department of Civil Engi neerf ng FCP 4SL1-012University of Missouri - Columbia II. CContract or Grant No.
Columbia. Missouri13. T~p. 01 R.po" ond P."od Cover.d
12. Sponlorin9 Agency Na",. ond Add,••• Final ReportFeb. 1978 to August 1981
Missouri Highway and Transportation Department14. Sponsoring Agency Code
80123 S1.5. Suppl.m.n'ar~ Nal..
Prepared in coopration with the United States Department of Transportation,Federal Highway Administration
16, Ab.'rac'
Tension. Charpy. dynamic tear. C-399, and da/dN tests were conducted on threeheats of A36 steel cut from a highway bridge which had been tested to failurein fatigue. Tension tests and E-399 tests were conducted at temperaturesranging from 700F to -2000F while all other tests were conducted in thetemperature range from 700r to -SOoF.
During field testing, the girder from one heat appeared to be more susceptibleto fatigue failure than the others. but there were no significant differencesin either fracture toughness or laboratory crack growth rates. Crack growthrates decreased with decreasing temperature, and did not appear to be influencedby fracture toughness. The E-399 plain strain fracture toughness test wasfound to be unsuitable for A-36 steel.
-18. Di .tribution S,ot.-nen,17. K.~ Wor".
Fatigue. fracture toughness, bri dges. Mo restrictions. This document issteel. material char~cterization available to the public through the
National Information Service.Spdngfield, Virginia 22161
19. S.c-uri'y Clo..,if. (of this report) :20. S.tu,ity Cl .....il. (0' .hi .. pa,.l 21. No. of P ag•• 22. Prite
Unclassified Unclassified l1¥-
Form DOT F 1700.7 (8-721 Reproduction of completed pOlle outhori led
•I
RELATION OF TOUGHNESS
TEST VALUES TO
FATIGUE CRACKING IN BRIDGES ~
STUDY 78-2
Prepared for
MISSOURI HIGHWAY AND TRANSPORTATION DEPARTMENT
by
JAMES W BALDWIN. JR.
and
JAME:.S A. COOPER
DEPARTMENT OF CIVIL ENGINEERING
UNIVERSITY OF MISSOURI-COLUMBIA
COLUMBIA. MISSOURI
August 1981
in cooperation with
U.S. DEPARTMENT OF TRANSPORTATION
FEDERAL HIGHWAY ADMINISTRATION
Theopinions. findings. andconclusions expressed in this publiCatiOnare not nec:esaarity those of the Department of Transportation, FederalHighw8y AclministratiOn or the Missouri HighWay and TransportationDepartmen1. This report does not constitute a standard. specification. orregulation.
t i
ABSTRACT
Tension, Charpy, dynamic tear, C-3'9, and da/dN te.t.
were conducted on three heats o~ A36 steel cut from. high
w.y bridge whtch had been tested to f.ilure in fatigue.
Tension test. and E-39~ tests were conducted at temperature.
ranging fro.70·F to -200°F while all other tests were
conducted in the temperature range from 70°F to -50°F.
During field t.sting, the girder from one heet appeared
to be more susceptible to fatigue failure than the others,
but there wer. no significant diff.rences in either fracutre
toughness or laboratory crack growth rate •. Creek growth
rat •• d.cr •••• d with decre•• ing temper.ture. and did not
appear to be influenc.d by fractur. toughne.s. Tho E-399
plain .train fracture toughne.s t.st was found to be unsuit
able for A-36 steel.
f f t
TABLE Of CONTENTS
unueT "list of Illustration.
List of Table. v t I
ACKNOWLEDGEMENT ' ....... vHI
CHAPTER 1 - INTRODUCTION
1. 1 Baek~U'ound
1.2 Objective.
1.3 Fatigue D.sion
1.~ Fatigu. Craek Growth Analv.i.
1
I
2
2
a
14
14
15
17
17
17
H
36
. . . . . 36
47
47
47
49
57
6'
63
73
79
....
CHAPTER 3 - MATERIAL DESCRIPTION
3.1 Test Specl.ens
3.2 Tension Test
3.3 Ch.,.pv Te.t.
3.4 Dvne.ie Te.,. Te.t.
3.5 E-399 T.st.
CHAPTER 2 - SUMMARY, CONCLUSIONS AND RECOMMENDATIONS
2.1 Su••• ry
CHAPTER 5 - RESULTS AND DISCUSSION
5.1 G.n.,..l Ob.ervation. • ••••
5.2 Effect of Te.p.r.tu,.e
5.S Eff.ct. of M.t.,.ial Prop.,.tl ••
2.2 Coneillsions
2.: Reco••endetions
CHAPTER 4 - FATIGUE CRACK GROWTH TESTS
4.1 Speci •• n D•• tgn end P,..p.,..tlon
4.2 T•• t Equlp••nt
4.3 T.st ProCedU,.e3
4.4 D.t. Reduction Methods
5.4 Effect of Load Shedd;ng
REFERENCES
APPENDIX
i v
79
LIST OF ItlUSTRATIONS
Figure 1 - Typical stre~~ v 5. CycieUI to Failur.
Figure 2 - Life Span of a structure
Figure 3 - Three "'ode Types
Figure 4 - Typical Crack length vs. Number of Cycles
Figure S - Determining AK and da/dN
Figure 6 - Regions of Fatigue Crack Growth
Figure 7 - Bridge layout and Heat Number!!
Figure 8 - Specimen Locations, .; .4 Bottom 1
Figure 9 - Specimen Locatipns, 4 ,4 Bottom 2
Figure 10 - Specimen locations. 4.4 Bottom 3
figure 11 - Specimen Locations. 4 • 4 Bottom 4
Figure 12 - Specimen Locations. 4 • 1 Botton:
Figure 13 - Specimen Locations, 2, ;) Top
Figure 14 - Specimen Locations. 2.3 Bottom
Figure 15 - Specimen Locations, 6,2 Bottom
Figure 16 - Specimen Locations, 4,2A Bottom
Figure 17 - Specimen loeations. 4.2C Top
Figure 18 - Speeimen Locations. 4,28 Top 1
Fioure 19 - Specimen locations. 4.28 Top 2
Figure 20 - Tensile Test Specimen
Figure 21 - Tensile Test Results
Figure 22 - Charpv Test Specimen
Figure 23 - Charpy V-Notch Test Results
Figure 24 - Dynamic Tear Test Specimen
Figure 25 - Dyne,,'; e Tear Test Results
Figure 26 - ASHI E-399 Specimen
Figure 27 - AST,., E-399 Results
Figure 23 - da/dN Specimen Design
Figura 29 - I''lTS Machine!
Figure 30 - Gaertner Traveling Mieroscope
Figure 31 - Cold Test Schematic
Figure 32 - Cold Temperetu .. e Box with Specimen
Installed
Figure 33 - Specimen Installed in Clevis8s
Figure 34 - Seven Point Polynomial Method
v
4
5
7
10
11
12
18
21
2.3
24
;'5
26
27
28
29
30
31
32
33
35
37
38
39
40
41
43
43
50
51
52
53
56
59
vi
Figure 35 - Reduced Data for Heat 271,981 at - 50° F
Using Secant Method 61
Figure 36 - Reduced Data for Heat 271,981 at -SOoF
Using Polynomial Method 62
Figure H - dll/dN vs. AK % for Heat 282,484 at -SOoF 64
Figure 3 !~ - da/dH vs. AK % for Hea t 282,484 at 0° F 6~
Figure 39 - da/dH vs. AK :r for HQa t 282,484 at 70° F 66
F i gu r. 40 - da/dH V3. AK% for Heat 351,680 at -50°F 67
Figure 41 - da/dH vs. AKx for Heat 351,680 at 0° F 68
Figure 42 - da/dN vs. AK% for Heat 3S1,680 lit 70°F 69
Figure 43 - da/dH v s . AKx fOI" Heat 271,981 at -50°F 70
Figure 44 - da/dH v s . AKx for Heat 271,981 at 0° F 71
Figure 45 - da/dN v s . AKx for Heat 271,981 at 70°F 72
Figure 46 - Results fo I" Heat 282,484 75
Figure 47 - Results for Heat 351,680 76
Figure 48 - Results for Heat 271,981 77
Figura 49 - Results at -SOoF 80
Figure SO - Results at 0 0 F U
Figuro 51 - Results at 70 0 F 82
y i i
L1ST OF TAH ES
TABLE 1 HEAT NUMBERS 19
TABLE 2 CHEI'1ICAL PROPERTI ES 1 9
TABLE 3 TEST SCHEDULE 20
TAH E 4 ASTM E-399 TEST RESULTS 44
TABLE 5 SECANT METHOD SAI'1PLE CAlCULATIONS 60
TABLE 6 LINEAR REDUCTIOH RESULTS 74
vi i i
ACKNOWl EDGEMEN T
The work reported herein was conducted in the Civil
Engineering Laboratori.~ u~ the University of Missouri
-Columbia under sponsorship of the Department of Transporta
tion. Federal Highwr.y Administration and the Missouri High
way and Tran~portation Department.
Sincere appreciation is extended to personnel at the
Bridge Division of the Mis50uri Highway and Transportation
Department and the Division Office of the Federal Highway
Ad~inistration for their support and helpful suggestions
during the course of this study.
1.1 BACKGROUNp
CHAPTER - INT~ODUCTIOH
1
While the number of catastrophic failures in bridges is
low, the fact that they do occur has led to increasing
concern within the engineering profession about tho poten
tial for f~tigue and brittl~ failure in steel bridges.
Relatively recent failures resulting in human 1055 have been
largely responsible for heightening this concern. The fact
that some bridges develop cracks under service conditions
while others uf essentially the same design do not, leads t~
some speculation that the problem is at least In part
related to some property of the material. As a result there
has been a recent move towards adoption of fracture tough
ness acceptance specifications for bridge steels.
Unfortunately, there is a great deal of controversy
surrounding the type of acceptance test for such a specifi
cation. On the one hand there i~ the AST" E-399 test which
is theoreticallY best but is almost prohibitively e~pensive,
while on the other hand there is the Charpy test which is
quite economical but is not universally accepted as valid.
Between these two are the Dynamic Tear and Bend tests. The
problem is complicated by a lack of knowledge concerning
threshold values Tor any of these test~ beyond which crack
ing becomes a problem in actual bridge structures.
During the full scale feti~ue test Cl)M of a highway
bridge in southeast Missouri, it became evident that certain
girders. Which were identifiable by heat numbers, were more
prone to cracking tha~ the others. At midspan, one girder
fractcred twice through the bottom flange and web, Nhil. the
other three were loaded to essentially the sam. stress
MNumbers in p.r.nthesi~
references
refer to the list of
load cycles expected during the service life of the member
is equal to or less thDn the numb~r of cycles to fai lure at
the design stress. This is known as "safe-life" design.
Typically. fatigue design data are presented in the
form of an S-H curve; a plot of possible stress fluctuations
(5) versus the number of cycles to failure (N). as shown in
Figure 1 (2). It h~s long been recognized that the S-N
curve is a function of material properties. geometry of the
member, and fabrication flaws. As a result. S-N diagrams
are determined by conducting fatigue tests on specimens
design~d with the particular material to be used and to
simulate fabrication flaws and details.
Because fabrication flaws are distributed randomlv.
there is considerable scattor in the data from these tests.
As a result of this scattEr and uncertainties conc~rnin9 the
magnitude and number of stress cvcles during the service
life of the structure. it is necessary to apply rather large
safety factors in safe-life design to ensure against failure
in the worst possible casa.
In recent years, it has been recognized that there
exist three distinct stages in fatigue failure (See Figure
2) (3). First is an "initiation" stage where an initial
flaw develops into a sharp-tipped notch or crack. The
number of stress cycles during this stage is a function of
material properties. magnitud~ of repeated load. geometry of
the member. and geometry of the flaw.
The second or "growth" stage is the period during which
the net cross section of the member is gradually reduced by
stable growth of the crack under repeated cyclic loading.
In bridges. this growth stage usually spans a period of one
or more vears during which it is possible to detect and
repair the crack. Growth rate is primarily a function of
stress amplitude and material properties.
Eventually. the c~eck reduce. the cross section to the
critical point where there is either unstable crack growth
resulting in sudden failure due to brittle fracture. ductile
tearing, or general yielding. This third or "failure"
loading applied to
steel cut from the
2
levels and no cracks dev.lop.d. In addition, at the ends of
the eight cov.r plates the bottOM girder flanges develuped
craeks at all locations while onlY two of the eight top
flanges dev.loped cracks. Upon completion of the fatigue
test. arrangements were made with the U.S. Army Corps of
Engineers to salvage material frOM critical sections as the
bridge was d.molished.
1.2 OBJECTIVES
The objectives of this work were:
1) To examine the effect of cyclic
st.el sp.clm.ns mad. from A-36
"issouri test bridge.
2) To .xamine the difference in fatigue crack growth
rat. between three different he.ts of .teel used.
3) To examine the difference in fatigue crack growth
rat. with varying temperatures,
4) To det.r.in. the r.lative effectiven.ss of conv.n
tional fracture toughness t.sts in determining the
susceptibility of A-36 bridge steel to fatigue
cracking. and
5) To d.termin. which fractur. toughn.ss t.st is best
a. an acc.ptanc. t.st for fatigue design.
1,3 FATIGUE DESIGN
fatigue i. the t.chnical ter. for failures which ar.
the r.sult of cyclic loads on a structura. Nor.ally the
a.plitud. of the no.inal cyclic .tr.ss i. below the yi.ld
str.ngth.
Traditionally fatigue ha. b.en treated a. a total-lif.
phenom.non. The nu.ber of load cycle. ~hat will cau •• fail
ur. is determined a. a function of the cyclic service
stress. Th••••b.r i. d•• ign.d such that the total nu.ber of
1Smax
•••
o
• oo •
••---+
4
~ signifies no failure
NUMBER OF CYCl ES ~
Figure 1 Typical Stress vs. Cycles to Failure
Q).....CD .=-:.= c ,c .2 Io - Q)
~:-=:0)- ,
n:l ~-a.~
0- ClI
I~c .... 0 ::l0._ ...
HIu::l
I '"...(Il
CD 10
I lU ow(.) 0en c:
I Cl 100 0-
<Il.GI
/ z ow. ....fI'J o-lQ)
N
I (.)GI>-
U k:l- CllI
0 ....foo
"-CD.aE:::J
Z
/,
5
6
stage, occurs without warning and occurs ov.r a very short
period of tilll •.
The point where unstable crack growth b.gins is a func-
tion of Maximum nominal str.ss. crack geometry. and a prop-
erty known as fracture toughness. This point can be
pradict.d reasonably well with the aid of modern fracture
mechanics analysis. In such an analvsis. the effect of crack
length and applied nominal str.ss are combi~ed and expressed
as stress intensitv. K. The general equation for the calcu-
lation of K is:
(Eq. 1>
f(g) = a paralll.ter that depends upon the sp.c;men andcrack geom.tries
• = maximUM no.i~.l .tress
The stress intensity yalue poss.ss.s the units ksi ~
and .av b. var;.d at any crack l.ngth by yary;ng the appli.d
str.ss. Ther••x;st thr.. basic tyP.s of crack surface
displace.ents known as lIIod.s I, II, and III as shown in
Figur. 3. Th. op.n;ng lIIod., lIIod. I, is the .od. which will
be discuss.d in this work and the str•• s inten.itv valu.
a ••oci.t.d with this mode will her.after be called K%.
Physically, K% d ••crib.s the ••gnitude of the .lastic
.tr.ss fi.ld .round the cr.ck tip and i. a ••••ur. of the
in the vicinitv of the cr.ck tip,
Fracture toughn•• s of the .at.rial is .xpr••••d a. Kxc. the
critical value of K% wher. un.tabl. crack growth occur.
under plan••train condition•• A direct t •• t for d.t.r.i-
T••t. such .s the
p
p
7
x MODE'
p
y
xMODE II
p
Figure 3 Three MOde Types
MODE II'
Charpy (ASTM E-23) and Dyna.ic Tear (ASTM E-604) provide for
indirect deter.ination of fracture toughness.
Recognition of the fact that fatigue i. a progre.sive
failure which occurs in three separate stages paved the way
for develop.ent by the aircraft indu.try of a de.ign concept
known a. "fail-safe" de.ign. The philosophy of this concept
is to provide. through a co.bination of initial de.ign and a
regular inspection progra., a procedure which will ensure
that even though cracks develop. they will be detected and
repaired before cata.trophic failure occurs. Thus. the
frequency of inspection Must be such that there is at lea.t
one inspection between the time a crack i. large enough to
be certain of detection and the tim. a catastrophic f.ilure
would occur.
Whether the safe-life or fail-safe design criterion is
used. specifications and acceptance tests must ensure that
the fatigue crack growth rate in the Material of the struc
ture Is no greater than that assumed by the designer. In
the case 0' safe-life design. a crack growth rate gre.ter
than that as.umed during de.ign would shorten the life of
the .tructure. creating the potential for failure before the
end of the d.sired service life. In the ca.e of fail-safe
de.ign. a crack growth rat. greater than th.t a.sumed in
deter.ining the insp.ction interval might re.ult in
catastrophic collapse before a crack wa. det.cted.
1.' FATIGUE CRACK GROWTH ANALYSIS
The stress intensity factor. K~. is not _ .at.rial
property, but .er.ly a function of the appll.d .tr.s•• geOM
etry of the sp.ci.en and geo.etry of the crack (~). Th.
stress int.n.ity vari •• during cyclic loading fro. a value
K% ••• at the .axi.u. applied .tress to KZ.'ft at the .iniMu.
applied str •••. Th. differ.nc. b.tween ~he.e i. the .tre••
intensity range, AK~, or
9
CEq. 2)
for any
crack length. a, on the a-H curve (Figure 4). Thi~ velue is
curve, da/dH. or the
the slope of theplotted on a log-log scale versus
rate of crack growth (Figure 5) •
a-H
et
each corr.sponding value of a.
This plot then takes on the form shown in Figure 6 (5).
This curve is easily divided into three regions.
is characterized by slow fatioue growth. or no growth at
ell. as there exists a value of 6K% below which no crack
growth is seen. Region II is a linear region, which Pari5
(6) has described by the equation:
da/dH = c (6K%)·
where.
(EQ. 3)
c = intercept on the da/dH axis (log 6K%=O. 6K=l) ofa line fitted on the linear portion of the curve.
• = slope of the curve.
This power relationship has been demonstrated bv others
including Barscm ( 3 ) . The importance of this is that the
coefficients become material properties
which describe the fatigue crack growth properties of the
steel.
The curve i. not linear in Region 111. however. This
region ;s characterized by rapid. unstable crack growth
limiting values of the creek growth rete.
which re.ches
represent
final fracture quickly. Regions I and III
The
crack growth rate is elmost zero in Region 1 end almost
infinite in Region 111. There thus exist two asymptotes at
They are called
ilQ
x...C)zW...J
~
o-<a::::u
NUMBER OF CYCLES, N ......... ....o
Figure 4 Typical Crack Length Vs. Number of Cycles
to
J:l-t.'Zw aoJ
~
o<C{a::o
AK calculated at 'a'
AK -APx f(a,geometry)
I
NUMBER OF CYCLES, N
//
/'/
dadN - slope of
a- N curve
11
Figure 5 vetennining M< and da/d!'!
Z'"C....to'"C.wle(a:::I:I-
~a:l.?
~
U-ca:uw::;)o
~l.?o..J
IIII.III1III
.1IIIIII
REGION I II
REG ION II
12
REGION III
LOG STRESS -INTENSITY FACTOR,M
Figure 6 RegioDs of Fatigue Crack Growth
the threshold
asymptote. 6KxHS'
growth.
asymptote. 6KTH'
respectively for
and the
zero and
13
instability
in'finite crack
CHAPTER 2 - SUMMARY, CONCLUSIONS AND RECOMMENDATIQNS
2,1 SUMMARY
Fatigu. crack-growth rat. tests were conducted on 2&
compact tension .pecimens frOIll the three heat. of st.el
recovered from the Missouri test bri dge. Tests we,.e
conducted at 70° F, 0° Fend -50° F with stre•• intensitv
ranges varying from 22 to 40 ksi Jinches.
Crack growth rate, da/dN, varied sigmoidally with
stress-intensity range fro. approximately 0.9 x 10-' to 0.1
inches per cycle . In all ca.8. crack growth was
• lower at low temperatures than at room temperature.
Material property te.t. including chemical analvses,
ASTM A-370 tension te.ts, ASTM E-23 Charpy impact tests,
ASTM E-604 dynalllic tear test •• and ASHI E-399 plane- strain
fracture toughness te.ts were iliad. for e.ch of the three
he.ts of .t.el, CharFlY and dynallic tear tests were
conducted at temperatyres ranging from -50 DF to +80 o F while
the tension test. and ASTM E-399 fracture toughness te.ts
were conducted at temperature. ranging from -201°F to +aOoF.
Because of the high fracture toughness and limited
thickness <5/1") of the .ateriel. none of the ASTM E-399
fracture toughne •• te.t. sati.fied the conditions for deter
m;nation of the plane strain fracture toughness. All of the
material property tests indicatad as.antial1y tha sama prop
ertie. for all three heat. of .te.l.
2.2 CONCLUSIONS
1. Fatigua crack growth rat •• in .t•• l r.cover.d fro.
the "i ••ouri t •• t bridge are in the •••e rang. a5
~ho •• report.d bv l.r50. fDr AST" A-36 .t•• l. Howev
ar. growth rat. in the t •• t bridge .t.el ••••• to b.
intensity
15
considerably more sensitive to ~tress
rllng'l, I1KI' than those r~portQd by Bllrsom.
2. There llPP~£lrQd to be no "i~;nificilnt diffQr<"ncp.~, in
either tha milterial properties or the :'ati'jlJe c r •• c k
CJrowth behilvior 01' the three heats of ste'i!l.
3. Dif~erQnces in fatigue behilvior between girdQr~ of
the Missouri test bridge were ~pparently the result
of difference~ in the sharpness of mech~nic~l flaws
rather than material properties.
4. Results from fatigue crack growth tests at varying
temperatures indic~te that fatigue crack growth ratA
is more likely a function of yield strength than of
fracture toughnes~. Thus, it may be that none of
the fracture toughness tests are suitable measures
of susceptibility to fatigue cracking.
S. The ASTM e-399 plane strain fracture toughness
is not a suitable test: for A-36 and similar
carbon bridge steels.
6.The data reduction method which best serves the
fatigue crack growth test ;s th. seven-point PJ}yno
mial method mentioned in ASTM E-647.
2.3 RECOMMENDATIONS
With the conclusions just mentioned in mind. the
following recom.end.tions for further work .re suggested.
1. Develop an automated system whereby crack growth
rat.s could be recorded systematically and consist
ently from t.st to t.st. With this. curve fitting
method could be employed and more definite stat.
menta concerning crack growth rates could be drawn.
2. Additional tests are need.d to determine whether
f.tigue crack initi.tion, like f~tigue-crack-growth
rate is unaffected by fra~tur. toughness. If this
i. in fact the case, then fr.cture toughness influ
ences only the length of the critical crack at
16
final fracture and rather large increases in frac
ture toughness would be required to significantly
increase the fatigue life of • structure.
3. Additional work is needed to clarify the effect. of
reversed .tress cycles on fatigue crack growth. In
cases where the crack closes during the compressive
part of the stress cycle. there is very little if
any change in the stress intensity. K%. during that
part of the cycle. Thus. if stress-intensity range
is the pri.ary factor in fatigue crack growth. the
effects of the negative portion of the stress cycle
.ust b. essentially zero.
17
CHAPTER 3 - MATERIAL PESCRIPTIO"
3,1 TEST SPECIMENS
The steel used in this investigation was ASTM A-36, the
type commonly used in hot-rolled shapes for bridges and
other steel structures, It was taken from the girders which
supported a highway bridge in southeast Missouri, The
girders were rolled from three different heats of steel. A
diagram of the heat numbers of the beams is shown in Figure
7, Section numbers shown in this diagram represent
locations on the bridge girders which were monitored for
cracks during the full scale testing, Beam pieces tested in
the lab were cut from sections 2, 4 and 6. A tabular repre
sentation relating the beams and their corresponning heat
numbers is shown in Teble 1, The chemical properties of
each heat are listed in Table 2.
Five different tests. as listed in Table 3. were
performed on .ach of the thr.e heats, Each of the test
specimens was stamped with a five digit identification code
consisting of the section number, the girder number, test
t~pe. and specimen number, The sppcimen locations are shown
in Figures a - 19,
3,2 TENSION TEST
Tension tests were conducted on AST" A-570 (7) speci
mens of the type shown in Figure 20 for each heat of steel.
Initial room temperature tests made in a 60,000 pound
universal hydraulic testing machine which had been adapted
to produce an analog electrical signal proportional to load,
Strain was .e.sured with an electro-mechanical exten.o.etar
and an auto•• tic stress strain plot was generated. These
te.t. were conducted at a strain rate which produced
18
West A~t:Irent
Girder1
Girder2
Girder4
lice
lice
pUce
Qlice
- East Pier
- west Pier
!:I /II , ~ ! II
I ; I I a I I I : II ~
, .! ~
: p
_I ( I J ! ~
• • J ~I • I ,I !...L 1+ •IT T s..,I
: I I I- • ~
..
~ c 0 ~(Xl co co co- ~ \D \D ~, , . ·('oj ..-l ....
IFco an 11".N "" l""I
.. I• ..L + ~~ T C;p· L~ ~ ~
co co co co~ 0". v ~- , . .. ·N .... N .......O('l l"'- CD 1lO('.I '" N N
I iu, -L u, + S·• , I ~
-" •
~ c: 0 ...CI) CI) co co~ \D \C ...· . . ·('oj ..-l .... N- co lI'l Lr, CDN "" l""I N, , .• u, l. :1-IT s
I • •,•
P d• • q
I- ~ • ~• • MI I
~K
• , II
Sectioo 7
section 5-
section 4
Section 3
section 1
section 2
Secticn 6
East.~t
Pigure 7 Bridge Layout and Heat Numbers
19
TABlE 1 HEAT NUMBERS
Swet j on No. liu.i2,1 282,ft84
2.2 351.630
2,3 351,630
2,4 282.484
'+ • 1 282.484
4,2 271.931
4,3 232,434
4.ft 282,ft84
6. 1 282,484
6,2 351,630
6,3 351.630
6,4 232,4&4
TABL E 2 CHEMICAL PROPERTIES P."cent
Hwcpt NR· 351, UO 271.981 282,4&4
Carbon .22 .23 .23
Aluminum <.01 <.01 <.01
Titanium <.01 <.01 <.01
Silicon .04 .0,. .04
Sulfur .020 .030 .019
Mangan.s. .64 .66 ,60
Phosphorus .012 .017 .014
Nick.l .05 .02 .02
Chromiull .06 .05 .04
P'lolybdenull .01 .01 .01
Coppar .11 .03 .03
Vanadiull <.01 <.01 <.01
Boron <.0005 <.0005 <.0005
TABLE 3 TEST SCHEDULE
TUt Code
A
B
C
E
F
Test Type
Tensile Te.t (A-370)
Ch.rpv (E-23)
Plain-Strain FractureToughn ••• CE-399)
Fatigue Crack GrowthT•• ts CE-647)
Dvnamic TRar CE-604)
20
I • ,CI. q
J
I I IEIO HI H2 E3 I I
I I C3. C~
..1 I I I I c
cs C6EOO E4 E5 E6 . I I
C7 C8
I 29" JSection 4,4Bottom FlangeHeat 282,484
Figure 8 Specimen Locations, 4,4 Bottom 1
Match Line i
N....
Match Line 2
Ai
Fl _!1 A3-AS I
t:--
- . ... ...
F5 F6.... ... ...
F7 Fa F9
...tch LineC;"'>
-----,1.l 24"
Section 4.4Bottom FlangeHeat 282,484
Figure 9 Specimen Locations, 4,4 Bottom 2NN
l,
7M:lteh Line :3
I
tSection 4.4Bottom FlangeHeat 282,484
~. 32"
I
A2 '1I
A4 Dl [)2- IA6 .. ..
/
> -.:
I ...A7
AS81-30 06
A9Match linec;
Figure 10 Spectmen Locations, 4,4 Bottom 3NW
~
<tHatch 3
D3 D4 DS
... ... ..
~p
... ... y
D7 D8 D9
1 36" lSection 4.4Bot tom Flang eHeat 282.484
Figure 11 Specimen Locations. 4.4 Bottom 4N-
II
E1 8"2 I E3 r E
I I JI II
II I , I
i
IE6 E7 \ B8 E9 E10
I
J 2~ _
Section 4.1Bottom FlangeHeat 282,484
Figure 12 Specimen Locations. 4,1 BottomNU1
D3
I I -, P I <4
---....E5 ! E6
D4
F9
1 3J" JSection 2,3Top FlangeHeat 351,680
Figure 13 Specimen Locat.Ions, 2 t 3 Top N0\
I AiFl B12-23 A2A
IA3
Dl A4
IC\ cr l{3LJ E2A5.&
U I". I A6
C4 IC5
I•D2
I I I 82-10 F3C6 Ctl "..
I..
827-30O~ I ~9 F2 F4
I
j 37" I!·t
Section 2.3Bottom FlangeHeat 351,680
Figure 14 Specimen Locations. 2.3 Bottom N~
• f2 Y E4iIE!
I IE5 E6 E7 £8
J 19" 1Section 6.2Bottom Flange~ut 351.680
Figure 15 Speci.nen IDcatioos, 6,2 Bottom Nco
I
I Er EL T E{ l./
I AIO
All
Al2
A13
1 21" 1Section 4.2ABottom FlangeHeat 271.981
Figure 16 Specimen lDcatioos. 4. 2A Belt tom
N~
B22-29
._.-
F5
D7
F6
F7
•
DB
- F8
F9
D9
J 2'" 1Section 4.2CTop FlangeHeat 271,981
Figure 17 Specimen I.Dcaticns, 4, 2C Topwo
IA5
D4 A6I rI _. __Al ________• AS
-----~".- .D5A9-_._---;>
-----. ---f----..--.--.... rD6F3I----
h.__• •
819-21 F4_.- -_. ---- - ._- ----~ --
Hatch Line""/
1 27" JSection 4,2BTop FlangeHeat 271,981
w....Figure 18 Specimen rncat.l..:.ls. 4. 2B Top 1
27"
F(Match tine
------- ----_._~-
812-14AlIA2' Dl
I [2
----A3 ....
El1--.."I'
-~IA4
D2 I ~•Bl-7 IEJ E4
DJ
B8-11 Fl
..Section 4.2'Top FlangeHeat 271,981
Figure 19 Specimen I.Dcatioos. 4,2B Top 2
wN
33
a loading rate of approxi.ately 20 k.i
el.stic region.
34
in the
It wa.
conducted in the servo-controlled electro-hydraulic testing
machine that was used for the d./dN tests. Low temperature
environ.ent was provided with the test apparatus described
in section ~.2 of this report. aecause of space limitations
in the cold box. strain wa. m•••ured with elastic resistance
strain gauge. and again an automatic stress-strain plot was
These tests were conducted under load control at
a loading rate of approximately 30 ksi per minute.
Re.ult. of these tests are shown in Figure 21.
Equation ~ .hown in the figure is from Barson and Rolfe and
shows the sa.e trend as the test result •.
17~.OOO
= (a~, + --------------------- - 27.~) (Eq.~)log (2+l010t)(t+~59)
where.
aYJ = .2X offset yield .trength at the temperatureand load rate indicated by T and t respectively,ksi
ay, = .2X offset yield strength at room temperatureand a load rise ti.e of 100 sec., ksi
T = .peci.en te.Perature. OF
t = load• ec.
3.3 CHARPY TESTS
ri.e ti.e fro••tart of load to fracture •
Charpy te.t. were run in accordance with AST" E-23.
The .peci.en. were cut fro. the flange. of the bridge
girder., twenty-.even fro. each of three heat •• at the
They were .achlned to thelocation••hown in Figure. '-lao
di.en.ton••hown tn Figure 22.
The .peci.en. were te.ted In a Tlntu. Ol.en Pendulum
Machine which wa. fir.t calibrated by te.ting a .et of
D. Heat No.
o 271,981
70~- o 282,484
0 6 351,680
0- Plot of Eq. 4
60·· \0 6YIELD 0STRENGTH
(ks i)
50~ ~O~
0
-b.
40-~ .~
~
I I t- 175 - 150 - lOa - 50 0 50 75
TEMpOF
Figure 21 Tensile Test ResultswU1
36
standa~diz.d speci.ens as specified by AST" E-23. Each heat
wa. te.t.d at te.pe~at~~e. yarying fro. -50° to 70°F. These
result. are p~e ••nted in FIgu~e 23.
3.' DyNA"IC TEARtTESTS
Dynamic rear te.t. were run in acco~dance with AST"
E-60~ (,). The specimen. we~e .achlned to the dimensions
shown in Figu~e 2~. They we~e cut fro. the flanges of the
bridge girder. in the location. shown in Fi~ur.s '-13.
Th. specimen. w.~. t •• ted on an "TS Ve~tlcal D~op
Weight rest "achin~. Spocimons wo~e tested at temperatu~es
yarying from -50°F to 7a oF. Tha result. are presented in
Figure 25.
3.5 E-399 TESTS
Twenty-.lx AS'" E-399 (II) specl ••n. were cut fro. the
girder flange. a. indicated In s.ction 3.1. Speci ••n thick
n.ss wa. the .axl.um thickne •• th.t could b. machined f~om
the girder fl.nge.. The r ••alnlng dl.en.lon. were mad. to
conform with the .peci.en thickne•••nd the AST" E-399 .pec
ific.tion for comp.ct tension sp.ci.en. (Figure 26). Starter
.lots were .illed .t~alght .cro •• and the .ide. of the SP.c
imen. were .urface ground.
Sp.ci ••ns were te.ted In. 100 kip s.rvo-cont~olled
el.ctro-hvd~.ulic t.sting .achin.. Howey.r. the 100 kip
lo.d c.ll wa. r.plac.d with a 10 kip load c.ll to incr••••
the pr.ci.lon of load ••••ur•••nt.. C~.ck op.ning was ••••
ured with a clip g.ug. fabric.ted to AST" E-399 .pecific.
tion.. Det.chabl. knife edge. w.~e po.itioned with • jig
and c •••nt.d to the specl ••n. with. cy.nocryl.t. c ••ent.
All sp.ci ••n. exc.pt 44Cl6 w.r.· p~ec~acked at roo.
te.pe~ature whil••peci.en ~~C16 and all .peci ••ns except
sp.ci.en 23Cl w.r. t •• t.d .t te.p.rature. b.low -51·F.
37
""~r D .~a
U)
t:Q)E-'
fNN
~ Ln ~.r-l\0r...~
~
.+1
N0
'f~0..-40
o 271,981 (5TrP 00
o 282,484 ~ 6-
80+ c: &.~ 351,6130 0
6-
0 6
60I 0ENERGY
~~ABSORBED[f t-Ib) 40 0o ~O
~r:fl6- 6.
20 + 6.0
O~~--fJ ~~ I I °1 I·50 ·25 0 25 50 75
T EM P of
Figure 23~V~otch Test Results
wQ)
39
0271,981 ~
+ 0282,484800
b. 351,680
IH
600
ENERGY I 0
ABSORBED(f t -I b) 400
I
20~a
6
riQ !
1), , I I50 25 0 25 50 75
TEM P of
J:'igure 25 Dynamic 't'ear Test Results•o
41
2 Holes.250+.002Dia. '"N '"l""I 0
+1o'"
1.25 + .01
Q.75" + •005
Thickne s s!ii~~_lof flange
r.15 min.~lf . r 450----""--------
]Precrack
Figure 26 ASTK £-399 Specimen
42
The low te~peratur. environment was produced in the cold box
used for the da/dN tests and dascribed in section 4.2.
Test results are shown in Figure 27 and Table 4. None
of the tests setis~ied all o~ the condition. for a valid Kxc
test. In general, require.ents for linear ela.tic behavior
(i.e. P••• /P. < 1.1) was •• tisfied only by those specimens
tested at te.perature. below -IODoF. Only speci.ens 44C3,
44C6 and 44C16 te.ted at teNperatures of -1&6°,
respectively, .atlsfied the conditions for plain
strain i.e., B>2.5(KG/.~.).
Although these two conditions could apparantly be
satisfied by tasting at suf~iciently law t ••peratures it was
virtually Impassible to simultaneously satisfy both these
requirements and the rQqu;re.ent that the maximum .trass
intensity during tha last 2.5 percent of precracking be Ie ••
than .6 <.v. pracracklng/.v. test) KG. Lowering the testing
temperature reduced the value of KG and increased the yiald
.trength at the testing temperature.
the permissible .aximu. stress intensity during the la.t 2.5
percent of precracking.
Although no formal .et of crack growth threshold tests
was conducted, observations during precracking
that the crack
approximately 10
growth threshold
ksiJTn. However fro. a
temperature was
practical .tand-
point it wa. very difficult to precrack at roam temperature
with .anual
ksiJr;. With
:ontrol and stress intensity less than 14
equipment for program.ed automatic continuous
load shedding, precracking stress intensity could be reduced
to approxi.ately 12 ksiJTn., but reducing the stress inten
sity below that level would ~apldly incre•• e the required
tl •• beyond practical ll.its. Even 12 ksiJTn. is signif
icantly higher than the 9 ksiJTn. which would b. the ••xi.u.
allowable for sp.ci ••ns t •• ted at a t.mperature of -200°F
wi~h a Ka valu. of 30 k.IJTn.
In order to rais. the allowable .tr••• Intensity during
precracking, specl ••n 44C1' w.s precracked at a t ••p.ratur.
5,-
:1
Heat No
o 271,981'
RSC
6 o 282,484
6. 351,680
0
2 ~.O~6.
8 00 0 0
1+ OO~ 0 ~6
I
. 200
I
-100,o
TEMP OF
100
..tAl
Figure 27 ASTH £-399 Results
TABLE 4 - ASTM E-399 TEST RESULTS ..... ...SPEC. S W PU- MAX TEST • .. ...
a Po MAX KO R • • .. ..
in. in. CRACK Kf TEMP. in. Be .. N .. \0kips P ksi . . . .
N .... .. ....TEMP. ksi deq F kips vrii'. . . . .deq P ..,-m. CD a'I r-- a'I
23C1 0.625 1.249 70 41.2 70 0.853 1.67 2.25 47.11 4.27 p F F F
23C2 0.625 1.254 70 33.0 -58 0.6951 2.30 3.28 37.90 2.07 T F F F
23C4 0.622 1.255 71 19.3 -195 0.7485 2.73 2.73 52.73 1.47 T T F F
23C5 0.623 1.202 70 15.0 -103 0.6422 2.81 2.81 44.33 1.53 T T T F
23C6 0.623 1.258 70 18.5 -135 0.7372 2.62 2.62 48.51 1.58 T T F F
23C7 0.623 1.256 69 14.3 -193 0.6625 2.70 2.70 40.68 1.03 F T F F
23C8 0.623 1.253 73 17.42 -148 0.7311 2.85 2.98 52.37 1. 72 T T F F
23C9 0.626 1.257 70 23.0 -112 0.6714 3.10 4.47 47.57 2.11 F F F F
42C2 0.610 1.253 70 30.0 -58 0.6563 3.16 '3.67 48.00 2.06 F F F F
42C3 0.609 1.257 78 17.2 -190 0.7207 1.97 1.97 35.37 1.04 T T F F
nC4 0.608 1.252 74 17.9 -160 0.7122 2.26 2.26 40.)6 1. 28 T T F F
42C5 0.610 1.254 11 36.2 -76 0.1365 2.50 3.00 47.59 2.25 T F F F
42C6 0.608 1.261 67 26.3 -166 0.6883 3.45 3.45 56.61 1.68 T T F F
nC1 0.606 1.255 15 20.1 -103 0.1691 2.83 3.18 59.91 2.10 T F T F
42C8 0.609 1.248 16 15.1 -130 0.6812 2.50 2.50 41.19 1.29 T T F F
42C10 0.592 1.260 11 33.2 -58 0.7008 2.91 3.41 50.85 2.28 T F F F
44C1 0.625 1.252 67 28.5 -58 0.6890 2.81 3.14 45.71 2.11 T F F F
44C2 0.626 1.253 70 32.8 -148 0.7111 2.97 2.97 51.23 1. 68 T T F F~
~
TABLE 4 tContinued)
44C3 0.623 1.252 71 18.1 -186 0.7247 1.90 1.90 34.34 0.98 T T F T
44C4 0.625 1.251 71 30.9 -112 0.6880 3.19 3.19 51.85 1. 84 F T F F
44C5 0.622 1.253 72 19.5 -197 0.7505 1.98 1.98 38.67 1.11 T T F F
44C6 0.623 1.253 72 18.6 -189 0.7358 1.88 1. 88 35.02 1.00 T T F T
44C7 0.622 1.253 73 11.3 -101 0.7421 2.62 2.62 49.86 1.91 T T T F
44CI 0.622 1.256 71 16 .8 -177 0.6674 2.95 2.95 45.17 1.18 F T F F
44C9 0.623 1.253 70 17.9 -189 0.7220 2.11 2.11 37.73 1.06 T T F F
44C16 0.601 1.199 -197 20.7 -207 0.6740 1.52 1.52 27.37 0.85 T T F T
.. T indicates specification is satisfied, and F indicates it is not satisfied.. Section 8.2.~ of ASTM E-399 defines the shape of the crack front for a valid test .
-- Section 9.1.2 of ASTM 2-399 requires that Pm xl PQ ~ 1.1-** Section 7.4.4 of ASTM E-399 require that Kf 8uring last 2.5'2precrack~O.6<~yl/~y2)KQ
**** Section 9.1. 6 of ASTM E- 399 requires that a & B ~ 2.5 <KQ/cry)
..,.U'I
46
of -193°F. This raised the MaxiMuM .llowable stress inten
sity during precracking to approxi.ately 13.5 ksiJTn.
However, the low teMPerature which approxi •• tely doubled the
yield stress also n.arlv doubled the crack growth threshold
level and the .iniMuM precrack stress
was 20 ksi!Tft.
Thus, it wa. concluded that with •••XiMUM thickness of
0.6 inches it is not possible to conduct a valid Kzc test on
this .aterial at any te.perature. Observations during
precracking of the.e speci.ens also sUQg.st that
fatigue-crack growth is .uch more closely associated with
yield strength than it i. with fracture toughness. The plot
of R•• shown in Figure 27 reveals no significant difference
betwe.n the.e three heats of steel.
CHAPTER 4.- FATIGUE CRACK GROWTH TESTS
The preliMinary version of ASY" E-647 used for this
work do •• not in .11 e •••• comply with the final v.rsion.
which was published .ubs.qu.nt to th.s. t.sts.
4.1 SPECIMEN DESIGN ANp PREPARATION
Crack growth t.sts w.r. conducted using Compact T.nsion
eCT), Wedge-Op.n-loading (WOl) sp.cim.ns. Flang.s w.r.
fl.m. cut from the web. and rectangular blocks were cut from
th.m with a bandsew. In Figures 9 - 18 the cutting petterns
.nd specimen orientation ar. shown for each flange eventual
ly used. No specimen was cut so as to be within 2" of any
he.t .ff.ct.d zone such e. e fleme cut or w.ld. This wa. to
.nsur. that the micro-structure. of all specimens were
essentially unalt.r.d. Th.se blocks were then machined and
ground to the di.ensions shown in Figure 23. Care wes taken
to ensure that the grinding process did not significantly
reduce the thickne.s of the speci.ens, but that it did leave
a ••ooth, well poli.hed surface. the grinding proce.s wa.
in the direction perpendicular to the line of crack growth
to aid the .icro.copic viewing of the crack.
The notch opening was eut perpendicular to the direc
tion in which the .teel wa. rolled during fabrication. This
wa. done to most clo.ely appro_i.ate the orientation of a
crack which could for. in a flange and propagate perpendicu
larly to the axial stress field. The speci.en. were sprayed
with. Krylon lacquer to prevent corrosion before te.ting.
4.2 TEST EOUIPMENT
2 Holes.750 +.002Dja.
--~- . --=----.....-.,
48
'"-o.+1oao
Thic.knes!>of flange
G)I
2.25:t .015 J-
Prec.rack
F1lun 211 .,dlI SpeCDen Deaip
49
electrohyd~aulic servocontrolled test machine was used to
load the fatigue crack growth specimens. Loading W~5
applied to the specimen through clevises designRd according
to ASTM E-647. Figure 29. The clevis.s were made of AISI
4340 st.el heat treat.d to a rockwell hardn.ss of C-40. Tho
position of the crack was measur.d with two Gaertner travol
ing microscope. mounted on miCrometer slide •• Figure 30.
To maintain a fixed low tempereture a plexigl.ss box
was constructed which would fit around the specimen and
clevi.es. Figures 31 and 32. The specimen was cooled by
blowing a temperature regulated gas, primarily nitrogen,
through the box.
The gas was blown through 1 1/2" diameter copper piping
which was installed with a throttle valve that forced a
certain portion of the gas through a dewar containing liquid
nitrogen. This kept the gas within a few degre.s of the
proper temperature. To fin. tune the system to the exact
temperature. a ••all heating element made of nichrome wire
was inst.lled in the flow and connected to a
thermo-controll.r. A ther.ocoupl. relay.d the temp.rature
of the gas to th_ thermo-controller. which cycled the he.t
ing ele.ent on and off •• n.eded. A s.cond thermocouple was
inserted in a hole in the .pecim.n to ••••ur. the temper
ature of the sp.ci ••n.
At the beginning of the cooli~g process the system wa.
circulating air. but as the liquid nitrogen boil.d off. the
t.st environment b.came primarily nitrogen. Every effort
w•••ade to k ••p the system airtight. as any moisture enter
ina the svste. condens.d causing ic. to collect in the
piping.
,,] TEST PRDCEDURES
Since the objectiYe of this .xperi.ent wa. to compare
the fatigue cr.ck growth rete. of the •• terial in the thr ••
h.at. of .t.el. the t •• ts were •• t UP with the ide. th.t .11
57
4,' DATA REDUCTION METHODS
The value. relating the crack tip growth rat ••• da/dH.
and the stress intensity rang., ~Kr, Must ~irst be derived
fro'" raw a vs,
fatigue craCk growth tests. AST" E-647 suggest. two method.
of reducing the data, the ••cant method and the s.ven point
polynomial .ethod, For this work, both method. were employed
and cOIlPared,
For both lIethods, the alternating .tre.. intensity
value AK% was calculated using Equation 6 (S),
where,
~IC% = ~p fea/w)CEq. 6)
fCa/w) = (O,2960Ca/w) - l,aSSCa/w)· + 6,557Ca/w)~-10,17Ca/w)· + 6,satCa/w)·) x 100 Cref. 3)
The fifth order polynomial in Equation 6, found in aarSOM
and Rolf., ;s a function of speci.en geo.etry,
Other COMPliance functions hav. been derived for this
specimen geo.etry and can be found in reference. 6, 11 and
lZ. Each arrive. at approximately the Sa•• value of ~K%.
The secant .ethod i. based on the •••u.ption that the
data point. lie pr.cisely on the .-N curve. The crack
growth rate i. derived using Equation 7, which yields the
slope of a straight lin•. connecting two con.ecutive point.,
If the data point. on the a-N curve are nUMbered a.,aa, , .• ,
aft' then the value of 'a' is equal to Ca, + a'.I)/Z t. u.ed
to calculate ~K%.
da/dN = ----------- ( Eq. 7)
Sa.ple calculations are shown In Table 5.
There I. a certain a.ount of .catter that exists in the
rew data which the secant .ethod a.pllfie.. The r.sulting
plot doe. not display the crack growth curve with .uch clar
ity. The .ethod do.s produco one da/dH vs. 6K, data point
for evory a-N data point after the fir.t. Thus. for a short
te.t. this .ethod would bo de.irablo.
The polyno.lal method utilizes a .econd order polvno.i
al equation to dorlve the relationship for da/dH vs. 6K%.
The .ethod u.e••even con.ecutlve data points to approxi.ate
the a-N curve with a polynomial. thus effectively ••oothlng
the .catter that exi.t. in the raw data. The original a-M
data are fitted to a curve as shown in Figure 34. The value
of a used in calculating 6K% i. arrived at using Equation 8.
( Eq. a)
where.
The value. b.. b •• and b. or. tho rogr••• lon para.otor.
d.tor.lned by the l.ast .quare••ethod over the range a,_" ~
a ~ 0'.... The value a Is the fl tted valu. of crack longth
at M,. T~. para.eter. C. = 1/2(",_" + N,.") and C. =1/2(N, ... - N,_") are u.ed to scale the Input data. thus
avoiding nu.erical dlfflcultie. in deter.inlng the
regre •• ion para.eter •• The rate of crackgrowth at N, I.
obtained fro. the derivative of Equation 7. a. shown In
Equat! on ••
a
a -----i-n
Figure 34 Seven Point Polynomial Method
f(x)
S9
60
TULE 5 SECANT I1ETHOD SAI1PLE CALCULATIONS
.. II a. d d./dN1. 00 100.000
.10 100.000 1.0h:1O-·1. 10 200.000
.05 ~o.ooo 1.25xlo-·1. 15 240,000
.05 30,000 1.67K10-·1. 20 270,000
.05 15,000 3.33xI0-·1.25 215.000
.10 20,000 5.00xlO-·1. 35 305.000
CEq. 9)
The v.lue of n used w.s 3. th.t is. 7 successive data points
were uti!tzed.
Th. d.t••r. reduc.d by .oving .Iong the a-H curv.
until th.re are only six point. left in the curve. D.t.
r.duction ends.t this point. thus d./dN yalues .r. not
cOMput.d for six of the points in the curye. three .t the
b.ginning. three .t the end.
The polyno.i.l w.s found to be far superior to the
s.c.nt •• thod bec.use it produced results which M.ke the a-H
curve .ppe.r to h.ve ••onotonic.lly incr•• sing first d.riv-
.tiye.
r.duc. the d.t. for this work. Figures 35 .nd 36 show the
cOMP,rison b.tw••n the two ••thods using H•• t 271,'11 .t
-50°F.
61
DELT A K, (M Pa J"rii )
-410
~~ (in/cycle)
30
••
o
40 5060
•
(mm/cvcte] 103
o 20 30 4 80
DEL T A K.t ksi ,/ffi)
Figure 35 Reduced Data for Heat 271.981 at -50°FUsing the Scc&nt ~ethod
62
DELTA K,(MPav'm)
-410 -
20I
~~ (in/cycle) (rnm/cycle) -3'-10
165_ 4
/ -104
,•
106_,••• '-105
•
o 30 ab 50 60
DEL T A K,( ksi \/Iii)
oFigure 36 Reduced Data for Heat 271,981 at -50 r
U.1Dg the polynomial Method
63
CHAPTER 5 - RESULTS AND PISCUSSION
Twenty-eight fatiguo crack growth test. were conducted.
The ra~ data were taken as previously described and reducod
to a moro usable form as da/dH vs. 6K%. Those results wore
thon plotted on a
Figuros 37-45. Th.
in tabular form.
log-log scalo and displayed as shown in
5.1 GENERAL OBSERVATIONS
It can be obsorved that the data
37-45 aro of tho sigmoidal It is
plainly s.en that at low values of 4K% the curve ris •• sh.r
ply with increasing 4K%. It is also apparert that at
certain values of 4Kx. thore is no crack growth. This is
the threshold value of 6K%. which yaried b.twe.n 22 and 24
ksi~. Beyond this tho cury. reaches a value of 6K% at
which tho da/dN vs. 4Kx relationship is linoar on a log-log
scal.. Thi. range was genorally botweon 2& and 31 ksi 1Tft.The third region. where rapid unstable growth
Thi. i. due in part to
i. not appar.nt from tho
the f.ct that the first two
loads were .hed w.ll b.for. the crack growth r.ached region
III. Only tho final constant load period wa. allowod to
entor the third region. However. no data could b. tak.n
during this .tage, because the .achine could not .aint.in
the full load cycle. Thus. it w.s impos.ible to determ;no
the value of the in.tability asymptot.. At 70°F. tho speci
.en failed by ductile te.ring. which could be observ.d but
not ••••ur.d. At both -50°F .nd OOF, tho .p.ci ••n fail.d by
fr.cture.
A line.r r.gr.s.ion mod.l w.. ..t up to obtain •
l.a.t-.quare. fit of tho lin •• r portion of tho curv ••• Sinc.
64
DE l TA K,(MPa./ffi)
-410
~~ (in/cycle)
30 40 50 60
(mmzcvcte) 103
••••
HEAT 282,484o
TEMP-50 F
o 20 30 4 80
DEL T A K.( ksi v'iil)
oFigure 37 da/cUl v. AItx for Heat 282,484 at -50 F
65
DE l TA K,(MPa.m;)
30I
40 50 60I I I
-410 -
~~ (in/cycle)
//-Cboo•o
(mm/cYcle) ..... 103
o
HEAT 282,484 ..... 165
TEMP 0°,
804b 50 60301Ci7-1- ,...--__---r__~-..,.___r--.,__..--.I
10
DEL T.A K. ( ks i J'ffi)
. 0Figurp 38 da/dN V8. ~l for Heat 282,484 at 0 F
66
DE L-TA K,(MPaJm)
-410 -
30I
40 50 60I , f 8p 100,
~~ (in/cycle)
•
[rnrn/cvct e)~103
HEAT 282,484 ~1C)5
TiM P 70°F
o 20 30 4b 50 60 80
DELT.A K,(ksi Jin}
Figure 39 da/dN vs. AKt for Heat 282,484 at lOoF
67
DELTA K.(MPaJm)
20I
30I
40 50 60 80 100I I I I I
-410 -
~~ (in/cycle) (mrn/cvcl e) __ 103
HEAT 351.680 -105
TEMP-50~
804b 50 SO30201(?4-------r---~--.,_-.___,--._-......
10
DELTA K,(ksi Jiil)
Figure 40 daldN va. ~Kt for Beat 351,680 at -50oF
68
DELT A K, (M Pa ./iii)
-410 -
20I
~~ (in/cycle)
30I
40 5060I I I
(mm/cycle) f-103
•••••
./'.••••e-o..
o
0.o
••HEAT 351,680
TEMP 0° F
20 3b 4b 50 60 80
DELTA K,(ksiJrn)
oFiguTe 41 da/dN ve. AK1
fOT Heat 3S1.680 at 0 F
69
DE LTA K,{MPaJiTl)
20I
30 40 5060 80 100
-410
~~ (in/cycle) (mrn/cvcte) 103
HEAT 351,680 1()5
TEMP 70°,
80430201(?-+------,.-----,---r--~__,r__-_._-......
10
DEL T A K,(ksi "'in)
Figure 42 da/dN VB. ~KI for Heat ·351,680 at 70°,
70
DELTA K.(MPaJm)
-410 -
30I
40 5060I I r
~N (in/cycle)
,•,
••
(mm/cycle) ~163
o 20
••
30
HEAT 271,981o
TEMP-50 F
4b 50 60
DELT A K. (ksi \/in)
oFigure 43 da/dN va. 6~ fot' Heat 271,981 at -50 F
71
DELTA K.(M Pa JiTi)
-410 -
30I
~~ (in/cycle) (mm/c ycle) ..... 103
o
I••
I•, HEAT 271,981
TEMP _OOF
o 20 4b 50 60 80
DELTA K.{ksi,,!ffi)
oFigure 44 da/dN VB. h~I fOT Heat 271,981 at 0 F
72
DE LTA K,(MPaJiTi)
-410
-510
20I
~~ (in/cycle)
30
•1.••••,
40 50 60
[mrn/cvc le l 103
HEAT 271,981
TEMP 70°,
o 20 30 4 50 60 80
oE ~T A K.( ksi v'ffi)
Figure 4S da/dN V8. AKI for Heat 271.981 at 70°F
somewhat between tests,
73
the
cu,.ves we,.e evaluated between the AKx value. which en com-
passed the linea,. po,.tion for each of the nine graphs.
this, an equation of the following form was det.rmined.
From
where,
da/dN = cCAKx)- CEq. 10)
c = intercept on th~ da/dN ax;. Clog AKx = 0, AKx = 1)of a line fittod on the lin.ar portion of thecurve.
- = .lope of the line
Th •• e ,.e.ult. ar. shown in Table 6.
S.Z EFFECT OF TEMPERATURE
It 1S gene,.allv accept.d fractur. mechanic. theory that
the critical str••• inten.ity value
rial's r.sistance to fractur., and the higher the value, the
tougher the materi.l. !n addition. as temperature
decre••es, the toughn••• also d.cr.8 •••. Charpy and Dvnamic
T.ar t.sts conduct.d for this work v.rifv this,
Figures 23 and 25.
Thi. would l •• d on. to beli.v. that as
d.cr •••• s .nd toughn.ss al~o dec,.e.s.s, that the crack
growth rat. would inc,..asing. Howev.r, the
r.sults ,f thes.
that the crack growth rat. actual Iv decrea5••• s temp.,.atur.
decr.as.5.
By plotting the .quations, .5 h•• b •• n don. tn Figures
it can b••••~ that both the v.lu. of the c"ack
growth r.t., da/dM, and the slope of the lin., or r.t. of
74
TABLE 6 LIHEAR REDUCTION RESUL TS
H.!tt..i Temp.rdur. fgultj on
282,tt8tt -50'F da/dH = 3.16 10- 1 1 AKr'·11
0° F da/dH = ft.ft5 10- 12 AK r 4 • ZZ
70' F da/dH = 5.03 10- 1 3 AK r 4 . • •
351,680 -50'F da/dH = 1. 62 10- 10 AK r:l • 1 1
0° F da/dH = 7. 94 10- 1 2 AK r' . , :I
70 0 F da/dH = 3.9a 10- 1 2 AKJ:4.ZI
271,981 -50°F da/dH = 3.9a 10- 1 1 AKJ:3.4'
OOF da/dH = 1. 7" 10- 1 2 AK:r4.47
70°F da/dH = 3.98 10-1:2 AK:r 4 • • •
75
-":. 1 _ ,
DE LTA K,(MPaJm)
20 30 40 50 60I
100
-410
~~ (in/cycle) [mrn/c vef e] 163
8050 60430201Cj1....... --.- --.-__,--_~___.,--~----I
10
DEL T A K. ( ks i Viii)
Figure 46, Results for Heat 282,484
76
DE LTA K,(MPaJrn)
20I
30 40I
-410
~~ (in/cycle)
700
00 (rnm/cvc le) 103
_500
8040 50 603020u:?-+------,.---~r_-__,_-._-.--__,_-~
10
DEL T A K.tksi v'in)
Figure 47 Results for Heat 351,680
77
DELTA K.(MPaJm)
20I
30 40 50 60 80 100, I
-410
~~ (in/cycle) [rnm/cvc l e] 103
8030107-+- ,..- -r--_-,-_-,-_-r-_---r_~
10
DEL T A K.(ksi v'iO)
Filure 48 Results for Ueat 271,981
is true fo,. .11 thr •• h•• ts.
71
Thus. whi 1.
failur•• ight occur.t • low.r .tr•• s int.nsity (1C~c:) a.
t ••p.ratur. d.c,. •••••• the ti •• to failu,.. i5 .ignificantly
long.,..
Thi. SUgg••ts that c,..ck growth r.t. i. not r.lated to
toughn •••• Chrok (13) .tat•• th.t cr.ek growth rate is
inste.d ,.elated to the yi.ld st,..ngth of the mat.rial. a.
indic.ted bv hi ••tat ••ent.
"Irwin (14) h•• shown that the .iz. of the localizedpla.tic zone .t the tip of a crack i. d;r.ctlv dependent upon the applied .tre.s int.nsitv-yield st,.ength,.atio quantity sClu.,..d. (KX/cry,,)2. In addition, it hasb••n shown (h.r.) and el ••where that the fatigue crackg,.owth rat. for a given m.t.ri.l incre.s.s a. thestress intensitv factor incr •• s.s (15.16.17,11>. Th.refor •• it is apparant that the fatigue cr.ck growth rat.incr.as•••• the pla.tic zone size increas•• , .ugg.sting that the ••chanis•• of fatigue crack beh.vio,. are,..l.t.d to crack tip pl.sticit~ consid.,..tions.-
Ten.ile t.st. eonducted on the bridge .peci ••ns 'ndi
c.t. that yi.ld strength does in fact Inc,. •••• with d.cr ••• -
ing temper.tu,..s.
aar.om & Rolfe.
This concurs with .quations shown by
wh.re,
17ft,OeO.yJ= C.v • + -------------------- - 27.4)log (2+101·~)(T+459)
CEq. 11 >
= O.2X offs.t yi.ld strength .t the t ••paraturaand load rat. indicat.d by T and tr.spectiv.ly, .si
= O.2~ offs.t yi.ld st,..ngth at roo. t.MP.ratur.and a load ri •• ti •• of 100 ••e., ksi
T = .p.ct ••n t ••p.ratur •• eF
t = load ri •• ti •• fro••tart of load to fractur ••••c.
Thu. crack growth rat. app.ars to b. ~ function 01 yield
str.ngth .n~ pla.tic zone rath.r than fractur. toughn ••••
7'
5.3 EFFECTS OF MATERIAL PROPERTIES
whether differences in crack growth rates in these three
heats of steel could be attributed to differences in other
material properties.
Comparing the results shown in Table 5 and plotted in
Figures 49-51, it appears that each heat exhibited similar
crack growth properties at each temperature. Thus, it
significant inappears that material differences were not
determining crack growth rates.
The chemical differences in the three heat. are minor.
From Table 2, the percentage of carbon content in heats
232,484 and 271, 981 is identical: .23X • Heat 351,680'.
carbon content is .lightly lower: .22". This hardly seems
significant, and there appear to be no other differences.
Toughness properties as determined by the Charpy tests and
Dynamic Tear tests also show no apparent differences.
5.4 EFFECT OF LOAD SHEDDING
During the course of each test.
load wa. reduced to comply with A51" E-647 and to prevent
the stress inten.ity from becoming so l.rge that it caused
excessive yielding at the crack tip. Loads were shed twice
per test. This proved .ignificant in analyzing tha re.ults.
As the crack grows, K%••• increases. which in turn
incr.ases the plastic zone in front of the crack. The slz.
of the plastic zone for plane .tre ,s can be determined by
Equation 12.
ICEq. 12)
80
DELTA K.(MPa.Jm)
20 30 40 50 60 80 100I
-410
~~ (in/cycle)
282,484
(mm/cvcle l 103351,680
271,981
8043020olil-+--------,r-----,----,r-----r-..,...---,.----
DELT A K, (ksi .,rrn)
Figure 49. Results at -5oPF
81
DELTA K.(MPaJm)
20I
30 40 50 60 80 100,
-410 282,484
~~ (in/cycle) (mrn/cvcte) 103
271 ,981
8043020107
-t- ---...----r-.......,..--r----,--10
DEL T A K.(ksi "'in)
Figure 50. Results at OaF
82
DELTA K,(MPaJm)
20 30 40 50 60 80 100I
-410
~N (in/cycle) (rnm/cvcte] 103
1C?-+-----....----r-----t--"""T"-.,----,--~o 20 30 4 50 60 80
DELT A K,(ksi.Jm}
Figure 51. Results at lOaF
83
In test 44E05, Kz ••• at the point of load shedding was 39
ksi JTn. the yield strength was 37 ksi.and the plastic zone,
rv. was .18". After load shedding. Kx••• was 26 ksi !Tn. and
the plastic zone SlZ8 should have been .08". At this point
large plastic strains around the crack tip just before load
shedding probably increased the yield strength in the ples
tic zone through strain hardening. This in turn reduced the
crack growth rat. until the outer fringe of the new plastic
zone had propagated to the fringe of the plastic zone
produced just before load shedding. This did not occur until
the crack had grown .08", K••• equalled 28.5 ksi ~. and ry
equalled .10".
This indicates that crack growth curves may be
distorted in the region below 28 ksi JTn and the actual
crack growth threshold may be lower than the 21 or 22 ksl
/Tn indicated. It was also observed during precracking of
the E-399 specimens that the threshold might actually be as
low as 10 or 12ksi JTn at room temperature.
REFERENCES
1. "issou~i Coop.~atiy. Highway Research P~og~... FinalRepo~t, "Fatigue Test of a Th~ ••-Span Composit. Highway8~idg.". UnlYe~sity of "i ••ou~i-Colu.bia, 1973.
2. Hoeppne~. D.W. and K~upp. W.E .• "P~.diction of Compon.ntLife by Application of Fatigue C~ack G~owth Knowl.dg.",Engin.ering Fractyr. Mechanici • Vol. 6. 1974. pp. 47-70.
3. Ba~som and Rolfe. E~actYr' and Fatiqye Cont~ol jn St~uctyr's • P~.ntice Hall. Inc .• 1977.
4. Pook. L.P •• Frost. H.E .• Ma~ch. K.J. Metll fatjgye. Cl&~
.ndon Pr ••s. Oxfo~c!. 197ft.
5. Campbell. J.E •• "Fatigue of High-St~e"gth Alloys at LowT.mp.~atur. - A Review", E,tj~U' ,nd Fraetyr. Touahnes,C~voa.nie Bthlyior • ASTM SPT 56.
6. Pari., P. and Erodogan. E.• "A C~itieal Anll-'Iis of C~ack
P~opagation Laws". Journal of '.'ie EDgjn •• rjna. Trlnsact; ons of the ASME, Vol. 85, 1963, pp. 528-534.
7. ASTM A370-77. "".chanlcal Te.ting of St •• l P~oducts".Part 10. AST" Standards. 1979, pp. 28-83.
8. ASTM E-23. "Hotched Bar Impact Testing of M.tallie Mlterial.", Part 10, AST" Standards, 1979, pp. 237-253.
9. ASTM E-60~. "Dyna.ic T,a~ Energy of M,tallie Mlterials".Part 10. ASTM Standards. 1979. pp. 6~5-653.
10. AST" E-399, "Plane-Strain Fracture Toughn.ss of Met.llieMaterials". Part 10. ~STM Standards, 1979. PP. 5~0-5'1.
11. AST" E-6~7-78T, "Con.tant-Load-Amplitude Fatigu. CrickGrowth Rat •• Abov. 10-· m/eyele". Part 10. ASTM Standards.1979. PP. 703-721.
lZ. We ••el. E.T •• "Stat. of the Art of the WOL Sp.ci.en forKxc Fractu~e Toughness 'I.tlng". Englneerjng Fr,etureM,ch,nic, • Vol. I, 1968, pp. 77-103.
13. Clark, W.G.. J~ .• Trout, H.E.. Jr.. "Influenc. ofTemperatur. and S.ction Size on Fatigu. Crack Growth B.hayior in Hi-"o-V Alloy St.el". Fractyre ",ehlnjcs.
WPla.tic Zone Hear a Crack and Fracture7th S,ve.gre Ordinanc. Mat,r. R.s. Cont.
1 5. E. T. We••• 1 , W• G• CIe " k and W. K • Wi 1 • 0 n. " Eng in•• r i n 9Method. for the D,.ign and Selection of "aterial. AgainstFrlctur., U.S. Ar.y Tank-AutOMotive Center Rep .• ContractHo. DA-3D-06'-AMC-602(T), ~~ ~o. 801005. (1966).
16. A.J. Brothers .nd S. YukawI,"Fatigue Crack Propag.tionin Low-Alloy Heat-Tre.t.d Steel,W J. '" Enanq. , ASME PiperHo. 66-M.t-ZClt66).
17. C.M. Car.an Ind J.M. K.tlin, wLow Cycle F.tigue CrackProp.g.tion Chlract,~i.tic. of High-Strength St,.ls". J. lalEngnq. , AS"E Pap.r Ho. 6'-Met-3 (1966).
WThe Fracture Mech.nics App~oach to1. tb '.Pallore ArMY ".tIC' Bu. Cpn.
18. P.C. P.ri ••F«I t i g u e W • ...p.,&c..l0'"c....' _ ....&.I..u..__ILII...LllL:IU-........a.Jr.:JII.K--JiJJl..LIu.;._-llULiiL&._~l£.U....._(1"3).
APPENDIX
as
FAT.GY~CRACK GMU.TH TEIT UAT.
S':'~C:a"~N hO. .at; ,j
.,.0.5•• INCHES _~.009 .NCtCS
TCIIPC'UlrURC 0 aeGRHI ,.
II. QII lUQIII 8li se 6 II
0.03.5 ~OOO. e.723 3•••g0 6.00 0.902 la200.O.lUI. 1000. ••922 3••321 6.00 0.899 19200.0.0119 • 000. ••259 2 ••1t4 • 4.30 0.914 2.J200.0.0139 • 000. &.1.2 2•••7• ".30 0.923 27200.0.0013 3000. 0.'125 25.0,e 4.30 0.925 ;'0200•0.0711 .OGGO. .J.52.· 26.320 ... 30 0 ••90 70200.0.0016 17.50. :'.;'02 21.a52 4.30 1.07. aaG50.0.050.1 7:100. 0.2.3 28.426 ••30 1.110 95550 •0.0.92 7000. 7.9a3 a9.7.1 4.a. 1.1•• 102550.0.G260 3i/:70. a.3GO 30••a6 ••28 1.192 105NO •0.G26G 300G. ct.196 31.00. ... aa 1.217 10aeao.0.G280 3000. 11....2 31 ••50 4.av l.a.3 llillao.0.oa75 ~OGG. 10.215 32.64' •• 29 1.2'2 u._o•0.G307 ,JOoo. 11.163 33.S.J5 ••2. 1.30.1 11 7BilO •0.036. 3000. 1~.tl92 3••131 ..2. 1.337 la"ct2o.0.0368 30.. 0. 1.;1:.0.5 36 •••n ••oJl 1 •.391 la.J82G •0.0431 30GO. 6 ••35 36.117 ..~I 1••00 12c._0.0.OlH9 30110. ..0•• oJl • .l3'1 ..31 1•• 18 12.a20.0.0032 22000. 1.113 22.'.5 2. itO I •• 'a lSI_a.0.0.5. 33000. 0.077 23.6"0 2 ••'1 I.SI. Ic. ••ao.0.010. 2••0G. 0.065 2••0.~ 2.50 1. saC. 211l!'20.0.04.0 100000. 1.110•• 26•• 39 2.50 1.6116 311620.0.0.52 30000. 3 • .1•• 270(.43 2.50 1.056 ~.Iwo.0.0500 12020. •• a75 29.'57 2.50 1.10»5 ;a5;a640.0.or7S 13000. 7.24. ;n .... 2.50 1.1... ~Oo"'h0.0513 5000. 7.to67 .12 ..... 2 •• It I.ItOf, 3716.0.0.056. .250. 1.9.0 ;a•••Co2 2.50 1.8.2 37:»"0.0.lIlU9 10000. .. ••SS 31.5'13 2.00 1.9iiiO HS"U.o.oa.o 2000. a.13. 32.'07 2.00 1•••2 ;,a7..0.0.0096 15;)0. 11.1 •• 3a.71S 2.0)0 1.052 "a"390.0.015\1 1500. 13••0. 33.537 2.00 I .... .100..0.0.011. 1300. UI.loI5 34• .1... 2.00 1.9•• 39~190.
0.0223 1300. 1a.'I03 35.611 a.oo 2.0G7 ;'9;'.90.O.O~" 13,)la. 2~.0•• 37.2:»0 2.00 ~.03. ;''''.7'10.o.oa.a I1GO. ot ... 1017 38••22 2.00 a. 0:i9 ;'9~1I90.
86
PAUGUE-CIIACJ( GII~.J" tESt O.tA
s!"f:C.jIleN "'0 • • 2': •
.-0.63$ 1NC:H&a .-,).032 .NC,..'."PEllA'''''E -50 DEGRUS "
QJ tilt IUglt IlIl. ge 6 tl
0.0211 3:'90. 3 •••3 3•• 71111 0.69 0 •••1 ZllOI o.0.0121 19Z0. 1.872 3•• 175 6 ••9 0 •••1 :tft930.0.0005 IV.2G. 0 ••36 23.1 •• •••0 0.900 ....50.0.0070 I a.u:o. 0.390 23.2•• •••0 0.907 •••70.0.00Ct3 22030. 0.3.9 23.375 4 ••0 0.916 ••700.0.0098 10060. 0 ••36 <13.416 •••0 0.919 90760.0.007. 22100. (hll91 23.S11 •••0 0.9ae 11dd60.0.00•• 2.JO.0. 0.913 "oJ. 71. ••40 0 ••39 1.a..o.0.02.7 a.3.0. 1 ••51' a4.121 •••0 O....lI 166t1eO.0.047. 25410. 2.152 a.... '. • ••0 IoPO. 192a.0.0.OZ47 10..00. a.31. 2S.33ft ..40 1.03. aoa••o.o.oa.,. 10'1100. Z.511 Zla.8li. ..40 1.0.1 a137Vo.o.oz.o 9280. 2.7.,7 2••343 •••• ••0_ :!:!.J070•0.0338 12t150. .s•••0 Z7.105 •••0 1.12.1 4!3:t920.0.027. 7S70. 3.:J4Z Z7.621 •••0 1.141 a4.J.90.o.oa., 7510. .. ••27 2•• 201 •••0 1.173 aSl000.0.0323 8110. ..0.7 28.911 •••0 I.aoa aS9Uo.0.oa72 7sao. ..610 29••sa •••0 l.a3. • ••630.0.03.3 7350. 5.069 30•••• • ••0 1.2•• a'''MO.0.03.0 la:loJO. 5.6.12 31.307 4 ••0 I •••• a'....o.0.0273 4530. 0.3.,3 3a.03. • ••0 1.325 <1..4010.0.0230 ••70. 7.3S0 32.930 •••0 1.356 a ....o.o.03a. 4000. • •••0 33.7a. 4.40 1.3.5 a9""0.0.0.1.15 3500. 9••a3 3•• 1..2 ••• 0 1•• 15 a"'.380.0.03.0 3500. 10.1191 35.9l.>3 •••0 I •••a a""..o.o.oa•• ~l»70. &1."20 30."". • •• oJ 1•••1 .so"••o.0.0317 aCtao. &1.il34 ~8.Z7. • ••0 1.51. .aOS100.0.0~72 2030. a.aoo 3•• IIIU 4••0 1.51. 101130.o • .a.a I~.O. 1.007 3••600 4 ••0 1.6•• .10.....o• .a•• .1••0. 1.00.3 ~•• ,J44 a ••o 1.5.0 30101.0.0.01.0 2li.'O. 1.3.6 ,s.o,a a ••o 1••1. .1.030•o.oa.s 1.600. ..721 .IS. 1&I a.oo &•••1 4.11..,0.O.OZI' 1kt.o. '.132 a•• I,9 1 ...0 I •••• ..1310.0.0206 II ;)00. 4&.e,,7 a•• ..,3l1 a ••o 1.68.1 .5aIlIO.o.o.uo 11320. Jl.041 al.913 a ••o 1.'13 •••130.o.o~.o 7020. ....... 211•••5 z ••o 1.7:1. .711.0.0.03il .370. 3.9•• a9.71t:; a ••o •• 7•• .,,,.ao.0.0230 ..."0. ..3.0 .I0.<lZ. a.eo 1.'14 ••••10•0.030. • 330. S.la. 31."• .1 a ••o I ••",s ."a740.0.oa.7 :a.Jeo. $.a02 .32•••1 a.oo I ..... •••1ao.0.OZ93 ...0. '.3•• 34••0. a.60 1••77 lioaooo.o.oaoo aloo. a.No 3••~. a ••o I .... 1..100.O.OZI. aMO. 5 •••~ 36.13. iI.OO 1.911 so...o.0.0.131 2170. ••a05 ~••I. a.60 1.9ao 10.UO.••UII u •••• " ••9 • JO .... a.oo I .... .ao....o.0.01" ..10. ...... 31.... 2.00 1•••.3 ..,..0.O.OZ•• ra••• ...... Ja .... a.o. il•• IO U7....
••03M ..... ••a •• 34.17• a.o. ...., ............. ••••• ••••7 ~••7'" a••• a ••7. ..01...
.....3 ••••• ....' 37••7• •••• ••u • ......••u ... .a•••• l.a.p. ....... .... ..,~. .,at.
Reproduced frolftbest Ivailabl. copy.
87
I'IiTIGUe-CAACK CORr••T.. TaST DIiTIi
5paCIM&N NO••2E.0
..0 ••04 I fIlCHES _.1.010 UtCH&S
TEII".. lljlTURE -SO DEaaaiS "Q6 11111 Q6DI Il& lie 6 Ii
0.0009 .70. ••a.s a~.'is.J '.30 0.900 ~"'070.
0.0053 27.(". ~.5~. Z'.ilOI ..30 0.9a. .lltSO.0.0065 ~a50. 2.003 2•• 2... '.30 0••20 .liOOO.0.0079 4000. a.I06 a••~~o • • .10 0.92. ••000.0.011. 5.50. a.a•• a •• 5.. ..30 0...0 5••S0.o.ola. 5650. .t •••5 2•• '90 ...... 0.9U &oaoo•0.01'1 5600. a .... a..... ..30 81.907 &5700.o.o.a. .010. .l ••ZJI as.a7. ..030 0 ••01 '0510.o.oa.o 'SOD. 3.09a 2••••9 '.JO 1.003 '1l090.0.oaa9 , •• O. .... ~ao a6.142 ••.JO ••oa, ••600.0.oa31 6570. 3.IH' 26.586 • ...0 •• 050 '1a070.o.OZOO 5940 •. .J ...u 27 ••a, .....0 a.o,a ..oao•1.019. sa20. 3••02 a'.6a.. 4.30 1.090 a03a30.0.01'9 • 610. '.0... 2'.4Ia .. • • .JO a.ao. 1077.0•0.009. 2...0. •• a29 2•• 0.12 '.30 a.aa. 11 0170•0.lIa20 5000. •.lit". a ••5a. ..30 •• a.o ...a70.o.oa.a 4a30. •• ".0 a ••M~ ••30 a.a59 .. 9300•o.oa •• 4000. lIo••aa 29•••S • • .10 I.aeo au~o.
0.oa9a Ja70. 5.7.a a ... "01 •• 30 l.a9• aa.570.0.01 •• 3a60. •• 0 •• JlO•.J.. ..30 ••117 .2'17030 •0.0211 3••0. ••237 30.M. .....0 a.23• a3..1a,0.0.011. 33.0. 6 ••57 3a ••". ..30 a.200 a3 ...0.o.oa.o 3.00. ....., 032•••7 •• 30 a.2•• a.03.0•0.oa03 3a",0. ,..- 32.'''0 .....0 a • .:I06 a• .I_o.0.0211 aoao. lI.a27 303.301 ..30 I.Jl20 a••aoo.o.oaao auo. 0.'1 • .1 ....OOot ••.10 a ....u •••7.0.0.02ao 2•• 0. ao •••• 34...Q ••30 a .... 'o a5laao.0.oa.7 a9liO. aa.a97 a.70. ..030 I ••oa· I•••~O.0.02al a '.0. a3.5S7 ..••••7 ••3. a ••Z3 ••••70•0.O..l2a a'.0. a••..,.7 .I7 •.JO. • •.JO a•••_ n,7MO.0.015" U50. a3••13 03•• 1•• ..03,) 1••7a a.9..0.o.oai. lZIlh ....ao 3a.a7. ..,JO a ..... ..0Uo•o.oal' la90. th2.a 39.U. ..30 a.500 aoaluo.0.0", 1330. 5 • .'1154 23..... a ••o a.6O. ..ot..o.0.0••• 3,JJO. a ••09 1••1" 1 ••0 ...a. 1••170.0.01 •• 01l10. it.oiI•• a•••• r a.oo a.53. a,a..o.o.oala ..00. a •••• as.070 a ••o •••S. Illl_O.0.0••7 7.40. ~.o.~ ilIa.c.•• a ••o 1••7. ..lMIIO.0.ltZ07 6770. ..... 27 a ••a07 •••0 1••9? a.".o•o.olao • 110. ~.7'• ~O.N. a ••o 1••19 a••~o.0.02a. 53••• ..aos a? ••a a. •• I .... a...o.0.033. 71000. .....a aa••• s a ••• 1.073 ........0.:32.'10 '.00. 5•••1 .O.SJ? •••• I .... II"••••...... 333•• ••0 .. M .... .... I.?a. ua••o •o...a. M.O. ..... 3 ...... .... a.? laOIO••...... ..... 7 • .11. .Ja ..... a ••• a.'" a....u ••...... U ••• ? ••.1 D ••a. I ••• 107M U .....I.". ~N•• 7.... ~..... a ... ...a. ......I ••, •• I.... ,.... ...... .... I .... g,....I.NN ..... •.0" M .... I." I .... ._.
88
89
'ATIGUE-CRACK CORO""" TEST DArA
SPECIMEN NO. 4ZE 9
B.0.6~0 IIoICHES ".:1.015 • NC"ES
'EMPt.RArUtiot. -50 OEGAU:; P'
lIa ..~ gaga» ~ Qe 6 III
0.oa20 16,000. 1.56.3 J.J. :t7e. 6.6. 0.793 1'42~0.
0.033. 21370. I,.~sa 3U.030 '.40 O.l1Jl ilSbOO.0.0109 6510. 1.154 39.96", 7.70 0.8:55 LOZII O.0.0600 II 31 o. 1.809 .0.470 7.70 0 •• 76 113420.0.0206 334.0. 1.,$b5 2•••.27 4.$0 0.92. 14b900.0.022a 22000. 1.495 2••834 4.!oO 0."53 16 ..»00.0.0150 .~1'0. 1••57 2'h908 4.511 0.961 171270.0.0221 10130. 2.114 25• .:105 4.50 0.980 1.7400.0.0.2.20 •••0. 2.~1. 25.6c1a 4.50 1.001 19111860.0.0231 10ZZO. 2.479 26.147 4.50 1.026 20e.080.0.0179 7500. 2.627 26.4V' 4.50 1.044 21,j580.0.02110 10"'30. .e.91$ 27.0«11 4.50 1.073 oil,z.510.0.0302 10;)00. 3.277 27.726 •• 50 1.103 2.34!lo10.0.0~09 11.90. ~ ...BI .elh370 4.50 1.132 oil4 ~OI)O.0.0260 0930. 4.oJ1I8 211.980 4.50 1.IS9 24~"'30.
0.0280 7170. 4.061 2"'.'03 ••:.0 1.189 257100.0.oall2 57ao. It.322 30.,j71 4.5,) l.al6 202UO.o.oa09 3ll10. 6.09.:1 ,j0.1l9. 4.50 le236 266630.0.0229 36GO. 6.72. 3h:a01 4.50 1.259 2702.0.1l.0a20 33.0. 7 • .:109 32.1.$ ••50 I.ZQ 273..0.0.0304 3400. 7.796 J2.... 4.10 le309 277060.0.0216 29JO. e •.I6" 33.575 4.50 I .~"" 27"990.o.o.~o 1620. •• 7~7 3.:1.9.1 ..50 1.:1•• 28..,10.o.o~u 3e.40. II.5IS 34.957 4.50 1 • .37. 2116••0.0.0271 2570•. 10.1131 3!h77. 4.50 1.4a.J 2.7820.0.0300 28~0. 1<1.1011 36..1.l6 4.50 1."35 2lfO.70.0.013. IIZO. 1:1.0"" 37.<iOjit 4.,.0 I •••• Z.17.0.0.0277 .l150. lit.1 ~I 3•••02 ••~o 1.4_ Z"'~940.
0.0••0 1750. v....5 3V.lfJ4 ••50 1.497 2....0.0.03•• 1820. ...100 0$11••.:101 4.50 •• 506 .l971UO.0.0306 15.:170. ,j.it.O 25.1 .. Z.7a 1.:507 31aS80.0."" 7770. 0:.0." it~.'03 2.70 1.5117 UO"SO.0.0240 10120. 2.5.1 20.J71 2.70 1••11 33.:1470.0.OZ3. VJ70. .l.7e9 27.10S 2.70 I."'" .1.3"'''0.0.0211 7it"0. ,).0)•• Z".7~4 2.70 &.655 ~47~.0.
0...09 6770. .1•••2 211.~dO 2.70 1.677 353UO.0.0240 7500. .."03 29.27. Z.70 1.10" .:1.13&0.0.0330 7330. ~ ••27 .JO.4:OZ 2.70 1.7.16 a ......0.0150 a5.0. •..501 .J0.9... 2.70 1.7.9 :l7IZ.0.0.0240 3750. 1.725 .J1.~'. 2.70 I. "'lo .175010.0.0...00 ,J.OO. ....56 33.~S.z 2.70 1.1107 37••10 •o.oau 2210. " ••07 3:1.""" a.10 1 ...22 .... Jo.&O.O.OZI. a200. 6.Z31 34.5:1. Z.70 1.-. 382..0.O.OZIO 9700. ,..IZ. tl7.Z22 2.00 1.87. ".2WO.•••.:1•• 53:a1. ..0.1 a•• , •• Z.OO I."'.~ .:1978&0 •••0a31 .7••• 7••51 29•••2 Z••O 1.....:1 ••~N••...... .1•••• ••••• .1••••• •••• I .... ............ ~... 12.... 31.9.4 ••0. 1 ..... .......0.0... ..... I ..... .13 ••7' ••0. , •• 019 ••••••
aeproduced frombest l"lil,bl. copy.
rA'.~YC-~R~K _ROW'" rell'-PATA
~pe~l~e" NQ. ale ~
..0.7001 • ..c... .-a.wa • ..cHE•
'E~PI!IlA'URE 10 I)eaua "U lltlI bUll Q& Ill! 6 III
O.OlllFl 10000. u.o•• .Ja.12:6 7.10 0.11011 IlOOO.O. 0'." 11100)0. :0."5. .J~.'15 7.10 0 ••61 22000.0.012' Jra o. '.MS ~1.7.' 7.10 0••7. a!i7'l0.0.0051 ~OOO. ••ao. ~'.I.JQ 5.08 0 .... a.,IO.0.020. la&OO. 1.'21 a••557 :6.05 0.9•• .1:S. o.0.01 •• • 4500. 1 • .165 ~4.15• s.o. 11.926 5S•• 0.11.01611 • 5500. 1 •••1 2S.G•• S.IIS 11.9.7 71:1.0.0.01 •• • 000. .....7 015.",,0 5._ 0.95• .001.11•11.11.21 ••a.o. a.967 016.049 5.0S •• 000 ..HO.0.0.7:S 6000. .J.5Z. 26.;'.' ..... 1.0.7 10.590•O.GaI' &000. •• 110 IO.II~1 5.05 1.0.0 110_11.0.0270 6000. '.705 27 • .101 5.0S I.MS II.HO.O.OZ•• 6000. 5.oJ71 aa.017 5.0S ..096 12a590.0.022. 3700. !i.7.0 ilia.47' 5.0:6 1.116 1262911•0.02•• .1>00. 6.a1O a9.0as 5.05 • • 140 l.Joa90.0.0.J.l3 5000. 6 ••91 019.160. 5.05 •• 172 1...2911 •1I.IIZ7. .000. 7 ••92 :SO.SOI 5.0. •• 0100 .19290•0.0270 ~5all. •• .13. II.UI s.n ••za. 161••0.0.oa7. 3300. ..0.0 31.9'. 5.0:6 ••1:.6 160UO•1I.0a.4 .1000. • 0.00. la.7•• 5.0• 1.2M ••9UO.0.0171 a700. .0.903 .J3.173 1.05 1.3.1 15••10.0.oa.9 1600. II •••• .1...... 5.0. I ....... 1:04a.0.0.oa.3 aloo. • a.'la 35.115 5.0.. a • .J66 1..... 0.0.015. laoo. loJ.oJ... IS.7a. ••0. l.oJ.l .5'.10•0.oa.3 1100. ...... 3li.JI. •• 06 ••3., 1.... 0•o.oa06 ."00. II•••• •" •• 1" s.o• • ••ao ••ao.o.o.o.SS laoo. 0.0.3 17.07a •• Oli ..eZI 1••alO.o.oz.a .allo. 0 ....5 "7••0~ ••os 1.430 l.a••o.0.0001 lS00. 0.0•• 11.050 1.9. 1•••0 1.9.. 0.o.ooJal la...o. 0.'" al..... a ••• I .... a • .JHo.o ....oe oJo••o. 0.951 21.79. a.96 &oUI 311690.0.01 •• .,300. 1 ••07 2•••6. a.91 ~.5H .J60990.0.0.17 16liOO. •••09 a ••07. a.93 • ...0 3.7.90.o.oa•• aOlloo. a ••91 ~••I" a.91 ...., 171••0 •0.0271 10300. 1 ••7. a6.10r 1.93 1••11 1.7790.O.Olal .SOO. ••••1 ar.026 a.91 1.....1 19• .190.O.O.OJ • 000. 6 ••14 a ••I •• 1.91 I .... .0•••0.0.01•• sooo. 7.0•• I ••UI a ••oJ •• 711 .09&90.0.037. SOOO. •••31 JO ••I. a." I. rso .1...0.o.oau 1.00. •• 1•• .JI .... ..... ..770 •• ,&90•o.oa.1 1000. 7.r36 1...Il. 1••3 •••0' ••01.0.0.0171 1000. 7••1 .J6.119 a.loJ a.'M .a~o.
O.Nao .00•• •••71 1....7 1••0 1..... •••190.0•••a9 .so•• ...... a7.... a • .Io 1 ••79 4oJ,790....... ...... .I.a... ar ..... 1.1• 10 ... .a.r........, I •••• ......1 a7.... •• IV 1••vl ....,...o.... r I .... ••ua ...... ••a• • 1 ...1 ...,...••O.la u ••• ...., a..... I.ao •••a.l ....060•...... H" • ..... ...,.. a... lo9.J.J ..7....
90
~AIIGUe-CRACK ~.I" TESI DAIA
a".'IIIIIH NO. 231 5
..0.70S • He". _3.00S INCHEi
TIIIPEIIAT",.E 0 DE....EES ..
~ Qil ilAQtIl WI. Qe A ~
0.0132 11000. 3.033 a3.90~ S.OS o ••all 36780.0.01l19 2S000. 1.710 ~4.$44 !:io.O$ 0.92S 61780.0.0203 172.10. 2.0•• 2•• lI46 !:io.05 0.'14. 79000.0.0322 15000. 2.a•• 25•• 12 5.0$ 0.977 94000.0.03.311 1I.J00. .3•• 111 26.1>13 5.0)$ 1.009 10$:100.0.0527 12dOO. ..231 26.li'a. 5.05 1.059 JJltlOO.0.072. ISOOO. 5.339 2e.50D 5.0S 1.1.19 133100.0.0.... 10000. 0.230 29.829 5.05 • .185 1.~IOO.
0.0• .39 lilOOO. '.36. 31.47. 5.05 1.249 183100.0.0.09 10000. ...51. 34.001 1l.05 1.0337 163100 •0.04611 :.000. 5 .... 7 .35.00r 5.05 1.3'0 1••100.0.0515 5000. 3 •••• .35.00" Ii.O!» 1• .170 173100.O.lUll' 30oaOO. 1.195 21.43. 2.-I.J 1••21t 20:1100.0.0060 11910. 0.$7. 21.:.05 2.9.1 1••32 21~010.
0.0113 42920. 0.2•• 2&.7,s, 2.93 1•••3 257931J.0.004.3 31500. 0 • .32a 21._.1 2.9'" 1•••9 1I894.J0.o.ol.a 270ao. 0.fo511 22.07Z 2.93 1••59 :11••50.0.00.' 26.50. 0 •••• 22 • .;1•• 2.'13 1.473 ...<E900.1l.01IM 211eo. I.S02 22.". 2.93 1.492 3.4080.11.029. • 5000. 2.03. 23.262 2.9.1 1.513 .3''''060•ll.OUIS 13000. 2 ....2 23.94. 2.93 I.M2 .392060.0.052. 11380. 2.M7 2•• '~tl. 2.9.1 1.57,'J .o~••o.0.0209 10200. 1.1171 2S•• '''' Z.9.1 1.600 .1.10.0.0.007. 63ao. 2.166 25.7'7 2."'''' 1 •• '0 .ld040.
Iteproduced frombest Ivailable copy.
91
'ATIGUE-CRACK GRO.TH 'eST DATA
s ..eC • .e6N hU. z.Je •
..O.TOI lNC..- • _a.9•• lNC..-.
,."PEIi,.TURE • OiOGaUS ,.
gj QlII Q6QI H lie 6 It
Q.oa~3 2220. ••09' 33 ••87 7. '0 0.173 29220.Q.oa76 Z~2S0. a.I.' "....... s.os 0.9.0 5...70.0.0353 21830. 2.S0' 25.327 s.o. 0 ••6. 80300.O.O<tllT 11 ••0. 3.184 25.905 s ••• 1.001 921.0.O.O.~ 11500. ••1.' 26.633 ••0. 1.03. 103..0 •0.0••5 10000. •••7. "7.60. li.05 1.082 , '3680 •0.0277 5000. 5.111 ZI.191 s.os 1.101 &1"'0.0.0... 5000. li.IOI • ••79. .... 1.135 '&36e0.0.0218 5000. ••••• Z9.4.1 5.05 I ••~ la8..0.O.UO. 5000. 1.1.' .:10.1£60 s.os 1.195 1""..0.0...» 5000. 7.'16. 3 ••236 s.OS 1.233 13.680.o.o~•• .000. 8 ••1'7 3Z.loS2 5.04 I.Z68 l.a....0.0194 3000. 9.15. .:12.'13. 5.05 l.a9. 1.5••0.0.032. .:Isoo. 9••3. 33••;). $.OS 1.3a. 1.'I.aO.0.0368 • 000. 11.,).5 3:i.03• S.OS •• 363 HUIOO.0..... ...50. ' .... 76 3_.$40 5 ••• 1••&' '51'0..0.••031. IISO. 10• .14. 37.1'a• ..0. 1•••6 1591.0.0.02.2 1540. ...,). 37.... 5.05 &•••6 '607ao•0.02:10 loS70. ••••• 3••a31 ..05 1.456 1.a090.0.01." "'''50O. 0 ..... &.1.3a7 &..... &•••1' '.0••0.0.00.0 19550. 0 ••1'9 &3.637 &••0 1.'10 ZOOI•••O.OOS. .0.10. 0 ••6' &.1•••6 a ... Ie,al ",Ja..o.0.0109 .117 •• 0.a.3 a ••oa8 a ... 1.1IaO • ••120.0.00741 z.ooo. 1.40.1 a ••2ge a ••• 1.=54,) 21'.&ZO.0.0112 .1S90. I. PI. a4.7• .1 a ••• I .... a89710.0.01176 ••000. ..0•• ~7••9a a.90 1.6S. 3a.71O.0....7 10000. S •••l1 • '.Oso a ••• 1.0.7 33'1710•0.01.7 5000. 7 .... 29.71. a ••z 1.7a8 34.7&0.0.04.1 .000. ••411 JO.877 a ••a 1.7.7 3••7'0.o.oau "0.0. 'II •••• .u •••• a.92 1.77a 350710.0••• 07 2000. .....37 3a.s•• a••• 1.798 :SS27l o.O.'~.II ~.,OO. " •••a 3J.7•• a.92 I..Z. 355710.0.oa7. aooo. •••07 3••li.1 • ...a I .... 35'710.0...01 10000. ••Z.9 3a.~01 a.4. • ••22 367710•0.0:136 31••• II.a•• $3.770 a.4. ' ••47 37....0.0.OIa6 10.0. loa.,;,... .J4 • .II1;' •••• 1••58 .11'1.0.0 ••1.0 IO~O. I •••al 3•• 071 2 ••• 1.972 312.0.CI.ClUtO 1000. Ht.'O. .15.9&. a••• ..9. ~7.JaO•0 ••16. 1000. 17.1'" 36••'" a.4. 2.003 374.0.0.017. • 000. ,,,.00. J7.9a.1 a ••• a.oao J'~.O•0.01 •• 10100. &1.08. , ••17. a ••• a.M. 31'••0.o.o.a.l '000. U ••70 .0._7 2.44 a.o•• .177.0.0.oa.9 ,.,00. z...".o • a • .I3:1 a ••• z.o•• J7••0•
92
·PAIIGUE-CRACK GAD.IH TEST DAIA
SPt!C. MIN NO. 62.. 1
eaO.7a5 • NC....S ....... 000 INCHES
lEOlPERArUAe -SO a.loRas "
Q6 Wf g6Q!l ~ De ! III
0.00.. 3 1112 o. .1.001 23. 1Iv.l 5.U 0.813 .91.0.0.o)a31 22270. 2.013 1 •• :>9. 5.23 0.915 11.10.0.0~01 111290. 2.I<;a 2••9.1. 5.23 0.93. 1101700.0.031., 123.0. 2.31' 25••51 5.23 0.9_ 102040.0.OiU5 11000. 2 •• 30 25.aS6 5.2.1 0.9all UOo.o.0.023. 10000. 2.31. 26.397 5.a3 1.017 120040.o. l217 10000. 1.9tH 2•• '2. s.a3 1.03. 1300.0.0.01 •• 7.50. 1.796 27 •• 0. 5.13 •• 052 137..0.0.01 • .3 1<1000. 1.....1 27.450 5.a3 1.069 1.9..0.0.0150 uo~o. 1.727 27.7.7 5.23 1.0•• 161••0.o.oaoo 11.120. 2 •• 36 .l•• 3•• 5.a3 1.110 177210.0.0323 II ;Jao. 3.3.9 Z••974 5.13 1 •• 37 111.2.10•0.0::'.0 10il!.0. •••95 29.870 5 • .113 1.175 19.510.0.0.1.5 1100. 5.410 30.7.3 5.13 ..211 100010.0.02•• .720. 5.'•• 31 ••72 5.2.1 I.Z37 210730.0.0.10. ...ao. Co •••• 3Z.293 ~.a3 1.267 215550.0.0150 2.190. 7.-,sa 32.709 5.23 1.2.Z 217940.0.0211 sooo. ••90'" 33••06 5.23 1.3ao 112940.0.0..... 4030. 11.0.3 3...W.... 5.2.1 1.357 226970.0.027. 2720. 11.06. 35.96.. 5.23 1.389 2a"'090.0.02.11 1170. 1.1.90. 3«>.73_ 5 • .13 I ••• a 23&460 •0.0250 11110. 13.229 37.0.9 ••23 1 ....3 133Z.0•0.022ft 2.130. •• 729 .1•• 0119 5.2-' •••50 235570.4.0523 16.0. 2 • .1.. 9 31•• 7.. 5.23 1 ••60 237Z.0.0.;1",•• .0000. • •••1 23.796 .1.0.1 1.526 21'250.0.0 •• , 2S,),)0. 1.7Z. a ..... I 3.03 1.561 30Z150.0.041.2 20000. a • .I.2 25.6;19 3.03 1.5"" 322250.0.0=0.1. 23"'60. 3.990 27.5.2 3.03 1•••2 3....110.0.0.171 lu70. ~.li4a 111.750 3.0a &••98 3....0.0.03•• so~o. ...,.. 29.632 3.0.1 •• 723 359..0 •O.O~.O :.000. •• 0.2 J11.01~ 3.03 1.760 .J6.....0 •0.0435 s~oo. '.332 32.d04 3.03 1 ••01 3.....0.O.OIU 2000. 6.332 33.5;U 3.03 1 •••9 37...0.0.11101 1000. 'h iIt 7. J13.~39 3.03 1. _10 372....0.0.00•• JOOO. •• 09. a•••• , I ••~ 1••.11 ..75..0 •0.0371 92.0. 0 • .117 30••~0 a.53 ••••0 3.S130.0.0••• 7CoOO. 1.1.110 34 ••10 2 ••~ 1.961 392730.0.oa.2 I~OG. 15.9... 36.G•• 2.5.1 1.99. 3".730.0.0.2. 2000. 1••050 30.0•• 2 .... 2.02. 396730.
Reproduced frombesl availabl. copy.
93
~ATIGuE-C.ACK GRO.'~ ,a.T 0"1'''
S~.C lieN NO. I~E 6
..0.7015 INCHES _~.00. INCte.
' ••NR"'UM a 01:....... ~
ga .. RAg, a • 6 Cl
0.01:S- 10260. 1.866 32.80- '.09 0.044 30,,.0.0.0101 '0000. I.' 09 ;'1.5.903 15.015 0.8.3 491500.0.01'6 '0000. 1.125 1••.z.9 15.015 0.1l06 .'560.O.O~" ~0'00. 1•• 01 1••72a 5.0' 0.'30 .'660.0.0302 186.0. a.40. 2s••ao 15.01' a ••" '06.1Z0.0.0.0' 12870. .a•••• 2•• 016• 5.07 1.0OS 11"190.0.0.. 31 10000. 3 ••01 2••IUl 5.0. 1.03. lall'.O.0.01" .000. '.11' 21'.30. ••0. '.01' '''.''0.~.oa., ~OOO. 11.327 21'.'" S.D. 1.092 1...190.0.0••, 5000. ...003 aa.3" .... 1.lao ' •• '90.0.022. 5000. .. ••3. 29.1toll 5.05 1•• 56 .531.0.0.~3.7 5000. '.200 29."1'7 ..0. 1.190 '114"'0.0...01 sooo. ,.,.. .10 ••01 la.O. , .1i!4 ' ....90.0.0399 SOOO. ••••• 3a.o~:. 5.0. 1.2lt6 1001.0.0.0213 2500. 9.117 32.659 5.0. ,.a•• 1'0.",0.0.0115 i!SOO. ... 710 "3.2.~ 5.0. '.311 1'...90.0.02.0 2500. 10.... 3~ •• '0 5.0S 1• .;13. 11'5..0.0.oa.7 2.00. II ••H 3•• ",.1 5.05 1.3.3 .,.190.o.on. a.oo. 11.11. 3•••10 ..0. I ....' 11106•••0.033. 2••0. 4••16 36.0911 5.0. I ••O~ 1.3ZTCh0.0183 1200. I.a.l. 38 •.166 11.05 1••11 1•••70.0.0371 saa. o. 0.522 22."'i 2 ..... 1.4.1 2.a680.0.00•• 20000. 0.32a 22.... 2 ... I ...... a.a....0.0009 1• .1:30. 0.300 22 •••0 a ... I .... 2.1....0.0005 llUUO. 0.311 aa ••loa 2.'. '.4". 300••0.0.00.0 20:300. 0•••7 .13.0.7 2.9e. 1••41. 320MO.IhOla. 20000. 0•••3 23.a90 ~... •• 1503 34MifO.0.01.' aoooo. 1.~.1 23.'3a a.96 '.522 S.M.O.0.02.0 10000. .z.o•• a'.'03 a.V#> 1.5•• 3aD..0.0.0•• 2.000. 3•• 11 a•• 1.17 2.96 1••1. .06••0.0.OS.5 10000. 4.0.a 27.171 2 • .,.
I ••'. .1••90.0.0••7 10000. ..766 a •• o.. a.90 1....3 .2•••0.0.0109 1••0. $.0.. a ...... 2.9.1 1.'01 .a~70.
0.03• ., • "0. •• a •• 30.Ii.JII a.",s I • .,.'" .3'3.. 0 •O.O.SI • ODO. 1 ••6' 31.35.. 2.P~ 1.770 "I~O•0.0~37 .000. 9••75 .12.7... 2.M I .... • ......0.o.ol.a :1000. .,.30a 33.0... a ••• 1••3. • • .aUO.o.oass aooo. '1.0'. 3•• 353 a ••, I .... ..0UO.o.oa•• 1000. 9.2•• 3....... a ••, 1 ••'9 '."UO.O.O~'. !II"'OO. , •• O. "I. '01 a ••• 1."1. .IU.:IO.
94
~.JI~UE-C••CK ~R~.r" rEST o.r.
5peCl ..e~ ~a • ••E •
..0 .... INC... ••2 • .,,,. IMetCS
JEMPeR.tURE '0 DECiIlIEES ~
g4 IItI Q6Uli ~ lie l "0.0la51 :i000. 5.331 3•• liO. 6.00 0.V3" 216020.0.01•• • 300. •• Z8. 25• .57• 4 • .10 0.960 36.5Z0 •0.030_ 20000. it • .-o' 2••21!t 4 • .10 1.00. !t63'l0.0.oa64 20000. it •••6 26.V19 4.30 l.o-a '6:'20.o.ooao a4.00. 4 ••• ' 28.90. ••.:11 1.1:.0 100920.0.0121 3600. $.947 29.1"0 4.:U 1.142 10.520.0.004. 10000. ' ••3. .10.5.- 4.aa 1.20' 114NO.0.0.0. 5000. 9.0.7 31.". 4.30 I.Z•• ll"NO.o.o.r. 5000. 10.150 33.101 ••..10 l.a.. la.NO.0.0406 .1600. lZ.i1190 "4.2'oi '.:'0 1.333 laalitO.O.o.H 4000. 11.004 35.11'''' 4.27 1.39a 1.-,U20.O.OSOO .USO. 10. '90 3,..9'S ••2. 1.429 l,saa70.0.0561 3300. 5.:'70 ~'.~Ol '.Z. 1.43" 13In.70.0.OQfo3 61010. .£.013 ll.S7I 2••0
1.__14••'0.
0.01 •• 30000. 0.9a6 23.5100 2.51 1.50. 1,..'0.0.011il7 31000. 0.5.3 23.0•• 2.10 I.N3 aOla67••0.00.1 12000. 0.~75 2.1.506 2.4,. 1.IU3 217.70.0.12•• IS.liSO. 4.03. .10.004 2.50 1.729 :'7.220.0.U,7 aoooo. 7.100 .1&••711 a ••• I." 3...,zaO.0.la21 10000. 1.6'1 3••130 a ••o 1.... '06zaO.0.0.4. 7aso. ....al 32.'.1 Z.OO 1.... .1,s.70•0.01.3 &000. 7 ••30 033.... a.oo ' ••'1 .llIi.70.0.0115 1000. 1.l.IO. 33.~ Z.OO I ••'. .'6.70.0.01.' 1000. 13.a.S 3 ••••• a.oo 1•••• .17.70.0.013' 1000. 1•••11 350370 z.oo z.ooz 41.470.O.Ola. 1000. 1•• V50 .s••&017 a.oo it.OI' 4''''70.0.0173 1000. ,..... "7.a'.- 2.00 it.OM 4aO.70.0.011' liOO. ZO.09. 37...... a.oo z.o-. 420"70.o.Ola. !i00. .10.4 ,. .1•••0' 2.00 Z.OM UI.70•0.009. 500. 20.971 39.3a, Z.OO Z.067 411 "'0.0.00•• ;JOO. aO.006 '-'.It.1 1 ••• z.or, 4az.,o.o.oalO 1000. &9••1' 3•• &09 I ••' a.ova 4&...70.0.0110 1000. •••••• 5ItoO.' 1 ••0 z.~ .iIl••70.
Reproduced frombesl a..,ail.ble copy.
9S
PA'IG~-~~_~. ~U.," ,••, DATA
IPe~I"~ ~. • •••
• -0.11.' INC... .-a.v.3 INCHIU
JUIPEllnUIIE '0 PlaR"S P
D6 .. WAQCII lK III! l ..0.02.1 5000. d••8. 32.0Z0 6.00 0.'92 11000.0.0.1'. ~~r ,,_ 1.282 .1•••9$ 6.00 0.021 a6000 •0.007. ••ro. e.r'2 32 •••7 ••00 0 ••'1 I,_ro•0.0.» 5000. 5.'03 33• .135 6.00 0 ...7 22_ro.0.0.1. .1Ii00. ..003 33.'0.1 6.00 0 •••• 26V'0.0.01'77 ISOOO. a.a9. 24.73. '.30 o••aa 6a.ro.o.o.a. .11000. I.:S•• 25••00 ••30 0 ••71 '''Sl70•o.o••a 20000. 1•••7 25••79 ••30 0•••• 9.070.0.0310 30000. a.311 a6.811 ••30 1.036 laa970.O.OZ •• 113l10. a.V96 27.156 6 • .s0 1.053 1.1.3&0.0.... aoooo. ••••• • ••06.1 4.30 1.laa H.....O.0.0••• 12600. S.'61 30.152 6•.n 1•••• ICIICIINO.0 ..... 0000. .."S %, ••lfll ••3a l.a.lO 11••ao.0.0.13_ 50,)0. 1.011 3a.16. '.ao l.a6. I,..,.ao.O.OS156 ••60. ..V6a 33• .309 '.30 1.'00 .0.11110•D.O••• 5~OO. 10.'3' ....,. 4.32 1.3•• 1• .".,0.0."'. 5000. 10•••7 .1,.". 6.:a1 1.6" 19••70•0."'0 uoo. 3 ••.32 37.0.1' 6.31 ••••• a...070.0 ..... 3100. a .... 37.7.. 6.31 1.63. aOll'o.O.H... 1.10000. 0.7aa a••633 a.so a.S.3 331170.0.011. 600a•• 0.977 as.a,. a.5O 1.57. 3,. .70.0.00•• a.oo •• ...~~ a..... a.s. a.59. ~'I1'O.O.OIU7 _0••0. a •••• 1".;'.0 1.50 1.6.0 6.1.170.0.H6. 100••• • ••0' .1..a9. a.so 1.'0. • ••• .,0.O.llS. 10.0•• 5.,..,. 33.'9a a.s. a ••_ .r • .,o.0.0••• 500G. 5 •••• ;a•• '#4,a a ••2 • ••sr .7•• 70.0.0... ..00. ..a•• 30•• '" 1.0" ...... • ••a,o.1l.01U 0.00. 7.9.' .1.t.5.3. l.oJ.. I •••., .9.a,0•...... ••••• 3 •••• 33.732 I.V7 1.9" ••~.,O.
96
rA'I~~c-'RACK Gaa.,~ 'ES' 0"'"
.~CIII&N .. a. Z.JE I
8.0.735 INC... •••••97 INCICS
'''....ER..l' liRE 70 OE~kS P
U Ila R6Qt1 QJ' lie fA Ii
0.0.110 10000. 9.:J9. 33.319 7.37 0••7. 2SMO.0.014. 10000. ,J.164 .t4 • .312 5 ••• 0.899 :J6.'0.0.0.92 31)000. 1.64. 25.187 5••• 0.9S2 65800.0.011.1 13800. 1."1 2S.Jl67 5.2. 0 ••63 79.00.O.M.' 22040. JI.OOO Z••JlI' !i••9 1.014 . 101.40.O.OJl:JI 10750. .I.... Z6.9M 5.29 1.045 II &390.0.0••:J 10000. 4 ••39 17.6•• 5.2' 1.0.. 11.3.0.0.0'57 sooo. 5.608 Z••:J77 5.29 1.111 127390.0.0210 .110. "176 28.~11 5.29 a.U6 a3a MO.D..... 7000. 7.ZS. Z•• 9:JS 5.2. 1.1.1 a3.8OO.0.M.6 6100. ••67. 310130 11.2. a.IU' a••600.0.0• .11 5000. 10.1.1 32.3.3 5.1. 1••7. 1•••00.G.OH9 3.00. 11 ••77 3:J.3.0 5.'. 1.30. a5:JOOO.0.O.:l71io 3140. 13.17a .14.503 5.Z5 1.346 ase ••O.O.O.l.Z .1000. a••••• 3a..... 5 ••• 1.3.7 a:>.a.o.0.0.1.12 ZOOO. 1•• JI•• .16.... S.a8 a ••18 16U.0.o.oalV 1.:100. a7•••• 37•••0 5.17 a ••39 a6'_0.0.0160 1000. 12••75 3•• a"" 5.27 1,.'7 a6""0.0.0070 300. ••••0 1•• a311 5.19 l •••a a637.0.0.004. .:100. I.S9Z :J•••aa 5.29 a •••• a.4MO.0.014:J 11050. 0.901 2a.6(;6 3.0. 1••7. 17SMO.O.OllV .I66S0. 0.SS6 a3.09. 3.06 a •••• .0.,.0.0.011. .157'0. o ••la 13.sa1 3." a.1I1O ••S480.0.00V2 100000. 0.'6' 2••576 3.0. 1.SSJI "!i....0.0.1•• 170.0. 1.a64 24.543 3.05 a.561 J6.~0.
0.01.~ 1.000. z.o.o as.407 3.0. 1.sn :I.osao.0.032" a0870. .:s.117 26."'. 3.0. 1 •••6 'Oa3•••0.02111 10010. .:s.1I86 a, • .;I4. 3.0• 1.6S1 411400.0.093V 20000. 5.1114 '0.717 3.0' 1.7•• ~1400.
0.M.2 lIOOO. ~.la6 .:s1 ....0 3.0. 1.776 6.1640••0••U2 1000. ••S•• 3a.17. 3.0. 1.7•• .37.00.o ••a;1I 7000. ~.r.7 27..... a ••• 1••aa •••••••0••a26 4000. 3•••3 a"••l1 0 ••4. 1••30 • ••40••0.00.. ;SOOO. ....79 27.665 a.66 a ••3• •• 160••0.01091 3.00. ..316 27.9916 a.46 1•••7 •••400.o.oloa • aso. ..Z07 28.7'1. a.46 I .... .5.....0.01•• 1.0•• ••1.0 1-;••39 •••• t .... ..t ....0.001.0 ~ooo. ....70 30."4 a ••• 1 •• 13 .......0.0••• 2lJO•• 11.1 •• sa.oS." ••43 t.9S4 .....0.O.o.ul 200•• 13.0•• H ... 1 a ••6 1•••• ..OSIIO.0••17. "50. 14.aS5 33.70. a ••.1 1•••1 .7.100.0.... t3 or••o. ...4&.7 .....I~ a ••• a.014 .72:S00.
97
PA'IGue-CRACK '-U.'H 7!ST OA7A
SPECiMeN Ne. ~~& Z
"0.7a. INCHES; .".1.iJOO INCMES
re-eIl,llTU'Ie 70 oe....... P
IH W. lUllIII a AM! 6 III
0.0159 ld.U·O. 2.&0~ 2•• 7;'5 5.20 0.9,.0 ••~70.O).O,JO,J 17000. 1.6as 25.077 5.2iJ O.HI 6 ......70.0.00.6 11100. l.aa5 25.010 5.410 0.947 71.70.0.00•• 17000. •• 5 .... 2S...... 5.20 0 .... •••70.0.0292 20000. a .... a••••• 5.410 0.995 10 ••70.0.0.159 10000. ~.a3a a .....oo 5.ao l.oaa uII.ro.0.oa60 0000. .....1. il....... a.ao I.OSO 12••70.o.oza. 6000. ••aaa a7•• ra 5.410 1.075 l.1a.ro.0.U70 .000. .... r a8.016 5.410 1.101 l ......ro.0.01•• • o~o. ••••• 2..... 5.2• ..Iao l.a.70•0.0411. .000. •••• 7 a .....1 5.410 1.1.... l •••ro.0.oa62 .0lUI. 6 • .,.3 29.582 5.ao 1.16• Ilt".ro.0.0...07 • 000. ••••5 .10.2a• lhao 1.19. IS••70•o.o~oo .000. 7.a7a ..0.11111 5.410· I.aal ....ro•o.oa.1Z .1000. 7.1177 31 •• , .. 5.410 l.a.a 161.ro•0.0.:11. • 000. 9.1.9 .12.a7. 5.19 1.27• 1.5.70.O.U." a.oo. 10.050 U .... •• 19 l.a9.. 1.'.70.0.oaZ9 aaso. 10."'7 33.... 5.20 ...121 Ir0120.0.0.10. a.so. la.167 .......5. 5.1. 1.:lU .r2770.o.oa.o aooo. IZ.IIS. .1•••11 s.a. 1.:17. lr.7ro•O.O.lZI U50. 1.....la .......0. s.ao I ••or Irrozo.0.01.. uoo. 15.';'.1 36e663 5.1. 1••U 17.120.0.017. lJ50. 101.7.1' 37.~ ..20 1 •••1' 17".ro.o.oaoo 10.:10. ••••• 37.r71 s.a. I •••• lllo.ro.0.01 •• 1000. 1 •.Ja. .111.1•• !a.ao •••56 1111.'0•0.00.16 10000. o...a. aa•••• .1.03 ••••• 19••ro.0 ...0. 1.0000. 0.6•• a~••5" .1.0.1 ..... .1.1I.r ••0.010. aOOlto. o ...a .. a3.i165 .1.00 I.Ma 351.ro.O.lIlJ. 1.750. 0.93. a ••;t~ .1.00 I •••• ....6220.0.0••• 1.IS0. ••• .1. a ••9ra .J.O.1 1•• ra ~3r••O.01aa • u.o. •• a •• 2••2...9 .1.0.1 ••582 .....NO.0.0.1a7 a5r.o. a.a3. a ••a .. .1.03 1.6.9 ••• a70.0.029. la.oo. .I • .J •• ar.... .1••3 ....r ....3 ..r ••0.0267 9700. ..... a ••aa• .1.0... 1••82 ••.1.7••0.0••• • aoo. O•• liI. a"'.71 r ..1.0.1 ..72!a .12'70•0.0.11.1 .000. •• 13. .'I..... J ••3 l.r.r ••r77••o.oas... J400. 9 ••al ...1 .... .1.0.. 1.7.., ..0770.o.o.na JOOO. • 1.2,U J3.ar" .1.O.J 1 ••• .1 ".171'0•0.H9. .000. ......... .1.1.'0' .I ••• ..IIoil. •••71'0••• o•• r 1000. •••ao• .... .1•• 3 ••• I ••"'• ...770•••0 • .11 100•• • "' •• 1'7 .I........ .1.0. ...... 460770•....,. liOO. 1:..aa.1 .....a.a .1.00 '.Ma ..727•••••••1 ftO•• •••••3 .1••'04 .1.0• ..... ..rrro•
98
rATIGUe-e~ACK GAO.fM TelT DAfA
IPeCI~eH HO • • .11 ..
• -0.60S ...c... ..~.oao INCHas
........ fln""e 0 o.uus r
~ QtII UlUlI Q5 De 6 ta
O.OO~" 1.560. 0.31. .1"••36 ".30 0.95. 63aoo.o.ooeo ..157'<10. 0.2.16 25.002 ..30 o.wal' ",,~70.
o.ooa" 31300. 0.21. 15.0• ., ••30 0••71 t3".70.0.00.ot3 1'260. 0.250 2a.a". ••30 O.'lfl'a 1""30.0.0000 &7160. O.it66 25.202 ".30 0••7. 16.1.0.0.01•• "5Z50. 0.6Z. 25 ••.10 ".30 0.'.1 .110."0.0.0097 152ao. 0.7'77 2••••Z •• 30 0..... 2.1'700.0.0&".3 alzao. 1.",aO 2••0 .. 7 " • .10 l.oa7 a.".,.o.0.oa7.3 I.VOO. 1.907 26••6. ..3D I .... 27UMO•o.oal. ••"0. I."•• 2••67. ".30 I.OS7 .17••.10.0.0.11.1 13790. z.a06 27.3.a ..301 1.0'10 290310.O.03atl ....0. il.77. 27.903 ..30 1.115 300170.0.01•• 96.10. 3.1'5' 2••S03 •• .1" 1.1.1 30.,..0.o.u"a 71160. .3.212 2W.t.<I " • .30 1.170 .1'1'_0.0.032. 10330. ..0." 29.... ".30 t.ao. 327990.0.0.301 ~60. 5.075 ~o••oa " • .30 I.za. 33:Nt.O.0.00a5 5660. ....72 ~I.3a• ".30 1.2... 33.310.0.0.... "it20. I'.V07 U.OZI ..30 I.z.a 343NO.0.026. 36.0. 9 ••a. 32.062 ..~o I.~U 3.72ao.0.0.1.1 ~I.O. ••7•• 3.3.11.. • ...0 1.34. ".0_0•0.0.171 26.30. 10.723 34.700 ..30 1.37. 3130&0.IhOllO ••0. 10.~I. ~••O.ll ••.30 I.~a. .~O.
0.0300 2960. IZ.9al 3•• 033 ••30 1.413 3...0.0.02.0 1600. 1••700 36....~ ••.30 1•••.1 ......0.0.0007 I.ao. .l3.1.0 .17..... ••30 t ••li. 35.MO•0.04.. 12.0. zt.7M .....lf7 ..30 I .... ..;a.70.O.OhO 360. ZZ.3.3 .3•• 0110 ••30 t .... 36t230.O.Ozao I.SO. V.19Z 39.3•• ••.30 I.SOS ~2.NO.
0.0000 11.0. .1.777 • 0.067 ..30 1.523 36.UO•O.UM 10~IO. 1.601 • 7.913 5.00 I.HI 37.1..0 •0.Ol~3 3a710. a.la' 26•••0 Z.70 1...1 .0....0.0.0.1.0 ".0.0. a.33. .17.1.. a.so I ....~ ......0.o.oz•• 13000. a.7•• a7.,,7 a.so 10'" .1...0.0.0.0. 9660. 2."32 z ••as. 2 ••0 1.6.7 ••10300.
Reproduced frombest a"ailable copy.
99
PATIGUR-C.ACK ~U.," '.'T DATA
~!CI ••" hC• • 2. 5
..0•••3 INC"•• _J.OO• INC....
JlU•••,.'U•• 70 I).~U. P
II. 61111 llJQIII a II! • III
0.0... ,.a.o. z.la.a a•••• O& • • .:10 0.'14' .li9.JO.0.0177 aalJO. l.la •• a •• 960 4.30 0."7 li."O.o.oao. d.OO. 0.".7 a••o~ • ...0 0 •••• ....0.o.oao. ' •••0. 0•••1 as.S71 ..30 D.'''' 9.040.0.0.0. l71110. 0.7U as.771 4 • .:10 I ••oa lOtl.O.0.015., a.alo. 0.735 a•• o:s. 4.30 1.0•• U~060.
0.00J7 ••uo. 0••73 a••••5 4.30 I.oa. 1.7IM/O.0.01" l7aoo. ••a07 a•••,. ..JO .;u. •••790 •0.01'. .IIJOO. ••7.l a••lJ2. ..30 ..... 1.....0.o.oa•• 13•• O. 2••7. .7.66' 6.30 1.007 .9.500.0.03.7 lIV-O. ~ ...OO a••131 6.30 1.117 ao....o.0.032. 9700. 4.110 a ••".a •• JO •• IS. a ••uo •0.06.0 10lolfiO. S.lol" ~O.OIU ....0 1.197 aa•••o.0.04 .9 7••0. •• 1" 3 •• 011 4.3,) ••2S. 1£3...0.o.u!>o 6000. 7.4" 3a.091 ••30 I.a,. a•• ,oo.0.OJ7. ."0. •••7. J3.11.. 4.30 •• Jla lol•••• O•o.oa •• 2.70. 9.0a. ~.'''O1 ••30 ••3U .....0.0.03.' .ItUO. Il.UIO 3•• 701 ..30 1.361 alil"O.0 .....0 395O. •a.510 36.a.16 ..... 1.61a a5...0 •0.0.1" 22ao. •.1.121 37....5 ••..to I .... alII....
100
PAT&~e-C.ACK GaO.," TEST DATA
SPIC. Ut'" HU. 41E 7
.-0.637 IhCHES _.1.011 INCHES
UlMPt.Il ..TUAE 0 De:oiAUS P
CU QIlI iUQIII 1m. Q£ 6 ~
0.027. 4920. .1• .,99 Z8.6al 5.liO 0••7. 20990.0.0050 17lf>20. I ...... 2••9.5 ~.70 O.VI& .4SI0.0.0045 ".020. ~.3.2 Z5.&~!5 •• 7C1 CI.920 .oI~O.
CI.00.2 21~70. 0.ol06 25.&9.1 4.70 0.9Z4 9.~00•0.0027 176&0. 0.a2. 2s.a•• •• 70 0••27 11.37& o •0.00•• Z.030. o.a•• 2S.3it~ ••70 0.9.1a &.177.0.0.00.' Z~560. O... ,JS 25•• &2 ..70 0.9~7 161300.O.OOM 27&90. 0.6K ali.N'" 4.70 0.950 1••••0.0.02ZS 32.120. I. &5. 26.0•• 4.70 0••7• UO.IO.o.u.o 2d180. I •••• ao.7'~ •• 70 &.01.1 2••990.0.OZ.2 15770. 2 •..17. 27•• la •• 7.1 1.0... 2.4700.0.0"411 10000. a.v.11 Zi ••2.1 •• 70 &.06' 27.760.0.0~7 1070)0. ~ •• &2 28••• 7 •• 7;» 1.10a z....o.0.00.. 29.0. •• 1 •• 211 •• 7'11 •• 70 1.&&2 a • .,.Io.0.030. 70.0. :i.OSJ 2~••".1 4.70 1.1 • .1 2"~4.0.
0.0,",.1 5<110. !t.VOI "'0 • .1~1 ••70 1.17.:1 .101270.0.031. 5110. 0.1A., .11.&0. •• 70 1.2" .10.440.0.033& 4• .10. 7•••• 32.0". ••70 &.a311 .3&0.70•0.0307 .1920. ••1I7a 32.'01 ••10 •• a70 31 ....0•0.033. 3.30. .0.~6S » .... ..70 •• .10. ......0 •0.0131 Z050. 11.0.7 3••lIOO •• 70 •• :5•• 3aOS70•O.NO. Z.70. II.". 3 ••••~ ••10 1.3., .12....0.0.0330 2Z00. lZ.70S 3••4.a •• 70 loJa7 Uli..O.o.oa.o 2.200. 1.3...... 37.6a7 4.70 1••15 .117040.0.G~30 2530. 1•• 31. ...8 ...... 4.70 1.4.0 .130370.0.0...0 2.&0. I ..... ..."'• ..,.& ..70 1.... 3.3a700.0.0.100 1.70. &7••3' ••• 1•• •• 70 1.514 » ....0 •O.O~U 1220. 11••.100 • 2 ...... ••70 1....s .13••70•0.03•• 16.30. lZ.00. 4.s.0Iol •• 70) 1.5•• 33'500.0.0il.7 1470. II •••• ..s.61. •• '0 10='71 ~~."70.
0.0,)•• "'••0. 0.0•• 2'••2'" 3.GO 1.63a 3•••0.o.oro&.J .~70. 40."'" ...1 •••2 ..1.00 I .... .s••120....0,)&. .S70. ••••a 32.aZ.l ,).0;1 1.71. ....a..,o•0.0~'.1 .l2vO. v• .,,,. ,).J.VIo!t .1.110 1.7•• ".•••0.o.~... .1790. &1.7•• .15 ...." 3.,)0 1.7•• 3...770.0.0.... .16.0. 13.0&4 "".2", ....00 1 •• &. "'2••0.o.o••a 31.0. 1•• .113 39.511 ,).00 I.". .17...0.O.o.J II a130. 1~.1". 41.6..3 3.00 I •••• 3"7')0.0.0191 ••'0. U.017 .3..... 3.00 1.9a3 3'''00.
101
102
,,,TIGUE-CRACK \oRO.T" TEn OAT"
SHCI.... Ml. UE a
••o ••ao aNCtleS .·3.009 INCtCs
Tl!'-l!."IU1U! 0 D~G8US,
'" QJII QUit III. II! , M
0.01~ ,..0. .h9.3. 2••52~ ••.10 o.ella .J0790.0.0.03 31Z60. Z.31S 2•• 76. ....0 1.020 6Z050.O.O.ZJ 21 ••0. 3 • .J.6 Z6.70. ..30 I.~• 413.90.0.0.9.;l IZ.OO. ..7.7 a7.76. ••30 1.11. 9••90.0.Oil.7 5Z10. ••••z a8.av. ..30 1.1.2 101100.0.0.13. .OSO. 7.Y.l a •• ta. ••30 1.10. 10S150.0.0.11. .1020. 41.7.1 a••so;, ••.10 I.I.J 10.U70.0.0215 .11100. ".116' 30.aao •• 30 1.laz 111170.O.O..JO. .J~O. aO.7•• 31.0'1 ...1. a.zs. 114.JO.0.0401 3-.60. IZ • .I43 3a.o• ., • • .10 1.19. 117.0.0.0~.2 11IIAO. 1.J • .t HI 32••10 ••.10 1.3a. 119.30.o.oa•• 1930. 1... , •• 33.S9a ••30 1.3... IIU'OO•0.02S0 1'.0. 1.....2 .I••3S. • • .10 1.30" 12....0.0.0"33 21.0. lS.3.3 3!O.364 •• 30 1•••n aas..o.o.oJaJ 2260. 1••0.9 36.S.' ..... a .... ' aI7940.0.oa9. 1610. 1...9.7 37.sa. ..,~ a••o. aa9HO.0.02 .... a490. 2a.0'5 .... lIIr2 ••.10 a.4'" a,a040.0.0.101 1250. 20.2.0 3•••.10 •• '0 1.US a,a..o.0.029. IZ.O. ..<lr.l " ••,.a ••'0 ..5a. I.lM30•o.ozas 9,)0. 2.40a 40.Z'. 4• .10 I ••H 13.430.o.o••v .19420. 2.196 26.'13 2.60 1.61 , 17,..0.0.0434 21.20. • 2.650 2••••• 2.60 1.6•• IVU70•0...... 10000. a.9.a a ....7. 2.60 I ••• aOS27••0••41. 10.0•• 3•• 04 30.1411 a.60 I.'•• al.'70.0 ••••.1 10.00. a.V5. .II ..... a.60 1.'6. 22.770.0.02•• 10J•• .;l•••3 32.S... Z.60 I.'" .3a770.0.02.1 .00•• .t •• " '2 ••SI 2••• I.'M a ..."o.0.0313 211&3oJ. 1.9•• ....9. Z.OO 1.... a6.VOO.•••.11.1 .0010. Z.O'. 4111.306 2.00 a.079 • •••10.oJ.03.6 a51.10. a•••• a ••••• •••0 1••11 ."040.0.O.Ia4 .2000. ......1 .. a .""0 2.00 1...6 .;10....0 •0.02'. • 000. .1.2.407 17.S"" z.oo 1.... 311040•
103
rA'IGU~AA~K GAO.'" 'E" OA'A
SP&~I"." "0. 41E 4
.-0.610 INCItES _3.0Ia INCHI!S
'E.HIiATURI! 0 OIl:CiRE~.,.
Il6 Q~ 1l6ge. ~ ge 6 tt
0.OUi4 2147Cl. 2.10. a~.0'7 ..30 0.9M 524. o.0.0172 20580. .1.054 as. 0.'" 4 • .10 0.9.S 72990.0.01~4 • 1l.0. 2.37. 2li.3•• ..30 •• 002 ••170.0.oa80 lZ7ZCl. .I •••• 2~.e:tz 4 • .;10 •• ou 96.90 •0.0.75 .a870. 5.173 26.e21 4.30 I.oao .097.0.0.0495 7670. ••6•• 27•••6 ..30 ••• a,) .. 7430.0.oa57 33.0. 7.,)2a aa.,)~o ••.,,0 ••••6 .a07.0.0.00a7 .000. 7 ••0. aa•••• • • .,,0 • ••54 .21740.0.0257 31.0. 7.8a7 a9.099 ••30 ••• 7a 11.010.0.034. 4130. ••••2 a9.ltoo ••,)0 ..a.l .a90.0 •0.,)2a. a7ao. V.41a 30.IUI 4.30 •• a36 &3.770.0.02•• 2200. 10.034 "'1.061 4 • .;10 1.256 133.70.0.0.73 4530. 11.:;35 .;Ia• .J71O ..30 1.304 13...0.0.oaa6 1.10. 12.4.6 .;1.;1.01'" 4.30 1.327 14".10.,).,)3•• 29ao. 14.,)51 34.143 ..30 •• 36. 143330.0.040. .10.10. Ut.44S .J=t.:ozol 4 • .10 1.40. , ....,JO.0.oa73 1570. • '.70a 36••13 4.30 •• 43S 1.'000•0.oa7. 1.00. Ilh."'5 37.alla 4 • .JO 1••60 149.100.0.0260 la.o. 19•• aa 3••3.. ..30 1•••0 I.OHO.0.02•• .uo. 5.70a .3••570 4.30 I ••'" 15ao.o•0.03040 1260. 2.963 39.038 •• 30 1.507 1.,1340.0.oa6.1 32.ao. 1.460 a5•• 75 a.60 ••570 1••••0.0.0.7. 16illO. •• 430 25•••• 2.60 I •••• aoa.so•0.017. 134.0. 1 ••.19 26.16e 2••0 ..607 21 ••• 0.0.023. .7060. 02 ••0. 27.02S a.60 1.63. 23a970.0.04...0 .5'130. ••69. a ....16 2.6" ..... 14.ltOO •0.04.. • v.Jo. 6.116• 30.a,. Z.60 ..733 a.7Uo.0.032a .1100. .....a ;1'.0<&7 2.60 1.7.3 .,6.NO •0.01" a200. a.7a. 31.790 a ••o I. "a a6,1.~0.
o.ozaa a.oo. v •••• 3.10672 a.60 1.794 1652,10.0.0093 z.oo. 9.0aa 33••35 a.oo I .... a.7:1:1O.0.OOt46 Z.OO. 10••1. .....Ia.. a.oo 1••:11 26••,10•
ReprodUCed lrombelt available COpy.
fA flGUE-CRACK IiROW'M 'I" UAU
5PICIMIN NO. 4ae 4
.-0•••4 lhe... ..a.99' INC.....
TIMP.~ATU_ 70 DECiMHI "tU IUt 11611. ~ ae l ..
0.~204 ..~oo. ~.V'7 .J.J.lt57 6.oa O.VI.J 29500.0.0140 7100. :1.&10 2••5.Jl •• 31 0.927 .,)0..0 •0.01 •• • 3000. I • .J.J.J 2••".~ 4 • .Ja 0.9.9 $~.OO.
0.00.. 6700. 0.65. 2••••0 4.3a 0.9.. .1100.O.O.J.' 471$0. a.I.I" 25._2 4.2. I.ooa ao...o.0.0'.1 27350. 3.605 a7.11I.J 4.30 1.07. 1.,)2aoo.0.0071 aoooo. 5.0.1 29.061 4 • .J0 1.15' 152aoo.0.0446 '400. 0 ••" 30.0.7 ••31 1.1•• 15'16".0.0300 5000. 7.76. .,)'.90. ••.J2 I.aa, 1•••00 •0.0010 5000. II.'.' :11 ••30 ••30 •• 26• .........0.0.76 5000. • 0.4.7 .1.$.150 •• .10 I. ,,)12 17.600•0.0447 0000. 11.040 3•• 416 ••a. 1.3.7 17MOO •0.04• .J ..600. a •• " •• .I6 • .la • •• .:U 1••07 102200 •0.0.05 3000. 2.001 35••51 4.30 1••02 1...200.0.0201 I~OO. ol•••a .J••4~U ••30 l.oa5 a••~oo.0.0009 1.7000. 1.0" 23.001 a ••• a.llI a .I~")200.
0.0.76 2.000. •• lt97 a.J.eoo a ••• 1.542 _a ••o.o.ua. a.3100. a.0.3 a••o•• a.so ..... • • .JOo.o.oao. ISOOO. 2 •••.3 25.77.3 •••0 1.611 3""340•0.06.1 a ••oo. •••a. .7.... a.so 1.67. • ••.J00•o.o~a. 6.300. 5 •••.3 •••603 a.so 1.702 .as..o.0.063. 10000. II.". 30•••7 a.50 a.'_ • .JtoMo.0.0.12 4000. ~.a.o .J2.1.'I ••4. 1.7.. .~'I_o•0.00.2 1000. ~.7'6 3a.17. a ••• 1.7" 000640.0.0~07 10000. :t.~.S 27.dZ.. 2.0.:1 • •••2 .5....0.0.0210 • 000. 1.<13• 29.3.7 a.03 1...0 .....0.0.06•• 6000. ..1.0 30.5.111 .... • ••.10 .....0 •o.oz•• .JIOO. la.Ol. 31.201' I ••a • ...0 ..77.0.0.0....1 .3".0. 1~.6.7 3a.51.,) 1••7 ••••• .70'.0.0 ..... 2000. 111.615 J ••••O I.'. lI.oa. 4'2'.0.0.0"" 1000. .7.11.33 .15.7.110 1.- 2.05. .'."0.o ••a.. 1650. •••••• 33.3.. 1 ••7 ;, ••• 7 .76190.
104
""1' I GUE-CAACK GMOWT" TEST OA1'A
S~eCI.EN NO. ~EZ
..0.6.10 INCHES .-30.00. INCHES
TEMPEIlA1'UAE 70 OEoOAEES ,.
U Il~ UQ!l g, ge A III
0 ••a92 ao~o. 3lO.927 29.cJ23 6.30 0.53. .,.00.0.002lS 1100. Ilt.lt70 29.11.50 6 • .10 0.&6.1 &700.0.159' 21500. 7.7•• 32.2&. 6.30 0.126 27200.0.02J1 IViOO. 2 ••2.3 2••ilM •• ~O 0.91. .6.100.0.'0219 32250. 2.1.3 2:a•• .32 ..51 0.911 7.550.0.051. .32550. 2.793 2••135 ..51 1.019 111100.0.06.& 20000. 3.".7 27• .15.1 ..51 1.07'9 131100.0.0••• 10000. ••992 211017. ..50 1.120 1.1100•O. ,)4.2 1000. ft••O. 29.137 •• 50 1.162 1."'100•O.OZ9.l 60000. 6.560 30.00. ••50 1.197 Ila5100.0.0••• 60,)00. 7.517 31.001 ..&0 1.237 1.1100.0.0.... ,.000. a.fl6. 32.ait.1 ..50 1.2.2 10'100•0.05.3 6000. 1.700 3••.337 ••50 1.35. 17:J100.0.0&0. 5000. 7 ••9a .3••90. •••• 1 •.187 17.UOO.O.Oli.S .000. 2.656 35.205 6.50 I ...N 1.2IUO.0.03.3 110970. 0.&31 22.995 2.62 1.503 2V3070.0.023. 11.00. 0.5041 22...7 .1.60 ...04 30.670.0.0100 a!looo. 0 •• 73 2.1.10. 2.60 1.516 H9670.0.00...3 12610. 0••9. 23.302 a.60 I.U. 34liZ...0.00.0 17000. 0.616 2.3....1 2.61 1.52. 3.9.1.0.0.0063 17150. 0•• 73 23.50S a.61 1.52. 37...10.0.01.. ,34.00. 1.211 2••031 2.61 I.S,.I .10930.0.031V .17500. 2.300 2=».02\1 2.61 1.5"0 .3...30.0.05045 .10610. .....0 26.c.... 2.6a 1.6•• ••"040.0.0.57 12500. 5.26. 2 •• 06. .1.61 1.6V2 .7IlMO•0.0." 10000. 6.6" .10.2112 2.6. 1.7.11 ••1.00.O.06la 1I0ao. •• 7.1 3".139 2.61 1...1 ."'11..0.0.0••0 .500. 6 ••7. 33.7.11 .1.61 I.U7 •••0.0.0.0.1'. 3750. 0••.1. 241• .130 .1.10 1.005 .97790.o.o.nz 7.100. 7.0... 30 ••0.. .1.1. 1.901 505MO.0.0.197 .!i00. ~.2Z1 31.771 .1.1. 1.93. 509••0.O.O.3.la .1750. lit.098 3.:1..U6 2.16 1.970 51.....0.0.0407 3220. 11.. 11.6 .1•• 7.13 2.0. 2.0019 51 .... 0 •O.Ola •• 3 ••0. 20••01 .... FI.l 2.10 Z.OlO 520050.0.Oit6S 1000. •••••• .10.826 .1.10 1.926 $.11050.
105
PATIGUe-'AAQK GAO.T~ T••1 DAIA
...ecl....N N4:1. UE I
.....&1 &IloCHe. .-3.000 INCtI&S
II_eR~TuAe 0 DEliRU. P
Ala llJf QAII" .. lilt! 1 III
0.0111 2.7.0. 1•• 71 2..... _.~01 0.977 :;4270.0.0273 3ol3.0. 1.4.0 2!).a51 •• :so 0••9. a.660.0.00'.1 120~0. 2.04~ 25••.16 •• .s& 1.016 986.0.0.033. 1•••0. 3 • .10. 26• .1.1 -.~I 1.04' 113630.o.oa,~ 1510. ...~. .16.7.3 4.31 1.072 122140.0.03~" .420. 1.3'1 27.3.3 4.31 1.103 120..0.0.047' 0910. 7.0•• 10.565 ••31 a.&SI 1:J7.70.0.0.1.1 4••0. 1.072 2••305 ••30 1.'09 141&30.0.0.1' 'ClIO. V.S.3 30.5.. 4 • .:s. a.a37 147740.0.0.1' ~770. aO.4.a 31.521 4.30 1.27. ISl5a o.o.o.a. 4020. la.2.0 32.73. ••30 a.:u. a11530.0.0••9 3510. 12.01. 34.01. 4.30 1.362 159.0.o.oalv 2700. II ..... ;l5.04S 4.3t' ,.;3.5 161750.0.031. 2700. IZ.203 :S6.102 4.3· 1.4Z0 1••••0.o.o.:&a. Z150. 1... 1.1 37.0.7 4.3l- 1 ••55 a••700.0.011. ZOOo. la.aoo :sa.167 4.30 I •••• 1••700.O.OH. &SOO. 5.1Z. 3a.&56 4.30 a.... &70200.0.oa3. loOO. a.v'l 3a.51a 4.30 1.6.3 ,70700.0.0••7 210.. 0. &.sa4 a...... 2.60 a.535 1• .1»0.0.0473 13.ao. 2.00. Z••3.7 .1.60 1.014 .1.57.0•0.0307 Z1&30. Z.70a 27.771 2 ••0 1.6S0 .1....0.0.060. aoo.o. 3 ••0. z••a36 .1••0 1.710 1....0 •0.0••• &3...0. 6 •• a. ~.4S. 2.00 1.7.. 300770.0.030& :soao. ••••• 33 ••3. 1.60 I ••09 30'7ao•o.oa•• as&o. ...... 3••~'. 2.00 &••ao H ....O.0..... 1900. 9 ••1. 31••31 1 ••0 l.a5a. :soaa.o.O.IU:SO 900. a.eoa. 3•••"7 a.60 I ••S. H."O.0.0••• la090. li••71 a•••• ' .1.00 1••0lt :S20a ...0.0&77 4':&s0. lI.ao. 3"0.SI0 .1.0,) I ••'" :sa6no•O.OlZ~ • 000. r••101 17..... 2.00 I •••• HltUO.
106
"A'IWI-C""Cll INIO.'". '.IT DATA
'~.C'M'" MD. .11 •
"0.6' 0 IIIICNII ..,.Oll INCMC.
' ......AT".. -I' 0•••1 P
g,II" UDII! U .. • It
0.0... a0430. 1.0•• as.a., 4.3D O.'M 003.0.0.01 .. 111.0. 1 • .1•• al.lo.. 4.30 1.01. 10•••0.0.011' 112.10. I.'~O 16.1.' 4.30 100.1 .1.1710.0 ...... 11 ••0. I •••• 17.0." 4.3.1 100" ,.taftO.0.011. U.100. ..,.. a? .., 4.30 1.09. 1....0.0.0184 11170. I •••• a7.71', ••30 ioU. .a".ao.0.0.1.. 16.ao. ....,. .a• .J7. 4• .:1. 1.1•• 14......0 •••7. 11070. 3.'0' a'.NO ..- I.ln 1•••'0.•••301 '.00. ••••• a•••o,. ..30 I •••" aOllflO.0.0••' 12000. •• 1•• .I, ..... ..- ,.... a.'9'••0.0662 .6.0. 8.108 :u.o•• •••• 10.1.11 .I"HO.o.o.a. JOOO. ...070 .13.900 4 • .)0 103.1 a30••••0.oa1.J .10110. I~.'I' 3•• ''';£ 4.:10 ..3•.1 a;l;l11l0.0.03aa 3060. 11.33' ....7". ••..a. 1.4" a.1.....o.O.OJlt a,.o. •.1.". .11••"6 4 • .)0 a ••• ' 13"4.10•0.0400 .1000. 14••" .s1.,,4. 4._ I .... I.au••o.oa.. 1"10. ,...., " •• 3_a ••30 &••a4 •••••••0.017' 1000. I'.'''' .O.oal ••.:ao a.ua •••1•••0.0••• 1000. .,.IU .0.... • • .10 ,.... ••al.8.o.oalo 1000. a •••o .0..... ..... ..••a I.,....0.0'11 aooll. ,.00. 41.a•• ..30 '."0 a••••o.0.0.11.1 • '.10. I .... ..,..., a.70 I.U" le14:aI.O.O.JIO 1••.10. a.a.. a ••6'. ..70 ,.... 310960.0.02.. 11000. a•••• a ••••~ a.70 ..... II&'MO.0.0~0" 10000. .I ••• ' 30 ...... a.70 a.,.~ .I~I"O.
0.oa07 • 000. 1t.46.. ", •..,.&. a.70 ,.,.. """'0•O.O~'O SIiOO. 7••1. "LO•• a.? I.Y". .14...0.O.OJII :1000. ao ..... .14.00. a.'. 1.,," .14,....0.0.... ao~o. 'a•••• " •• 00. 10"0 1.111' M""•.0.0'01 aooo. 1..... H ••I. a.70 .....1 ~.I"..O.
0.0'" aaao. I'•••• .:I,• ..,. a.70 ..." .4oaO.O.OI:S.. 1~0. ' •••~l ~••o." 1.70 I ....,. .1~.a70.
0.013a '60. a, •• ,. "...... a.?o 1.9.a ~1J'.30.
0.01 ... ..0. aO.911 • •• 1.. a.... I.VJ. ~•••O.0.0111 .10. 1•• 141 4,.se" 2.6" I .... .7.00.
ReprodUCed fromhesl .v.il.hle COpy.
107
._I.GUI-CMACK GRU~J" JeSI DAWA
.IIec ••e. -.J. 4.1: ~
••0 ••'1 INC... _:S.OO'• • He.....
le_...UURE -50 DEaH• •
116 !Ill Q6QII II!' ge 6 II
0.'U41 16•• 0. a• .l~. a •• o»~ •• ;so le02S 49900.0.0.'1' aal90. a.it.a a••• _ .."JO ••0.,) '<&690.0.01•• 213.0. •• 904 a6.707 •• .JO 1.07' ••oeO.O.OU. ••• 00. 2.0•• 2'.5•• • • .JO I.UO IIZIaIO •0.0.... '740. .l.603 a ••400 • • .J. 1.137 .1£••••0.0.17. .0410. ...., a •••• r ••:t. a.17. l.:Ia..)~o.
G.,U06 6030. •• 7.0 a9••0. •• .J. ..209 L.JtI~••G.O~•• • ~ao. ...." .lo.u• 4 • .J. a.a.J.J l.a.70•o.oaoa ".20. ..,.. 3a••S9 •• .JO 1.2.7 1••090.D......? :tUO. 7 • .J06 ;S•• rr a ••.:10 a.zllO I."'UO.0.0240 ,).JOO. '.6'" 32•••• •• :to a.:to. a52'OO.0.0;,... ••.JO. ...laaa ,).J •• a. 4 • .10 1.3.0 157U••G...ao ".30. 'II.S.9 ;S4.,06 ..3., I • .l1. .616«00.o.oa,. .JOOO. ao.,a" ~•••70 4.:t0 1••09 .......0.03•• ,)000. • •• '11.4 :s•••o, ..3.J I •••a .6'''0.o.u•• 2.00. a...... 3/.0•• ..<&0 ' ••'3 .70a60.o.oa.. .000. ao.o•• 3....a 4.;S0 a.4.' .7& ••0.0.02.4 .... 0. .I.a,. .J..... ..u 1.4." '71.'0•0.009. 530. a•••• 3 •• 9.. • • .;so ••5U .73....0.010? .7.Jao. O.VO. 014.'<&.1 z ••o l.sa. .vOtalO.0.00" ,0.SO. 1••a.1 01...... 2.60 ••6.S ..77"'.0.04 ... 1....0. •hZ•• z7 ....a a ••• a.D• a9a900.0.04ao a"..Ch .J.030 ...... a .... a."o• :1&0960.0.00.19. aZlt.o. ••ou ;'lea7. a ••• l.'~ 323sa••0.0... Gaao. ... ,. ;,a• .103 2••' •• 70. :124163••0.001.. ~.10. aa ..... .1.Jd"~ a.ftO ••OOJ! "",...0.0.0.11. 2••0. ••53' , •• 0•• 2••0 a.... .1.1.....o.u,,, ~1£00. ••"00 ........ I ••' ...... 3.1...0.0.01•• "1l0. •.. r. "".134 I ••' I .... 33'••0.o.02ao 1&100. •••0.1 1'9.1•• ••00 1.91. "'''710.0.0." ••00. •••• a7 016•• '0 P••' a ••a7 .....JIO.
108
109
fAr IGUI-CAACK GAO.r" raST o"r"
SP,eCIMeN HU• .I~ a
..o.aal ....C..s _~.OIS INCHES
TeMPERATUIlE -so DE....U. P
QA lUI !WIlli IH5 ge 6 III
0.0109 4.1470. 0.57. .14.:0.37 •• ;'0 0.....0 127420.0.0211 4Ieo.O. 0.793 24.94. 4 • .30 a.oa.3 ae.",aoo.0.03•• .0550. 1.21. .15.5&. ..30 1.040 201lb50.o.oaos 22400. l.a.7 26.123 • • .30 le075 232050•0.041. 21200. .1.10. .16.67. 4.30 a.11I 25.3250.0.03.7 10010. 2.73. ol7.e.3. 4.30 1.I.a 20'1200.0.033. 10000. 2.~.6 20.311 ••30 a.17. 279260.0.0.307 12030. 3.3.7 29.20a ••30 1.21. ol.IZVO.0.03•• 9210. 3 •••• 30.017 ..30 1 • .1•• 300500.0.03.15 10430. •• 564 311.0.:- ••30 1.287 3109.0 •0.031a oliO. 5 • .127 .31•••• • • .10 1.315 3170-0 •0.029a .420. 5.9al 32.5113 •• .30 1.330 321.aO•0.0190 J:Oli O. ••.3~1 :l!.3.I'.I<t •• ;'0 1.362 .125010.0.02310 .14.0. .... 13 JoS••47 ••.10 1 • .384 ~~••5'.0.0.140 3.90. 7.2.2.1 .1••57. •• 30 1••07 331,,",0.0.033. 4.10. ••019 35.0107 ••.30 1••45 336750•0.04ZIi .0.10. 7."9a 37.1".1 4.311 I •••• 341370.0.02.3 3100. ••0.32 .18.122 ••30 1 ••09 3•••70•0.0~01 31.0. •• 09. 39.31. 4.30 1.5.0 347610 •0.(1'01 25.0. ;'.11. 39 •.331 ••30 ".41 3.0190.0.0.1. 2••0. ,.IS. 39.7M ..30 1.551 3.30311.0.01.0 00000. 1.29.1 .15.547 z.ao 1.009 413030 •0.0404 261.0. 1•••1 2..634 2.60 1.647 • 39170.0.0169 10.10. ~.a60 27.239 .1.60 1.607 .4",seO.0.0.1•• 11.150. .1•••7 28.0". .1.60 1.693 ..031t30.
PA"GU~-CRAGK GRO.'" '.ST DA'A
....c:'••N HU• • 1& 7
"0.". ...e.... .·~.'II INC ...
T~....ERA'UII. 70 OEGRaS "QA lHf UUIII Ill' lie 1 ~
0.0000 5••0. 0.7'~ a••10. • •..t. 0.9.10 .&6.0.0.0079 19330. 1.6a3 a ••a"" ..30 0.9•• 60970.0.009. 1.00. 0.61. 2.- ••0..t ..~O 0.'~6 e9550.0.0110 '900. 0.0.0 2••••• • ..30 0.961 '7610.0.0019 &.070. 11.6'. a••6"'. ..30 0."3 97.00.0.001. 9000. 0.'00 2•• ' •• ••30 0.91. 101000.0.00'0 .0.0. 0.7.9 a....' ..30 0 •••3 110••0.0.01.3 alfooo. 1.299 a5.131 •• 30 0.9•• 135000.0.oa7. 16111ao. 2.150 .0.59. ••.30 l.oa3 a=l&600.o.oau 105ao. 2 ••7. a••o.. ..30 a...7 I.auo.0.0;'0. 9000. ..t.,a. a ••s •• ..30 1.0'. a7laao.0.0307 ' ••0. ••••3 17.232 ..30 1.10• a 7.700.0.030. 7000. la.dO' a7 ••93 •• 30 &.a3. a.:t700.0.OZ73 6660. e.717 2••5dO •• 30 1.&65 a901.0.0.OZ9. .000. 7.766 oZ••a., ..30 &.&.3 aV6&20.0.03aa 3600. 4 ••54 2'.~.0 •• 30 l.aa3 a'7020.o.oa•• .a.t4 O. 9 •••3 30.740 ••30 &.&=1& aOI060•0.043a ."0. 1I.1l.7 3a •••• •• 30 l.a9. aOliaao.0.0231 a••o. &&•••• 311.... ..30 a.3a. a06..0.D.oa6. ao.o. &••a •• 33.&.' ••30 1.3•• a09000.D.Ol.a &070. l:i.&•• ~.7'-I ..30 1.35' a10170.0.01.0 1070. '0••00 3••a.0 4.30 1.375 all &.0.D.oa.~ ,570. '7.6" ~.'05 ..30 a ••03 aI2710.0.01.. 1000. a••S57 3S.71a ..30 , ••al la37ao.0.0204 \NIO. a•••o, 36•.1ao 4.30 ,..... 21 ••70.0.0&32 "0. 1••••3 3••••• ••30 I •••• al=tUO.D.oa.. MO. a.3D. ~.'7. ..30 I •••• .&0370.0.021' .50. I.asa 37.3" .. 30 a...7 la 7a.0..0.02a4 • 0000. 0.9.& a3.64. 2.60 a.S,5 a57UO •••oa3. 3UIO. 0 ••Z2 a ••3za 1.0. a.... a..no•0.033V 2641 •• 1.0•• a•••a 1.60 I.'" ;la ...o.0.0106 19.ao. l.a.9 as.5U 1••0 I .... U3..0.o.ouo 113ao. a.17. Z6.1.. 2.60 1.613 3a'j£70.o.oa•• 1.510. 3.3'. 26••al 1.60 1.63. 3637".o.oa•• luao. ...., a •• o.o a.foO '.0". 37.900.O.Oelilt 6500. S.liO. a•• 031O a.... 1.10. 3ltl.OO.0.""." 5500. e.~5. 30.ao. a ••• a.7..tO 30.900.o.o.,a 30.0. 11.3'1 31.lla a••• a.763 ..••900.D.oao5 2000. 9.aa. 31 •••" a.60 a.771 Ba900.o.oa•• 200u. aa•••• 31.aa. I ••' 1.1•• 393900.0.0179 1300. ' ••91. n.o.. a 2 ••0 1••06 395.00.••0100 13'0• 17.0•• 33 ••7. a ••o a •••• 3....0.
110
111
FAJ.GU.-eRACK GRUf'" 'EI' OA'"
I~ECI_~H hOe ••• ~
..0.598 IHC~S • ·~.OOI lNCI1I: •
,.,.,..IlI"JURe 70 DEanS "lit ga lUlIlII Q" lie " III
0.02e.... 10500. :..a 09 Z5.e.J7 ••~O O••,n J.t500.O.OJl.9 a.OGG. 4.!o.J 26.16 ... 4.JO I.GIO 47500.CI.0:.55 10000. e..JII a7.IUIl ••JiO 1.062 It'500.4'.OJlOO 6000. a.11I a,. 946 •• 28 1.102 oJ500.0.0••• .000. 9.113 21••2. 4 • .10 1.IJl5 e.7500.O.oall JOOO. 10.0)4' 29.350 4.a. •• 163 70)500.0.0323 3000. u.u .. 30• .J.t. 4.30 a.I.7 7.1500.0.oa19 .1000. .1.797 31.07. 4.<f. a.ail' 7••00.0.03.. 3000. 13.363 32.04. •• 211 l.a66 79500.o.OJl'" a500. 15.163 .I.J.OI~ •• .so a • .Joo .2000•0.027. 2000. ao.,•• .1.....0 4.3it a • .s.U ..000.0.OJl73 aooo. 111.412 35.080 •• 30 1.3co5 ••000.0.03•• 2000. 12.110 .sco •.s:.co ••.10 1••0. ...000.0.009. ~OO. la.993 J6• .:I2. ..30 1•• 0.. ..500.0.00.3 500. • ...33 3••6.1~ ••32 1•• 01t .",000.0.0109 50)00. 1.072 21.711 2.sa 1••2" 9"000.0.0200 1••00. a.lo. ~2.I26 2.52 I •••• 10.. MO.0.00•• aoooo. 0.".. 22.5.1. a.52 I .... 12...0.0.00.0 20000. o ....a a2 •••• .I .... 1••72 1....00.0.00" aoooo. o••a. 11••5. a.50 1••77 1....00.0.006. aoooo. 0 •••• 2ot••,).J a.50 I .... 1...600.0.000" • 000. 0.S70 22.77:. 2.S0 a••O 197500.0.0307 • 0010. a.,•• 23 ..1&0 a.roo 1••a7 a.7roI0.0.03.5 aoooo. a ••oa a ••co"o 2.50 10563 I.'IUO.0.0001 aoooo. ...00. 026.5.0 2.50 1.6.10 211'S.0.0.0".0 10000. :...JI a7.7"~ Ol••G 1.070 a"7SI0.O.GOG. 10000. ,.:." a•••7Z a~.o 1.730 J07S.0.~.0.7. 2000. '1.530 30.a91 2.50 1.7.2 3091UO.0.0399 .000. IG.703 3 ••~a.. 2 ••0 '.7111 31"'''0.0.041. .0.:10. .... 20 3 ••0 ... .1.50 1.8.11 317.10.0.05•• 3000. • ••Z2. 31»069.. .1.50 I .... .320SI0.o.O.2a. 30.,0. II • .:112 JlO.G'" 2.00 1••00 n ...lo.0.022. 3000. 11.700 JlI.5.... 2.00 I ...... .. a6.10.0.0.. 09 '000. 1•• 1•• ..3.0.7 2.00 I .... n ..... o.o.oao. I~OO. 1••72. ;J.:J ....&!' I.~. 1.1t•• 3..10.0.0.0254 15011. ~••5.17 33.3•• 1.17 a.012 33a•• O.
Reproduced frombest availabl. copy.
IlZ
PAI.GU!-(RACK GROW'" ' ••T UAIA
~P!C.M!N NO••ae ~
1180.,a6 .JlCHe. _a.tlvo .Ile...TcMPeIiA,uae. -.0 DaliNa•• P
.a U 'lARD .- Q£ 6 til
0.0109 1••00. z ••a. ~•• 70' ~.z.. 0.91. 5aa10.0.0••0 15060. z •• r. a ••ao~ 5.allo 0.94.1 .,z.o.O.O'~~ 11.00. 3 •••• a•• 269 S.Z5 1.00. 95~.0.
0.030. '.10. 3 •••1 a6.'010 5.ZS 1.0as 101aDO.0.0350 10000. ••••• zr•••a s.a5 ..OM •• aooo•0.03•• 02.0. S.D•• a ••3•• 5.ZS 1•• 01 lalO6O.0.0.06 ••.3ro. • •••5 a9.,.r ••ZS 1.16a 13a.30.0.0606 6rao. ..930 .Jo.a.8 5.110 a.a•• 1.19160•0.03a" ..10. 7.rr. ,11.998 ••a. I •••" I••ao.0.03.0 .MO. 0.03a ..~.ooo ..as l.a.3 1.9370.0.03"1 • .Iao. 9 ••33 3•• 0." s.as 1.:a&0 15....0.0 ....9 .3.0. 10.800 .....6. S.15 1.3•• llao.OrO.0.03•• 3••0. l~.ZO' 36.'." 5.as 1••0.. 1611020.o.oasl 2500. 111o.19. ..' .... 1 s.a5 1..... 1••020.0.0239 • 3.0. 13.357 30.9ol. s.as • ...3 1.....'0.0.033" 23ltO. ' ••3. .. ••03a s.a5 ••••• 167,ao.0.0••• ••70. a.rrl ~..~... 5."S ••• '9 a...II90 •0.00'. .0"50. • •• 01 a..... ~.O.J a.S$4 10.., ..0.o.O.1a.l • 0.1. D. ••••• ali••8' 3••3 lesr. , ....0 •0.03.0 a.ooo. a • .I,;I, 2'.~~" 3.03 a ••17 arS"D.0.0396 20000. .1•••• ar.9•• :lea.. 1.66" 11'...0 •0.0.53 ••oro. a.o•• a ••rvo .1.0.1 I.,az 3.0120.0.06•• ..l»o. s •• u ~I.~". .J.o~ •• 7 • .., 3a0&2••o.or•• .0.0•• ••••• ....a71 3.0.1 1••"9 3a.ao.0.0600 .0000. S.,.S .17.89. 3.0.1 1••99 33ltaO.0.0401 ...00. It.ara .0 •• 7. 3.0.1 • • ..,• .1 .I••.a.lIO.
~A' I lOVE-CRACK liAQ.'" rl!ST UArA
~P~CI"I!" ..C. 6a& •
e·0.7;'0 INc:t4&a ••3.001 IIolC~S
le:"..£IlAfUU -50 D£4.iMI!I!S ~
IU lib 116ga ~ l2!! 6 aO.Ul.", I~~~O. ol ....7 2!>.o~ol 5.Z!> 0.9.n OZZOO.0:040S 1.100. .3.,29. 26.2:'5 S.2S 1.01. 106;'00.0.')579 1.260. • ••~2 27.19.1 5.2.3 1.066 I<tO!tCoO.0.()34l1 77.0. •• ;f62 28.001 5.20$ 1.10. 121300.o.oaiol 0••0. S.70S 28.755 5.Zo$ 1.137 13.740.0.0.3•• :t030. ...~26 29.50a 5.23 1.160 140370.0.01 •• ,'lAO. 7.119 30.123 5.Z.3 1.104 14.ZZ0.0.0543 67.0. •• IU7 31.4'0 5.2.3 1.246 150)960.0.0376 3VVO. 9.723 3a••l. 5.2.. l.allO 1~4950.
0.0260 30Z0. 10.00. 33• .311 5.23 1.31a IS7970.0.Oill41 2000. 11.4107 33.\oOo$S 5.Z3 1.33,'J 15'11'1110.0.0230 2~0~. 12• .149 34.6. L S.23 1.35. 101970.O.OZ•• 2000. 13.599 ..5 ••0l> '-.2,j l.o$al 163970.0.IlZ8a 2,)00. 1•• 8a. 3e-.375 S.23 1••09 le-lIV70.0.0300 ",000. 1•• 5•• 37.651 ~.2~ 1 •••• I C. 7 III O.0.034. aooo. 3•• 14 37.6.1 5.a,'J 1.4.5 lltV970.D.oaN 1340. 1••5a 38.124 5.2.1 1••59 171310.0.0:167 • ,UO. 1.394 23.677 3.03 1.529 219130•O.O,'J•• ....10. 1.911 24.090 .1.03 1.5.1 25.7.0.0.0.19 ao• .3o. a.614 20.2.17 3.0.1 1.626 .l75370.0.04Z0 15640. .1.",00 27.11"0 .1.0.1 1.670 291010.0.031.., 6470. 1hZI. 28••0' .J.03 1.695 2V7••0.0.0.31.1 11110. 7.0.0 a" • .J44 3.03 1.7;t2 30Zft90.o.oz•• 4000. 9.37. 30•• 18 .1.0.1 1.751 3065VO.O.OZ" 3000. 6.7Da 31.779 ...0.3 1.70tl 30",5",0.0.0.310 aOJo. C..".I 32.27. 3.0.1 1.797 .n 1590.0.0.122 .lUD. 5.0.5 ..2.S..,0 :t.D") 1 ••0. 31.1620.0.11113 1.150. 2 ••49 22.7... Z.D3 l.a3. 32,nD.0.OID4 la.80. •••.12 2.3./11 Z.O..l l.a6. 340Z50•0.0231 7D70. 6.16a 30.9..,. 2.5.1 1.89' 347320.D.O..;'\; ....0. ~ • .z10 ,J,j ••U· ~ 2.5. l.la.Z 3llo.210.D.".4a 3500. 11.561 35.20)'1 z.a. 1.9". 35771 o.
Reproduced 'rolllbesl _venable copy.
113
