plane strain fracture toughness data handbook for metals
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AD-773
673
PL NE
STRAIN
FR CTURE
TOUGHNESS (KIC) DATA
HANDBOOK
FOR METALS
ARMY MATERIALS AND MECHANICS RESEARCH CENTER
DECEMBER
1973
DISTRIBUTED
BY
1.
S.
KPMIUET
t Uoo=
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I
I0
13-
The findings
in
this report are not
to be construed
as
an official
Department
of
the Army position, unless
so
designated by
other
authorized
documents.
Mention-c-f-any
trad names or
manufacturers in this
report
shall not
be
construed as
advertising
nor as
an official
HinosMent or
approval of uich products
or companies bvr
tOe
United
States
Government
DISPOSITION
INSTRUCTIONS
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DOJMENTATION
PAGE
READ
Is4TRUCTIONS
BEFORE
COMPL
-IMG FORM
.R T2.
OV ACCESSION
NO.
3.
RECIPIENY'S
CATALOG
NUMBER
4.
TITLE
(nd
Subittlo)
S.
TYPE Of REPORT
& PERIOD
COVER Ed
PLANE
STRAINl
FRACTURE TOUGHNESS
(KiC)
DATA
Final
Report
HANDBOOK
FOR METALS
1. 7ERFORMING
ORO. REPORT
NUMBER
7. AUTHOR(*)
S. CONTRACT
OR GRANT
NUMBER(E)
William
T. Matthews
f
9. PERFOWAING
ORSANIZATION
NAME AND ADDRESS
I*. PROGRAM
ELEMENTrPROJECT,
T?.SK
AREA &
WORK
UNIT
NUMBERS
Army
Materials and
Mechanics
Resevrch
Center
)/A Project:
1T0621059349
Watertown,
Mwassachusetts
02172
W Code:
612105.11.299
AM)M4R-TM
___
ency Accession:
DA OB4707
It. CONTROLLING OI'FICE
NAME
AND
ADDRESS
12. REPORT
DATE
U.
S. Army
Materiel
Command
December
1973
Alexandria,
Virginia
22304
IS.
NUMBER
OF
PAGES
I1.
MONITORiNG
AGENCY
NAME
& AUDOESS(;i
differitt
Ito. Confroline
Office)
IS.
SECURITY
CLASS.
(of this toport)
Unclassified
15..
DWCLASSIFCATION/OOWNGWA
OING
SCHEDULE
16. OISTRIBUTION
STATEMENT (of this Report)
Approved
for
public
release; distribution
unlimited.
17.
DIST0i8UTION
STATEMENT
(of
the
abstract
entered In
Block
20. it differsot
hem
R~pot)
10.
SUPPLEMENTARY
NOTES
It. KeY
WORDS (Ceithwpe
on
et.erae
side
ii
ncesas.w
ind
Identify
by
block number)
Fracture
properties
Tables
(data)
Thughness
Experimental
data
Griffith
crack
Static
tests
20.
ASSTrIACT
(Centhnwe
raentoe
aide It ndcvzary
and Idmnfif
by
block
number)
(SEE REVERSE
SIDE)
1f--p-oduced
by
NATIONAL
TECHNICAL
-NFOPMATION
SERVICE
S
;.~I
S
Oo|)pn {,1rnn
(,(
Con'mo:ce
-
I
I _ I ISpr;n-pjl-e-*d
VP. 2.11-1
t i
147
Z61IiON
Of
t
N(OV
95IS
O33OLETP.
J
*7,
UNCL SSIFIED
Is SECUR11Y
CLASS)FIC&TATON OF THIS PAGE Utmi
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UNCLASSIFIED
SECURITY CLASSIFICATION
o THIS
PAGE(Wh.a
Do m U10
Block
No. 20
ABSTRACT
-A compilation
of plane
strain
KIC
data
is presented
for
metals
manu-
factured
in the USA
and
Europe,
including SO steels, 21 titanium
alloys,
38 alumiuum alloys,
and
one beryllium
material. The data corresponds
to
static
loading in nautral laboratory environment. The
effect
of
tempera-
tuie
is included
in the tables along with the direction
of testing, the
form and
size
of
the material, its composition
and
heat
treatment,
and
the
specimen
type
and size.
(Author)
UNCLASSIFIED
%ECURiry CLASSIFICATION 101 Y1hS PAGEMl.
DOM Fnt.md)
-
-
.
A----
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TA8UF
OF CO0%TENTrS
fitle
Page
I.SrRODUCTION
1
DEFINITIN
CF SYMBOLS
AND
UNITS
REFERLMCES
E
BIBLIOGRAPHIIY
Kic DATA
A. Steel
Tabl-.-
i.
Low
Alloy
AISi
43300I, EN30B
3SN%016,
L%40C
3
11-11
AISI
4140
4
AiSI
4540
5
MAC
7
I'vZ4.
Ni-Cr-!4o-i
8
ii.
Nickel
Steels
9.i--tzo-.
2C
9
9Ni.4Co-
.%
10
9%i'4Co- .4-5C
Hi
10
Nickel
12
iii. Haraging Steel
12
Nickel
13
IS Xi-200
Grade
1.1
1S
Ni-250
Grade,
DID 212,
6100, G110
M.-rval
18
is
18 Ni-300
Gzade, G125
16
18
Ni-350 Grade
17
:
v.
Stainless Steel
17-4
PII
18
17-7 Pit
19
Pl1lS.7"o
20
PilIl83-1o. FVSZOR
21
MU 43SS,
AFC-77,
AaC-20
22
v. Lcew trength
AilS-C,
ASTM A203
:
AISI
1045
24
ASM;
A216
25
AMT!
A'.2,
26
SAS"W!S33
27
,STMfA-42,
ASM A543
28
vi. Intertwdiate
Stt.rth
AISI 1144,
!fl 80
29
ASMTA469,
N-.o-V
30
ASV4
A470,
Cr-Mc-V
31
XASr*
A471,
Ni-r- P--
32
AS 11 AS7-F,
HY 130
33
a.
Ttanium
Alloys
i.
a Alloy
SAI-2.S Sn
34
111
679,
1141
685, .Al-.Mo-IV,
6AI-2Sn-CZr-Z4o
3S
Uwll
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B.
Titanium
ttlloYs
(Cont.)
iii.
u-8 Alloys
I4I SS0j,
I
551,
6AW-31O
36
IA1
6
W
37
IA1-3No-IV,
7A1-2.,1o,
7AI-4'1o
38
6AI-4'V
39
6AI-6V-Sn
40
6A1-6V-4Zr-4Mo, 6A!-2Sn-4Zr-6N'o,
6AI-2Sn-2Zr-3lo-2Cr
41
iv.
8 Alloys
13t'-I1Cr-3A.
8&4o-8V-2Fo-3A1.
11.5
Mo-62r-4.SSn,
3A1-8V-6Cr-4Zr
42
C. Aluminui
Alloys
i.
Copper
Alloys
2(04,
DTM
5020, 111)
66,
BS
177,
BS
L93,
GB-26S
43
2020
44
2021,
2219
ZC-24.
2124,
DTD
S000,
A-U4Gl
46
2613,
RR 58,
DTh
731,
C01
003/41,
A-U2QV
47
ii.
Zn..Ig
Alloys
7031,
7049,
7050
48
7007
49
7075, DID
SOS0,
0TD
5074,
BS
L9S,
AZ
74,
7175
sO
7178,
DT D
363
51
iii.
Zn-Mlg-Mn
Alloys
"700 9.
7005
52
/079
53
DT D
5024,
1'W 50L.
54
7081),
.-
75S
55
iv.
Other Aiinum
Alloys
6061
56
D.
Beryllium
S-200
57
1_
i.l-l
;"
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INTRODUCTION
The
plane
strain
fracture toughness
values presented in this compilation are expressed in
terms
of
linear elastic
fracture mechanics. These KIC values have
been obtained
by
the ASTM'
E399-72
"Standard
Method of
Test
for
Plane
Strain Fracture
Toughness Testing
of
Metallic
Materials" or a similar method.
This
data compilation includes materials manufactured
in the USA
and
Europe.
The
following factors are
involved
in
the
selection
and
interpretation
of the
KIC
values.
Testing Conditions
The
material values shown
correspond
to
quasi-static
lo.ding of
approximately one
to three minutes
duration.
The
environment
is a
neutral
laboratory
otivironment
in
which
no
aggressive chemicals
or
extreme of humidity are intentionally introdkuced.
Specimen
Types
K
values
shown
have
been obtai-ied
from
AST?
ecommended
bend and
compact
tensile
specimens
an d
from a variety of other
specikens:
four-point ben(,
double cantilever
beam,
wedge
opening
loading, side
edge notched,
center
cracked specirens and
a
few double
edge
cracked and notched round specimens.
Surface cracked
specimen
data
is
rot
included in
the appendix since, although this configuration is
extremely important
in
applicatiens, criteria for
validity of
KIC
measurements of surface
cracked
specimens
have not been
establis'ied.
Criteria for Validity
of
Typicv.l KIC Values
The AST%1 E399-72
requirerents are
taken as the
general
guide for validity.
However, since complete
details of
factors cited by
ASli. are usually
not
available, personal judgment
must
be exercised. For
example, although
all data listed pertain
to
fatigue-cracked specimens, the range
of
imposed KI
during
fatiguing
is usually not
repirted.
In addition,
the crack front curvature and the orientation of the
crack
plane with respect to the loading axis are also
unknown.
Other
typical unknowns are the critical
crack length,
the
details
of selection of the critical
load
value,
the appearance
of
the
fracture sur-
faces,
the
details
of
fixture
design
to minimize friction and
the
linearity
of
the displacement
gage.
Therefore, it is
often necessary to assume
that in
general the test
measurements
have been carried ou t
according to good practice.
In term
of
specific
criteria for
inclusion in
this
tabulation
the
ASlIl
requirement of thickness greater than 2.5 (KIC/eYS)
2
, was applied.
Virtually .11
of
the
data
satisfied
this requirement. Although it
would
be
destrable to require
that crack length exceed
2.S (KIC/OyS)
2
,
this criterion wrs
not
rigidly imposed. Tite minimum
reported
crack
length for data
presented
in
this
appendix is 1.25
(KIC/oyS)
2
.
Accuracy of
KIC
Values
In general the KIC values shown are
averages
of several tests. The range of typical data may be
interpreted to be
the
average
shown 10.
In cases
%here the range of toughness
values
was large,
either
the
entire range is
shown
or
the
extremely high
values
were excluded
before computing
the
average.
It
should
be
recognized that
these
accuracy
limits rc'er only to the specific results
obtained
and may not
be
appropriate in
general
for
material
of the s.,me
nominal
compositien, form, and size
which
is
processed and
tested
elsewhere.
Parameters
Influencing
KIC
Where available, the
influence,
whether significant or
negligible, of material form
and
thickness,
composition,
heat treatment,
testing t'.mperature and
material anisotropy
and yield strength upon KIC
is
shown by the series of
data
entecred in the tables. In
most
cases uhere a particular heat treatment
prodces both the highest yield strength and toughness, data for other heat
treatments
are omitted. It
- -
is important
to
note that for some materials, data from the
cumbination
of
composition
and
processing
which leads
to
the
highest
toughness
is
not included in
this
compilation. In those
instances
it is no t
possible.
to obtain
valid
IC measurements
for
the particular
material
thickness of interest. There are
add- ional'-,arameters Vaich may also influeice KIC values vhich are not shown in these tables
since
-the"are
-rtler infrequently reported. Thrse include melting practice, heat
treating
practice such as
the
qize of quenching bath relative
to
the
material
size, and
the amount of
material
straining
during
('orging.
DEHINITION OF SY'MBOLS AND
NITS
Ulits, Symbols
and Nomenclature
Data is presented in the customary units tiw.ed
in
tize
United States with accompanying International
Sotem Units (SI)
it,
arentheses.
The definitton of units and
symbols
for
specimen
orientation and
tylu
are
Liven
preceding the
tabulations.
a) Composition and
Heat
Treatment Codes
Code
Form:
Letter,
Number
Letter
-
Identifies
Composition
lumber - Identifies Heat
Treatment
tetailed Jescriptions of composition
and heat
treaiment are at -.he bcttom
of each table.
The
compositional
values are measured
values
in
terms ef percentage by
weight,
except
when
designated
pps
(parts
per million).
*en only
specified
composition
is
available, the
nominal
specifi.ed Ivel-
are
followed by the
letter W' nd the maximum levels of other elements
are
followed by
"'".
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b) Orientation of Specimens
Code: First letter:
Direction of
Loading
W, Second
letter:
Direction
of
Crack
P'.opagation
L:
Ditection
Parallel
to
Primary
Grain
Flow
Direction
of
Plate,
Forging
or
Extrusion
T: Direction Parallel
te
Largest
Dimension in
Plane
Transverse
to
L
Direction
S:
Direction Parallel
to Sualle.,
Dimension
in Plate Tran,,verse
to
L Direction
ST4: Prection
45S
Between Directions
of Largest
and Smallest
Dimension
in Plane
Transverse
to L
Direction
R: Radial
Direction
C:
Clrcumferential
Dire
tion
If
a
direction is ambiguous
in
terms
)f two of the above definitions, thei
both
dirtctions
are shown.
c)
Specimen Identification
Bend: 3-point
Bend
Specimen
Bend (4
pt): 4-point
Bend Specimen
CT: ASIT
Compact Tensile Specimen
SWIL:
imilar
to
CT, but with different
dimensians
CC:
Remotely
Loaded Flat
Tensile
Specimen
with Center
Notch
DEC:
Remotely
Loaded
Flat
Tensile Specimen
with
Double Edge
Cracks
SSEN:
emotely
Loaded
Flat Tensile Specimen
with
a Single
Edge
Crack
NR:
Round
Tensile
Specimen,
Circumforentially
Notched
DCB: Double
C.ntilever
Beam Specimen
d) Units
Temperature:
F - Degrees
Fahrenheit
K - Degrees
Kelvin
Stress:
KSI
- Kips per
Square
Inch
l'/m
2
-
Mega
Newtons
per
Square
Meter
Stress Intensity:
KSI
in- Kips per
Square
Inch Times Square
Root Inches
?IN
m172
-
Mega
Newtons
times
(Meters)-
3
/
Length:
in,
mm Inches, Millimeters
ft, m - Feet, Meters
RFFERENCES
1.
Kendall,
D.P.,
Materials
Research and Standards
Vol 10,
No.
12,
p 14.
2. Baker,
AJ..,
Lauta,
F.D., and
Wei, R.P.,
Structuze
and
Properties
of Ultra
High Strength
Steels
ASTDISTP370, 1965,
p 3.
3.
Guthrie,
J.L., "lligh
Strength Steel Evaluation
for Supersonic
Aircraft,"
Boeing Co.,
AD818490,
Mtarch
1967.
4.
Vishnevsky, C. and
Steigerwald,
E.A.,
Fracture Toughness
Testinga_
onie
Temperatr-es
A5D45TP496,
1971,
pp. 3-26.
S.
Irani,
J.J., et
al, "The Effect of
Therna"
and
Thermomechanical
Treatments
on
Temper
Embrittlement
of
Low Alloy Steeis",
BISRA IMG/A/81/67, NTIS
PB 10444.
6.
Jones, M.H.,
and
Brown,
W.F. Jr., Review of
Developrents
in
Plane Strain
Fracture Toughness
Testing,
AS131STP463, 1970,
pp.
63-101.
7.
Steigerwald,
E.A.,
Eng. Fracture
Mech, Vol
1, No. 3, 1969,
pp. 473-494.
S.
Kula, E.B.,
and Anctil. A.A..
J. Matis,
N.Y.
Vol 4, No. 4, Dec
1961),
pp. 817-841.
9. Srawley,
J.E.,
Jnes, M.H., and
brown,
W.T. Jr., Materials
Research aid
StandIards,
Vol
7,
No. 6,
June 1967, pp.
261-266.
10. Shoemaler, A.K.
and Relfe, S.T..
"ThL Static
and Dynamic
Low
Temperature Crack
Toughness
Performance
of
Seven
Structurul Steels," Eng. Fracture
Nech,
Vol. 2, ,o.
4,
June
1971, p
319.
11. Wessel,
E.T.,
et al, "Engingering
Methods for
Do5ign and
Selection of
Materials Against Fracture,"
Westinghouse
Research Laboratovie5
report
to U.S. Army Tank-Automotive
Center,
ADSOIOOS.
12. Amateau,
M.F.,
and Steiterwald,
E.A., "Fracture
Charactoristics of
Structural hetals,"
TR1W
nc.
AD611873, January 1965.
13.
Bullock, D.F.,
et
al,
"Evaluation
of the
Mechanical
Properties of
9 NI-4Co
Steel
Forgings,"
Boeing
Co.,
Air Force Materials
Laboratory
Report AFML-TR-68-57 :.4arch
1968. AD
833
650.
14.
Brown,
W.F.
Jr., and Srawley,
J.E., Piane
Strain Crack Toughness
Testing of
Hilh Strength
Metallic
Materials,
ASTM STP 410,
1967, p 18
4 p 60.
15.
Srauley,
J.E., Fracture,
Chapman
and
Hlall,
1.e69.
16.
Bubsey, R.T. and Brcusn,
W.F.
Jr.,
"Crack
Toughncbs
Characteristics
ef
Several
Alloys
For
Use in
Heavy Sections of
IHigh
Speed Aircraft,"
NASA--N-D-4998,
;>nuary
1969, N6t'-17275.
2
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8/10/2019 Plane Strain Fracture Toughness Data Handbook for Metals
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____ - -R - -
17. Carter, C
,.
nt.
Trans., Vol 1,
No. 6,
June
1970,
p 155?.
1F.
Pendlebe-tf, S.L-,
et al, "Fracture
Toughness
and
Crack
Propagation
of 300%1 Steel,"
Lockheed-
Calif -n Co..
AD
676573, August
1968.
19. 'flechd :cal
Properqy Data,
300M
Steel,
"Batelle Memorial
Institute,"
AD
700072, 1969.
20. Amai.n-;u,
Y.F.
and Steigerwald,
E.A.,
"Test.
Methods for Determining
Fracture
Toughness of Metallic
Mat-rials
"
TMR Inc., Air Force Materials Laboratory Report AFML-TR-67-145, September 1967.
21. tre,- '.
C.N. and Goode, R.J.,
"Correlation
of Two
Fracture
Toughners
Tests for Titanium
and Ferrous
Alloys," Nawvl
Research
Laboratories,
NRL 6740,
Jinuary
1969.
AD
683
659.
22. Heitman,
G.H., Coyne, J.E.,
and
Galipeau,
R.P.,
Metals Engineering
Quarterly, ASM,
Vol 8,
No.
3,
August
1968,
pp.
15-18.
23.
Lgis, H. and S.'hUtz,
W., Luftfahrttechnik-R.wfah--tecLni.k,
B
15,
Nr,
7,
1969,
S180/84.
24.
Freed, C.N.,
Eng. Fracture
Mech., Y I,1 1, No. 1, June
1968, p
175.
25. DeSisto,
T.S., und Hickey, C.F., Proceedings
ASIM, Vol 65, 1965,
pp. 641-653.
2.'. Shannon, :.L.
Jr., and Brown,
W..F. Jr., Applications
Related Phenomena
in Titanium Alloys,
ASTISl
:.;,
:968,
pp. 33-63.
27.
Leis,
ii.. d
Schuitz,
W.,
L'aftfahrttechnik-Raumfahrttechnik,
B16,
NrlO,
1970,
S247/251.
28.
Hanna,
L.,
and S.eiger~ald,
E.A.,
"'Fracture
Characteristics
of
Structural
'-.tals,"
TR',
Inc.,
June, ,.oZ,
AD4nlSO9.
29. Greenlee,
M.1
.
"Evaltwa'on of
Ti-8Mo-8V-2Fe-3A1 Die Forging,
Wyman-Gordon
Co.,"
Titanium
Metals
Corp.
of
Amei .ze Case Study
M-61,
February
1969.
30.
Bahanek,
E., "Heat
Trearabi'ity of 11l4
680, Beta
III,
and
T1-8Mo-8V 2Fe-3A1 in
Ieavy Sect-ons,"
Titanium
Metals Corp. of
America, Report No.
31, June 1968.
31. Breadwell,
R. ., and Coyne. J.G.,
The Fracture
Toughness-Tensile
Property Relationships
of
'-veral
Deep Hlardenable
Ti-arium Alloys,"
TICA, Presented at
AIME
Annual Meetings,
Las Vegas,
*i,.o--a,ay 1970.
' -
V.C.,
Guernsey, J.B. and
Buehl, k.L..,
'ir
Force %aterials Laborat.ory Report
.
-'. " 171.
AD856 70.
33. -. 3.?. and Blackburn,
MI.J., Met Trans.,
Vol 3,
No.
1, January
1972, p 340.
34. -or
is,
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