plane strain fracture toughness data handbook for metals

8/10/2019 Plane Strain Fracture Toughness Data Handbook for Metals

1/92

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=


2/92

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

Destroy

this

report when it is

no

IoW neeed

DO not

return

ft

to the origingo.


3/92

UNCIASS-IFIED

SECURITY CLASSIFICATION

OF

THIS

PAGE (10%mn

Date

Ent_

___

REPORT

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

Dvta Ber.e)


4/92

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----


5/92

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


6/92

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

;"


7/92

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

"'".


8/92

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


9/92

____ - -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,

R.E.

and

Spurr,

W.F., Trans.

Am.

Soc.

%etals, Vol

61,

No.

1, March,

1968,

pp.

115-127.

35. Carman, C.:1.

&nd Katlin, J.M.,

AI.

lications

Related

Phenomena in Titanium

AllL.s, ASIhSTP432,

1968,

pp. 124-144.

36.

Hall,

L.R.,

Fracture

Toughness

Testing

at

Cryogenic Temperatures, ASTMSTP4i.o,

1971,

pp.

40-60.

37.

'-ufman,

J.G.,

Schilling, P.E.,

and Nelson,

F.G.,

X,

als Engioscring

Quarterly, Vol

9, No. 3,

S..gust 1969.

38. Kaufman, J.G.,

Nelson, F.G., an4

Ilolt,

M.,

Eng. Fract

e Mech.,

Vol

1, No.

2, 1968, p 259.

39.

Nelson,

F.C.,

and Kaufman, J.G., Fracture

Totl;hness Testing

at

Cryogenic

Temperature.%

AST.STP496,

1971, pp. 27-39.

40. Judy,

R.W.,

Goode,

R.J.,

and

Freed,

C.M., "Fracture

Toughness Characterization

Procedures

and

Interpretations

to

Fracture-S-_fe

Design for Structural

Aluminum Alloys,"

Welding

lesearch Council

Bulletin, No.

140, May 1969.

41. Brownhill,

D.J.,

et al, "Mechanical Properties

hi..ltuling

Fracture Toughness

and Fatigue, Corrosion

Characteristics

and

Fatigue

Crack

Propagation

Ra,;s

of

Stress-Relieved

Allminum Hard

Forgings," Air

Force

Materials Laboratory

Report

AFIL-TR-70-10, February,

1979.

A) 68 376.

42.

Brownhill,

D.J.,

Davies,

R.E., and Sprohls,

D.O., Air Force Materials Laboratory

Report

AFPML-TR-68-34,

Febz

ary 1968. AD 828 772.

43. Westerlund,

R.N.,

et

al, Development of

High

'traight

Aluminum

Allcy Readily

W.pldab!e in Plate

[Thickness

and Suitable

fur

npplications

at -423'F",

ALCOA

Contract No. NAtS-8-5452, October

196.',

NTIS N68-14135.

44. lheyer, R.11.

nd McCabe,

D.E., Review. of Developm'ents in Plane

Strain Fracture

Toughness

Testing,

ASTM

STP 463, 1970,

pp.

22-4!.

45.

Wilson, W.R.. Clark,

W.G., and Wessel, E.T.,

"Fiacture

Tv~ghness Testing for

Conbined

Loading

and

Low to .ntermediate

Strength Metals,"

Westi.aghouse Research

Laboratories, U.S. Army

Tank-

A'itomotive

Command

Report

10276, Noverber 1968, AD

682 754.

3


10/92

46.

Hlanna.

C.L.,

and

Steigerwald. E.A., "Development of Standardized

fest

,nhods

to

Determine Plane

Strain Vracture

Toughness,"

Air

Force Materials

Laboratory

Report AFML-TR-65-213,

September

1965,

AD 475 012.

47.

Walker

E.F.,

and

May,

M.J.,

"Single Edge Notch Specimens of Tao

Ilirn

Strength

Mirtensitic Steels

Tested

in Tension and Bending," BISRA-The

Inter-Group

Labs. of

British

Steel Corp.,

MG/EB/337/67,

1968, PB 180 455.

48.

Davis.

S.X.,

Tupper,

N.G.,

and

Nicmi, R.M.. "Plane Strain rract' re

Toughness

Properties

of

Tirte

Aluminum

Alloys a3

a

Function

of

Speciren

Geometry,"

Air

Force Materials

Laboratory Report

AFML-TR-6S-I50,

Jul,,

1965,

AD 470 276.

49. Davis, S.O.,

Tupper, N.G.,

and Niemi,

R...,

Eng.

Fracture

:iech.,

Vol

1,

No.

1, 1968,

p 213.

50. "Thick Section Fracture Toughness,"

lechnical Document Report ML-TIR-64-236, Boeing-Nurth

Ame-ican,

1964,

AD452

824.

SI. Feddersen, C.D.,

Moon, D.O., and

Ilyler,

W.S., "Crack Behavior in

D6AC Steel,"

MCIC Report 72-04,

Jan. 1972,

AD

737

779.

52.

Gunderson,

A.W., "Preliminary

Mech-inical Property Evaluation of D6AC Steel in Support of the I'-Ili

Aircraft Recovery Program,"

Air

Force

Materials Laboratory Technical Menorandun AiM0,0-6. July 1970.

53.

IHoenie,

A.F., et

al,

"'DEtermination

of

Mechanical Property

Design Values

for 18;i-Co-Mo 250

and

300

Grade

gKaraging

Steels,"

Air

i',-rce Materials Laboratory

Report

AFMIL-TR-65-197,

July 1965.

54.

Steigerwald, E.A.. Revic.

o: '-te:.pment in Plane Strain Fracture

Toughness

Testing, ASTI STP

463,

1970,

pp.

102-123.

55.

Bates, R.C., and

Clark,

h.G.

Ir., 'tans. Am.

Soc.

Metals,

Vol

62

No.

2,

June

1969,

pp. 380-389.

56.

Nelson,

F.C.,

Shilling,

P.E,

.. "d Kaufman, J.G., Eng. fracture

Mech. Vol 4, No. 1, p S5,March 1972.

57.

May,

M.J.,

Pe ie

t

.. evelopments in Plane

Strain

Fracture Toughness Testing,

ASTM S7P

463, 19-0,

pp. 41-62.

58. Swart-berg,

F.R.,

er al.

"Cryogenic

Alloy Screening"

NASA CR-72733 Nov. 1970,

NtIS \,1-10447.

59. Carter,

C.S.,

"Evaluaizon

.

a 1igh

Purity 18.

Ni

(300) Mlaraging

steel

Forging,"

AFML-TRh70

139.

June 1970 AD

871 979.

60. Sertour, C.,

Societe

Nationale

lnij.trieile,

Aerospatiale-Laboratoiz

.'entral,

Suresnes,

France,

Private Communication.

61.

Kaufman,

J.G.,

et

al, "Fracture

fou.h.ness,

Fatigue.

and

Corrosion

CI'rac'ter,stics

of

X-OSO-TE41,

7178-T651, Plate

7075T6510,

7u75-T73510,

X7080-T71.42

and 7178-Th.!d Fxtraed

Shapes"

AFUL-TR-Z9-255.

62. Kirby, W.T., Royal Aircraft

Estabiishment,

Farnborough, IHants, U

6.,

Private

Communication.

63.

Braithhaite,

A.A.,

Unpublished

Work

UK

T)D

P.L.).

64. Rea, M.J., "Research Into the Improvement of

rracture

Toughness of' High Strength Titanium

lloys and

the Reduction of Crackling Susceptibi~ity in Aqueous Environsent," ' .\9 Ltd. Rsch. Div. Rep.

No.

IS55663/1,

March 1971.

65.

Arnitage, M.R., BAC Preston,

U.K..

Private Cormunication.

66. Le-,. K.T. and Hubbard, R.J., "Relationship Betheen Fracture

Toughness,

Plain Tensile Properties and

Metallurgical

Structure

of

a

Titanium Alloy,"

iron and Steel Inst. Publication

120,

Fracture

Toughness of High

Strength

Akaterials,

1970.

67. Nuorood, J.I., "A

Comparison

of the

Strength

and

Tensile

Properties

of

Several

Ihgh

Strength Steels,"

BSC

Report S5 33/70 P 25/PD Oct. 1970.

68.

Nictarnaid, D.S.,

Unpublished

Work, UK

.Dfl

PL.).

69. Bayliss, J.,

Baker,

TJ.

and

Dewey

M.A., "The

Effect

of

%licrostructureon the

Crack

Propagation

Resiatance

of High

.,:rengtb

Steels for Aircraft Applications,"

'ulmcr

Rsch. Inst. Rep. R 30/2/nec.

1970.

70. Maraging Steels,

Firth

Brown Ltd, ,'ublicati.,n,

Niov. !970.

71 ",oberts, C.

"Fractography

and

rEncture

'le .anics:,

U.k.

MEODVEE

Report No.

70505, 'lay, 970.

72. Binning,

MA., Unpublished Work,

U.K.

MOD

P1:).

73.

Cisholi, T.

and

Reuter, P., "Plane

Strain

Fracture

loughness

of Flectror. Beam ,.lds in 1111 .,

5,

and

48

Aluminum

Alloy Plate," Weld and Met

Fab,

lol 39, Nc.. 6, June 1971, pp. 233.241.

74. Peel, C.J.

and

Forsyth,

P.J.L., "Fracture Toughness. of Al-.n-'Ig-qn Alloys to DTD 5C:4"

RUl

Tech. Rep.

73162, Sept. 1970.

~

- --- -

- -


11/92

75. Peel, C.J.,and

Forsyth,

P.J.lE., IOnpuhiished hork, U.K. (K))(PI.).

76.

Simrson, A.R. and lielding, J., "Aluminum Alloy

Plates

- An Evaluation of the

Scatte-

in

KI,

Values,"

UISAReport

I.R/!IISCflAN/

I050, July 1971.

77. Webster, 1)., rrans. Am. Soc.

Mletals,

Vol.

62, Nn. 3, Sept.

1909, p

7',9.

78.

FisL-r,

D.N.

and Repko, A.J., J. Matls, N.Y., Vol.

7,

No. 2,

June

1972,

pp. 167-174.

79.

hauser,

J.J. and hells, M.(;.II., "Inclusions

in

Hligh Strength

and [.earing Steels," AFIMIL-IR-69-339.

AD

867.824.

80.

'Iravic,

B. and Smith, J.II.

"Develnpmrent

of Inproved Iligh Strength Steels for Aircraft Structural

Components" AF,.L-TR-71-213,

ADl73t-81-.

12. Judy,

R.W.,

et al, "Fracture Characteristics of

li-6Al-251o and Ti-OAI-4'

in

3 inch Thick

Sections,"

Naval Research Lab

Report

41R-21SO, August 1970, AD

711-856.

82. Goode,

R.J.,

et

al, "M.etallurgical Characteristics

of

Hligh Strength

Structural N.aterials,"aval

Research

Lab

Report

b405, Nov.

1965.

83.

Johnson,

F.A.,

and Radon,

J.C.,

Int. J. of Fract.

%tech,

Vol.

8 No. 1, 'larch 19-2.

84.

"Mlechanial Property

Data

7049 Aluminum

T73

Forgings,"

Battelle Memorial lastitute, IDec.969.

;5.

Rolfe, S.T. and

Novak,

S.R.,

"ki

Testing of %ledium Strength Hligh foughness

Steels," UI.S. Steel,

Prcject No. 39.018-007(11), August 19b7,

AD) 17 373 -

86. Jones,

M.11.,

Bubsey,

R.T.,

and Broun,

1%.F. J:., "Crack Toughness

Lvaluation of

Hlot

Pressed

and

Forged

Beryllium," NASA

TX67967,

1971,

N72-14546.

87.

Feddersei., C.E.,

and

Elyler,

W.S.,

"Fracture

and

Fatigue

Characteristics

of

7075-T'351

Aluminum

Alloy

Sheet

and Plate," Battelle

Menorial Institute,

MEarch 1979, AD714019.

88.

Spaeder,

q.J and Hurphy, W..1., J of

MIs

., Vo'a. 5,

o.

1, llarch

1968,

pp.

116-133.

89.

Freed, C.N., Sullivan, A.M.

and

Stoop, J., "Effect of Sheet Thickness on the

Fracture Resistance

Kc

Parameter

for

Titanium Alloys," Naval

Research Laboratory, To

be

,oblished.

c

90.

Webster, D. Tranr-. Am.

Soc.

Met.,

Vol.

69,

No.

4,Dec.

1968, p 816.

91.

Robinson, J.N.

and Tuck, C.11.,

_ng.Practure

Mech., Vol. A No.

2,

1972, pp. 377-392.

92.

Coyne, J.L., "The Beta Forging of litznium Alloys," The

Science, Technology and %pplicationof

Titanium,

p 97, Pergamon

Press,

1970.

93.

Hunter,

D.B.

and Arnold, S.V.,

"Metallurgical Characteristics and

Structural

Properties of

Ti-8Mo-8V-2Fe-3AI Sheet, Plate and Fcrgings,"

The Science

Technology

and Applications of

Titanium,

p 959, Pergamon Press, 1970, also U.S. Amy

Mlaterials

Research Agency Report

W'ALTR 405/2-14,

October, 1966,

AD 648

244.

94. Boeing

Co.,

Commercial

Supersonic Transport

Progran,

Phase

II-C

Report

rA-SS-66-S, V'.66,

AD 806 980.

95. Curtis, R.i.

et al,

Trans. An. Soc.

Metals, Vol.

62,

1P457,

169.

96. Hleitman, G.IE., J.

of

Metal.;,

'lay

1971, p 37.

97.

Jones,

R.E., "Mechanical Proper~ies of 76,49-T73

aM- 049-T76 Aluminum Alloy Extrusions

at

Several

Temperatures," AF.41.-TR-72-2, Feb. 1972.

98. Nelson,

F.G.

and

Kaufo.L, J.G., 'Fracture Toughness

of Vlain and Welded

3-in. Thick

Aluminum Alloy

Plate," Presented

at ASTi

S:xth

National

Symposium

on

Fracture

Mechanics,

Philadelphia, Pa.,

August 1972.

99. Jones,

R.E., "Fracture Tcughness

and Fatigue

Crack

Grouth Properties of

7175-T736

Aluminum

Alloy

Forging at

Several Temperatares," ADIL-TR-72-1, Feb. 1972, AD

748

257.

100. TIMET Div of Titanium

Corp.

of

America,

Project 99-4, Report

No -4. ug. 1. 970.

101.

Seagie,

S.R.,

et

al,

Development

of

a

Deep-Hlardenable

Allny for !ntermediate

Temperature

Applica-

tions,"

RIlIo., Presented at the Second International ConFerence on

Titanium,

Camabridge,

Mass.

May

2-5, 1972

(to

be published

in proceedings).

102. Etuettich,

N.J., et

al, "The Toughness

of 2-1/4%, and 3-1/21

Nickel

Steels at Cryogenic Temperatures,"

Welding

Research

Council bulletin No. 165, Sept. 1971.

103.

Greenberg,

11.D.nd Clark, N.G., REetals

Engineering

Quarterly, AS'l,ol 9, No. 3,

p 30,

Aug.

1969.

104.

Seman, I.J., et

al, "Fract'.re

Toughness of Low Toughness Steels," B,-ttis Atomic Power

Lab.

WAPD-Tf4-

89S, Hay 19%, NrIS N71 j8075.

5


12/92

105. Wessel, E.r.,

Eng. Fracture

Mlcch., Voi

1,

No. 1,

pp. 77-103, 1968.

!06.

Wessel,

E.T., "Linear Elastic

Fracture

Mechanics

for Thick-1valled,

Welded Pressure Vessels:

Material Property

Considerations,"

Practical

Fracture

Mechanics

for

Steel,

Chapman

and

Hall,

London, 1969.

107.

Landerman,

E.

and

Yanichko, S.E., "Determination

of Fracture Toughness of

lleavy-S*ction Pressure

Vessel Steels

Using a Fracture

Mechanics Approach," Welding

Research Council Bulletin

No.

120,

Feb.

1967.

108.

Greerberg,

11.D.,

et

al,

Lng.

Fracture

Mech,

Vol.

1,

pp.

653-675,

1970.

109. Thornton, D.V., Eng. racture Mech, Vol. 2, pp.

!25-143, 1970.

110.

Harrigan, H.J.,

"B-I Fracture Mechanics

Data

for Air

Force

Handbook

Usage," Rert

TFD-72-S01,

North Americc.n Rockwell,

Los Angeles

Division, Los Angeles, California (April

21, 1972).

111.

Chu,

H.P.

and Wacker, G.A., J.

of

Mtts, N.Y., Vol. 7, No. 1, March 1972, pp. 95-9:.

112. Moore, R.L., Eng.

Fracture Mech.,

Vol. 4, No. 1,

March

1972, pp. 51-63.

113.

Roberson, J. A. and Adair,

A.M., Met

Tras.,

Vol.

3,

July

1972, p 1967.

114.

Webster, D., Met Trans., Vol. 2,

No. 7,

July 1971,

pp. 1857-1862.

I1S. Rich, D.L.,

MCAIR IPXD

Data

for Fracture Mechsnics

Engineering and

Design Data :landbook,"

McDonnell Aircraft

Company,

McDonnell

Douglas

Corporation,

June 1972.

116.

"Damage Tolerant Design

Handbook,"

Metals

and Ceramic, Information Center MICIC-IIB-Ol,

December,

1972

AD

733774.

117.

Cha't, R. and

DeSisto,

T.S.,

"The Fracture Toughness of

Three Heavy Section Titanium

Alloys."

*lMRC

PTR 72-S Octobei 1972, AD753

919.

118.

Adair, A.M.

and Roberson, J.A., "The

Influence of Processing

Variables on

the

Structure

and

Properties of

Extruded Beta III Titanium,"

AFML-TR-70-277, March 1971.

i19. Deel,

O.L.

and

Mindlin,

IH.,

"Engineering

bata on

New

and

Energing

Structural Materials," AFML-iR-

70-252,

Oct. 1970.

120.

Dccl, O.L. ,rJ lindlin, If.,

Engineering Data

on Neu Aerospace Structural Materials,"

AFML-TR-72-196,

Sept

;972.

121.

Broadway,

M,

Imperial

M,.tal Industries

Ltd, Neu

Mletals

Division.

122.

hanhill,

R.J.HI., ct al, "l'ractkre

'Toughness an4 Sub-Critical

Crack Grouth in

a

High

Strength

Titanium Alloy (1.11

50) National

Aerospace Laboratory (\LR)

Report NLR TR721071J

Aug. 1972.

125.

Webster,

D., "Efftct

of Crain Refinement

on the Microstructure

and

%lechanical

1roptr-ties

of

434aM,1,

Sunnarv Report

1)0-25220,

The

Bing

Company,

Renton,

hash.,

ARPA

Contract

N0001

4

-

6 6

-L-OSb5 Nov.

1969.

124. Shabbits, W.D. and

Logsdon, W.A.,

Journal

of

Testing

and

Lvaluation,

Vol. I, No. 2,

March

1973,

pp. 110-118.

B B

OGIRAPHY

"Standard

,lethod

of lest

for

Plane Strain Fracture roughness of Ietallic Mlaterials: 1. 399-72 1972 Book of

ASTM

Standards,

part 31.

"Proposed British Standard for Plane

Stratn I racture

Toughness

t'lC) Ie.eting"

iHSP\

Report Ik, 1

B/350/09.

Review

of

Develonnents

in Pl.ne Strain

I'ractuie

loughtiess

restin

1

E ASl

STP .163,

1970.

Plane

Strain Crack

Touliness r,,ting of Nigh Strength 'letallic Materials,

ASP,

:1P -110,

9),'.

Fracture

roughness

lestiny,

and Its Ap~plieation-,

ASIl

Sil'l'

381, 19t,5.

Aerospace Structurtl

M!etals HLandhook, AI'Il-TR-oS-I11, 1972

Publtcation.

"Planz!

Strain Iractare

Toughness Dtatat for

Selected Metal.- ..

nd \lloys," Battelle 'lemorial

Institt., , D'IIC

N port 5-28,

June

i:49

Leis,

Ih., and Schiit:, h.,

"L'alua tion of Neu

-\ircraft

Structural

'laterials with the

'lethou of

practure

lccoanics" Air

lorce S~steo- otnmand, foreign

Technology,

Ilt ision

Tran.slation

|T11-itF 23-1219-71,

Poe.

1971.

Steigcr'ald,

L.A., "Plane

strain

I

racture

Toughness for Handbook Presentation," \I'll-TR-(,7-

1.7,

Jul% 1907.

Goode, R.J., et

a', t'tJ.gigal t haracteristic.-

of high

Strength

Structural

'Iaterials", 10th Progress

Report.

Naval

Research

La:, Leport ,*4.

lyr,ril 196.6.

6


13/92

Puzak,-P.P., et

al,

"Metallurgical

Chrracteristics of

High Strength

Structural Materials,, ilth Progress

Report, NRL Report

6513, Aug.

1966,

AD646

52.

Goode, R.J.,

et al, "'letallurgical Characteristics

of

High Strength

Structural

Materials",

12th Progress

Report,

NRL 6607. Sept.

1967.

Freed,

C.N.,

Goode,

R.J., and

Judy,

J.I. Eng Fracture

Mich, Vol. 2, 1971,

pp. 359-371.

Forney, J.. "Fracture T.%ughness L-aluation

of Titanium,

Aluminum

and Steel" Frankfert

Arsenal

Report

M66-20-1.

March

1966.

AD

632

926.

Witzell, W.E., "Fracture

Data for

Materials at Cryogenic Temperatures",

AFT4L-lr-66-257, Nov.

1967.

Wit:ell,

W.E., "Fracture

Mechanics - Plane

Strain Characteriatics

of

Severa; Aaterials at

Low

Temperatures",

General

-ynamics Report

GDC-ERR-A.-1228, Dec.

1967, AD

854 611.

Cottrell,

C.I..W., and

Mn, "N.J.,

"Lineor

Elastic

Fracture Mechanics in

the United Kingdon

- Work

of

BISRA

Fracture

Mechanics (hligh

Strength Steel)

Committee ,

B SPA Report WG/E/160/69,

%TIS PB 185

931.

Walker, E.F.

and Hlay, H.J., "The Effect

of Pro-Cracking

Stress on the

Plane Strain Fracture

Toughness of

SSeveral

lartensitic Stees". BISRA Report

MG/E/W,6/68.

Walker, E.F,

and

May, M.J.,

"Collaborative

Fracture Toughness Programme

Using Single

Edge Notch Tension

Specimens", BISRA Report MG/E/401/6u.

Priest,

A.H.

and Mlay,

..

J., "Fractu:'e

Toughness of

a

Series

of Experinental High

Strength Steels",

BISRA

Report MG/E/404/66,

NTIS,

PB

185 433.

Krafft, J.M.

and Mlulherin, J.HI., Irams.

Am. Sec. Metals,

Vol. 62, No. 1,

March 1969, p

64.

Urban,

R.J., "Plane Struin Fracture

roughness

of Large

D6AC

Steel

Specimens Heat

Treated to 220-240

and

260-280 KSI Strength

Level",

General

Dynam:cs, 1964,

AD

437 887.

Malters,

J.N.

and White, J.L.,

"Development of Fracture

Toughness Properties

of D6AC Steel for

F-111

Applications",

AF4L-TR-70-310,

Jan.

1971, AD

882 120L.

Hlarmsworth,

C.L. and Iervay, R.R., "Fracture

Toughness

Evaluation of D6AC Steel

in

Support of

the

F-Ill

Aircraft

Recovery Program", Air Force Materials

ULboratory TM-AFL/LAE

71-2, Dec.

1970.

V'ishnevsky, C. and Steigerwald, L.A.,

"Inflirmnce

of

Alloying Elements

on the Toughness of

Low Alloy

Martens.aic

Ifigh Strength Steels,"

Army Materials

and Mechanics Research

Center

Report AM161I

CR-60-09(F)

Nov.

1968.

Ilauser, J.J.

and Wells, -l.G.IH., "Inclusions

in IHigh

Strength Steels,

Theii Dependence or

Processing

Variables and

Their Effect on

Engineering PropertieV', AMIL-TR-68-222,

Aug. 1968.

Craik,

R.L.,

et

al,

Metals Engineering

Quarterly,

Vol. 9, No. 3,

August

1969.

Kalish,

D. and

Kulin, S.A., "Coupling

of

Ultrahigh Strength

and

Fracture

Toughness in

Steels

by Means of

Thermo-echanical

Processes",

ANL-.TR, 68-69.

CIE

Ault,

R.T.,

et

al,

"Development

of

an

Improved

Ultra-hligh

Strength Steel

for *Forged

Aircraft

Components",

-AF

M -1-71-27,

Feb. 1971,

AD

882 806,

Rolfo,

S.T. and Gensamer,

:1.,

"F-acture

Toughness Requirements

for Steels",

U.S. Steel

Project

ARL-89.01?-O,

Coatract NOBS-94535,

July

1968, AD 855 923.

Z= Carter,

C.S.,

Met

rrans.,

Vol. 2, No.

6,

June

1971, p

1623.

Cirter, C.S.

1

-he

Effect of

Heat

Treatment

on Fracture

Toughness and Subcritical

Crack

Growth Characteristics

of a 35So

Grade Uaragin; Steel",

Boeing Commercial

Airplane Group Report

D6-22978, AD

692 169.

Simder, G.J.

at

al, Trans.

Am. Soc. Metals,

Vol. 60. 1967,

p 418.

Tuffnell, G.W.

and CArns,

R.L.. Tra.saction

quarterly,

ASH,

Vol. 61,

No. 4, p 798.

Brand, R.A.,

and

Rolfe,

S.T., "Procedures for

Dete-m';,ing KIC

for

180/210

Yield

Strength Steels", US .

Steel

Report 40.018-002(23),

Dec. 1964.

webster,,D;,

"iDevelopment of

a

High

Streng.l. Stainless

Steel with

Improved Toughness

and

Ductility",

Boeing

Co. Report

06-25443,

Scpti

1970,

AD 712 724.

Judy, R.K. , et

al,

"A Characterization

of the-Fracture

Resistance of Thick

Section Titanium Alloys"

NRL

Report -74Z7, July

1972,

WE

Gooje,

.R.J. et al,

"Procedures for-Fracture-Toughnets

Characterization

and interpretations

to Fa-lure-

Safe Design

Structural Titanium

Alo-4, NRL Report

6779. Dec. 1966, also-

.ld Res.-Council gull

Feeny,

J.A.

and Blackburn,

M.J., tTrn. s Vol.

1, No.

12,

Dec.

1970, pp.

3309-33:4.

77

- ~ ~ ~.

-g

-- Q


14/92

Dotson,

C.L.. "Mechanical and

Thermal

Properties of

lligh

Temperature Titanium Ailoys", AF4L-TR-67-41,

March 1967.

Coyne, J.E., et al,

Mtals Engineerinv

Quarterly,

Vol. i, No.

3,

August

1968.

Carman,

C.H

.

et

a2, "Plane Strain ?r~cture

Toughiess and

Mechanical

Properties of

SAl-2.SSn

E1,1

Titanium at Room

and

Cryogenic Temperatures". NASA-CR-S4296,

April 1966, N66-30117.

Shannon,

J.L.

and Brom.,

W.F.

J.-.,

Proc.

ASfl4, Vol. 63, 1963, p 809.

Petrak,

G.J.,

"Mechanical

Property Evaluation

of

Beta Forged

Ti-4A1-4VW, AFML-TR-70-291,

Jan.

1971,

S~AD

720

828.

Petrak,

G.J., "Evaluation

of Threr.

Point Fatigue Cracked

Bend Test Parameters", AFML-TR-68-327, Nov. 1968.

Schwartzberg,

F.R.

et al,

Metals

Engineering

Quarterly, Vol.

9, No. 4, Nov. 1969.

Schwartzberg, F.R.,

"Cryogenic

Alloy

Screening",

NASA-CR-72617, Feb.

1970,

NTIS

N70-19729.

Lorenz, P.M., "Compatibility of

Tankage

Materials with Liquid Propellants", AFML-TR-69-99, May

1969.

Lorenz,

P.M..,

"Effect

of

Pressurized Hydrogen Upon Inconel 718 and 2219 Aluminum", Boeing Co., Aerospace

Group Document D2-114417-1,

Feb.

1969.

Zinkham, R.E. and

Beker, C.,

Eng. Fracture

%ech., Vol. 1, No. 3,

April 1969.

Kaufman, J.G.,

et

al, "Fracture

Toughness, Fatigue and Corrosion Characteristics of

2020-T651,

2024-T851,

2219-T851

and

7001-T75 Aluminum Alloys",

AF ML-TR-66-291 AD 802 836.

Gerdeman,

D.A.,

et al,

"The

Evaluation

of Aerospace

Materials, AFML-TR-68-53, March 1968.

Radon, J.C.,

Canadian Metallurgical Quarterly, Vol. 8, No.

4, 1970, p 297.

Van Leeuwen,

H.P.,

et al,

"Correlations Involving Properties

and

Microstructure

of AI-Zn-Mg Alloy Forgings

of

7079 Type",

National

Aerospace

Laboratory Report NLR-TR-7010S,

Oct.

1970,

N72-24S97.

Paris, P.C.

and Harris, D.O.,

"Engineering Evaluation of the Status of

Utilization

of

Beryllium

From

Viewpoint

of Fracture Mechanics",

U. of California, Lawrence.

Radiation Lab Report

tCRL-72422.

Green, A.T.,

et al,

"Subcritical Crack

Growth

in Beryllium

at -520F",

Aerojet-General Report RPN-S-523,

Oct. 1967,

N70-30070.

Harris, D.O.

and

Donegan, ll.L.,

J. of

Ntls, N.Y., Vol. 3, No.

I, March

1968,

pp. 59-72.

Hiarrod,

D.L., ,lengstenherg,

T.F. and Manjoine,

H.J., J

of ,tls.

N.Y., Vol. 4,

No.

3,

Sept.

1969,

pp.

618-

632.

Repko, A.J.,

et

al, Evaluation of

lietallic Naterials in Design

for

Low-Temperature

Service,

AS1M

I'P3042,

Junc 19.".

Fedde,-

:, C.L.,

et

al,

"An Ixperimental and Theoretical

Investigation

of

Plane

Strezs Fracture of

2024-

T7351-Aluminum Alloy Sheet

and Plate", Battelle

,em.

Inst.

March

1970

AD 714 019.

Irwin,

G.R., Journal

of Basic

Engineering, ASIE, June 1960,

p 417.

8


15/92

-T

O

v

~

~

~

S

4

4c

0r

0

C;

0.

.i

0

T-

.Mn

o n

V

urn

a~

.0

n

In

in

7

.L!0

t~~~~~i1

.1N

N

N

N

0 '

O

o3

n,

~

~

U~

~~~

~~~~

'a0

0

0

%

'

a

-2

-3

-3

r0

.

-

L:

r-

CI

(I0

0P

a

a

c

c .c

39

.%

z1

a*

QI

00cc

00%

~t

,

0

0

-

- - -

-

0.,

T

M1

-

.

-

0

0

0

0

0

L

0

5

0

4j

.JC

C0

L

? o

11

-

~

~

~

~

r

T

'a

'

'

a

0

~In

%~t

No

'n.7'

~xv

Nn

l

It"

0

i

tr

nc

. L

~L

%

0.

S.N~

U

U

en

r7

L"

C7

.

0

04n

N

-

CC

13

1-1 IQ,

10D

I'D.

7O

0lu.

i

r.-0

--

-

-. -6.-

-

o C, o.

n

I1

%

ulna

,

-

d

a

m

s .

a

j

cc

1 L,

c

'a.. 00U

z

c;


16/92

rTT

Lh

c

Coo

C

o

oc

t

t

C'

in r.*0

oo. Not -

i C 4

5h~~~~~g - o Ctg.t o C

o~~

a C)

0

-a.

0%- l m N a

n .ru

0. 0

ob 0.?

.C

O--C

-

Ut -o

w~--

~

'

a-

Go In

921a

.5 5' N'a

at

it

Z I..

.'

00

130

N

-~ac

-

0

U,

~

0f~-

; c

nL n 4

am

o ' C . 0

N0-. - -


17/92

0 I

- - - ---

-

-

a

S

0

W

v

0

0

10

1

.

Nn NAA 0n %n M0 'n. N

0

N

.0

.

0

0

-4-

a

.

i* Q.

go

o G

)

cc

c I

0 0

0

LA

NNA

0

~~C

;

0 0

0'

0

Z-

- -

*U

9.

U M

c+ LL

N ~~~

~ ~ ~

0

0 N0 N0

- 7

C:

10 I

e4 Q ( ; 00

0

Q

0 0

0 0 0

0

4 L

0o

0 D n

n 4 Go1

M.

T

go

0~ 0n

m

0

00

Cc, C8

0

00

0

0~ ~~~~~ 10 Q m'

.0

.0

4

0

.

N

- 0

N

0N

0

oa~~~ -1

.z

LzJ

.*

p ;

= R 9

0

-

0A 0M 0

0

0o Ol 0

0;

a

= .. N

n

00

0 m

0 C7

0I0n

0

0

m

m

m0I

0

a

tF .

tC

z

a

e 0

0

N1 0

0!0

0nC1 0 0

y

C,

CN

0

NM

(

!

NO 0!0'

2

00000

n

0 ?

rT

a5

00

0~

ASN

'

7 7

'

-j

-l

O

f-

(L

LM

.

L

'0 N

"00

4, 00000

0

0o 0i

0 N N N 0

0 0

N .0-.a N

to

u Li

icB

r

cL

OS~ 4.3 a

0

N

LU

S.

ts

a, 0

U)

9L

w

C

---


18/92

'.I

4444

4e4

0 c

-

t

~

6 L.

v 0 In

I

0

0

Q .7 -,

U.

r4

f,

0

C,

*-

c:

.

*L

a

4"4~~C

C

C!

'

*

8

o~~c

0q

t

0

oo

-l

t8

.3 4

U

i-

jz

N

< 32

0

o

.. tIN

U3j

. C

8 ".

t

0 4.

- i~

I~ .'.

t

c

'0

U


19/92

ann Is

- -

.Z

*

- In o7 cr. c. O

. . . .h . . . . ~ . . .

. .

(( C ' ' '

'a -

-

h

-

- -

'5'

'A4

c4

U

C

unA

a.oo

Ina

('a

%

I

34 b

- h

Oh

-

-

Oh

-

-

-'

-' -' -'

-h

-' -~

a~

0

0 oh c.

N O ch 0 cca CC Cl

0

Li

-z

Ir

cc.

n

hnin

vn

0 0 0 h O C O

;2

In. 7

.

7 7 . 7 . . 7 . 7 .

-I In Mn

Mh

h CC CCV

C

(C *

N

-

4

C4

'7 '7 '0

'

-

N a C C 7 ( 4 '7 ('7 (' a

i

UU

-7

co~O

~

U'......- "7 7N CC

CC ('

O

-

C

-

CC N CC C C

'a

C

i

o -

7 V h C in in N CC N C-

UC

u~n CC i in Oh C

f

IC3

C

~~ ~ ~ ~ ~ ~ ~ c uh'

c

C

C h CC an

0

(a

0 i h 0

O

h~~~

~

cil

O

* 0

O h

C

/ C n

C

C

C

~~~~~~~c

. N *C O C i

/

O h

O h 0

(4

CC

CC N

O

~~~-~1c

.

- u

n (4

CC

Oh 0

a

h C h CC

0 O n C .

D6n

Oh

Oh r4

u n

i 4

h

O h

i

-a.

'-

u'a44


20/92

Cl

ot

-

0.0

- .

S 6

.

.wL

As *=

u

Q._

U-4

m

r-

.-.

5M

1.

n

'20

a

a

.

al

aa

IAj

r

-.

at.

0

Y4

.2C

00

.

I

ol7

.

M-

01

Ln 1.

1.

Ln

s

V

W ,----

-1

t-

CA~~O VI

0zM~nO

o

CS.

"15Ci


21/92

Oh

a

in

n

h

0;

-:

C.

P.

P

C

U;

CI

00

0 8

n

a~~

0

0c

u

u

4

0

0

I

.2

03

V la-

t

be 4n C-

cc Ch N

00.00

LA

-.-

s

-

~~~~~~0

S

U U. 0 .

*

*

a

-T

n

OD

:;

5

1

n

w:

2AO

T in

-T

Q

M ~

n

W.

n *

Lr)

N 0

-

W

a en n In

C4C

*

sC

C

n

C4

CIA

C

.00

.0

N0

o.

us

M

Cs

U.s~~

.

C

s S.

C

S

-C,

L

0

.

4

0

.

0C

0

0

.

0

.

0

.

In~e

x0 %a

0

r40

0

.0N

.

0

.

I)

O

0

.

N

0

NW

Nc

N

-

-

N

N

6 Oh Oh

xh Oh Oh 0

-.

" h -

h O O

h

0

0

h

O

00

0.

a,

Cs1

0 04

M

.

CL

so


22/92

ar

.u

..

V~

r

rz

- 1~~in

n

M.

Lt.

2. Lt.

CD

L4

1-

Ln

00

ifn

Do %

0

0 3

C..'

a 0

0 :0

-

0 0 0k-o ~

* +2

-

0~~L

.0

..

C.0

in'-

&

(n

to~

to)

N~L N

>IS

I;

;

1In

+00

0nW

44~~I

M"

".IU

1n2-rMLnMr

c.

in

on T

-

-0

-e a

.

12.1

r%~

*..

=

W -W

-

-

2. v vIn

v0 InonI

CcE0t.'rJ0';.

m

N

InP2W-nnonInL

..

~ ~

~

~

L0

0

240

Ob

tjuu

1 9

LL. .

~~g

~~~~~

M L,

0 0 0

0 ,.0 .

.N

N .

!9%9%

N~~~~~

0;;~

cicica~

0 .

l

--.

''.

-40

000000

..

n

--

*

-.

1-

OD

00

0

0

0

v

Ms4

2b

.5.

AAg

.0 ~~

~

~

~

C

m I

0

0

0 0

v2~

0 f0

n-.

N

*t'.0

W 1 % 0

-

.-

93~


23/92

.3

CN

;

0; C;

C Nc

C :7- 71

7%- n

rl

C,

l C

C; C

C

;

C;

C

C;

C ; C C

-a -W

q 0000 0 0 C' 0 0; 0 0

M 00 cc . c

o l ~

nF

a

C, - -

- - - - - -

I,-

-

-

-.

-

-

N

-

N,

0:,

o 0 0 0 0

o 10

0 0D 0n 0

- N -

u) U)

-

u~ u 0

IS .1 f,0

0

N C 7 C C ~ 0

.

q~

mO

.1 f, Zo

I.

0 N

U 7

in

C-

C

*1

C )

U

C O S

U)

0 C ) C C N

C C - N001

U W. N

~

() C ) 0

U) U)

0

UIn

N N

U

o c

Lc

;-

Z;U0 S

- -

N 0 - CI

"I

on

m

-0

P0

l

o

o-

U

Ln g or 0000

0I

tr

G

N

O

0

A)

0000o

*

.99

.9

u

Ac

r. Go

F-I 00%

Lno

r.

C6, 12 .

-NU


24/92

X 9:

CC

CD

S

In

41

In CS

r-

In

a.

;

Q c

.-..

C.z

ame

C

~k0

i90

o

n a

*


25/92

Cl

i

a

oU

0

00

00

~~

C

on1

CIA

C; C;C

71I

-I

0 7 .7

' 0 4

00 0 0

0

0 0 00

0

,

rt E

7iC'

't

C

007

ccLca

"L0

C:,

ti

ID

l:

000,

17,3

~i00oj

c:

1~ .

.7 7 .7 .7

--


26/92

.7 C

In

*

-

*I

. *I

-

In

- -

71

ig

*

. - o

*1

.

In

7*

*

0

0

C,.

'N.

.7

*I

Cl

-

-

0

I,-

'C

o

-

*7

In -,

U -

&

-. -

V

Cl

. *0

41

l In 0

- In -

7

-.

I

.0

Cit

-.

7*

'I

.-,

.

*1

'NJ

--

0

-

-

.-

it

00

,,

-

I

Z..

-

-S.

-

-

7*

-

U

7*

7.

E-

--

-'In-

o

In

Cl-?

Cl

S.'-

In

"a

-

71


27/92

4-

3a-

c

m.

"I on

ult

ts

&A- n- I-

Nn 4

o 4) _o o oa

.4 9

V

9

'm in

0n 0 0 t0

00

-

0 0

4

Ch

Go

go

4

.

.

t*

ID

'-~~

-e - -C C

4 N . .

4

.

~~coo

CA

e

4

c o

o

LA

LA

t, t,

t0 Go

-

t4

M

'C-.(1

Cl

Iq

a

~~~~~~

-3.,~

- ~

.

,9~

0~~~-

0n

Q4

0

4

C4 CA

f49 0tq0

.

Icj

64C

0 .

404

00!

16

r0

0i

0

in


28/92

a 14

*~~~~~~~ 40

4

40

- 0 0 .

A'

; 0s a

0 C3

0

N 4

0

0

0 04

can

-r -e1 e4

-

* 1

l0e

.o

0f

n

In

n

Nn

In

n

a

C)

'0:

C4

40

10N

'

0-

-..

J

-

0 04

Lt u -nI

N N 'oq 0 'D 4

u00

U)

CA i Am

1 C D I W

t. 100 01S

go

-

0 0 0 0 0 0 0 00U)0

00 0

a

aM 0

04 '0

4n~~~

.0

n0U-g . 4L

Oa

r= w 6M a

N

a

a 0

C;

0

0,

0n!

0S.

-

00'U

.

-SS %t-z,-'&

4

0'-.,

0c 0n N, '0

W)0 a 0

0) 04 0 9-

'

'0~

~~~~~~~~~~~~

c0

0

'C

0

' 0 ' 0 N ' 0 '.

6an tn~

fq i

'04

,

0

7 el C, -q

0 (4

al 0 0

c.Cooo

m u ra

4U

L).3

4M....

1. r4 a.

-

4 '

0

' 0

Un

r- (4

0

U 0

A 4 r44'

-'

.~~~- '0ca0 4

160 Z"0

'0 04.0

04.


29/92

.4*

L40

01

NR r4

I..

c;

c

Q

~

[?

to

a

o

0a

0

SW.~

to

N

N

N

a

g

Ie.

-cc r.. N-

-c

.C40

)

Ag

t,

'-.

'-.

v)

fo

t

.

N

-n

C :

,

1*

0 00

4-fl

r,

m~

NL

N

G

N

0 0

'

U

It Q?D

0)c'

c;

)0)n

C'

N

C'S

0

D

-

0 0 0 U )

4*~~f

0

N

N

N

UI

coo.-

s..

ftU ; 4C

amoo

IL

0

0

0

-a

0

4*.*u*

.

00

c;

D

I.e

-n

0.f

0

0

aIn

'0

U

0

. .

..

)

.


30/92

ft~ ~

~

~ d

__

_

_

_

_

__

_ _

_

_

3

n m 4

4 In

A

;I

8 0a

.U)

'D.

o

0.) U,

0

Q

Cr4 -

-

-

-

00 Oh

U) 0

M

h

N

f,

L

'0;

N

C4

.4

IM

Z

-3 -3V)S

~L

n N0

m0

0 0

Q

O

N00

Q C3

-G

V

Oh

'0

N

1.-Ieta%

N 0

cc

-

NnNiN

Ci)~~~

a0 C5, Q

)

'

* U'

(j~

N 0000

0

U

-C6-

~

.0.N.

160

NV

0

.4

.

.

..


31/92

1 0

0 0

r* "A M

a!

o0

0

-

0

0 .

cb

Al;

C;C

. .L

~~~~~

CDC

0 1

N~

~~~

0 00

008. 01

00

0

0

0 -

-

w-

-1

-

N

'

1

-

$.

*n*

r4 Go 0)

--

,,

0 nL

nL

04

.

.

. . . .

c

In00

mV

~

2lt

4;v

0

0 0 0 0

N

U)

uu~uId

CrCA

*~~U

6L

.0

In-

n~

U

C~

~

'0

-) - -

)

- 0-

01 N Nz

*Ir,

c m m

N5

0Q

o-

L 0- 0

0;

0

01 0- 0

U )

01-

L!..

*Q

0

1

-l

n

-

1

~CLI6UU

-~~~~~~~

'--

"-'~

00

N 0 0 01

U)

N

0

0

Q)U

I

0~C U) '

00

0

AN8

0 -

4'

*

~

-

'0~~~~t 0n

wn u

0 '

N

-

I

'0

r Ud) U ) U)

0 U

0 0 U

=

UU

9m

4'% 9

. - .'

~ '. .

.

0

MORE

0

I

0 01 -

0 0 0 0N

..


32/92

In

1.. 0

na 0C

aq a- eq a

Inco

cow

n

n

In LA

an

r!

Go

0o0

e4

a,

Qo

'0

c o

co v

n

an_ j u L

m - am

T

w

cc

r0

tC u) (qa.Na n

u.

-

lo mn

cn anD an eq eq

aon

a

n a 0 o

co Co '0

Go

Cm

o

co

Go N7

I

o 0

e q N N e

c;

0

Q o

o0In

a a

7

o a

0 0 0

o cl

seq ~

-a jag Co an

0 Co Co

~~~~Anto

. o . o N

n

' d

o

~ o o 0 o C'0

o d C C q o 0

N~ ~~~ ~~~~q .2'

e

q ..

eq

e q e q . q e

Ca

-

n

to

Cd

-a 0

xo~

a

=

K N N N N N

- -- a -

96

u-a.a

.----

aa

o -

00

n

0 0 n 0 0

Cd.

..

eq Co e 0

Co a-

-. . -

-

4: aca a

.

U


33/92


34/92

"awla

t :

U . C

It

0..

-0 b-

oO

ak'

0

ur

CL

eU

jn1

4 e,

mo

0

0r

o

-o

0

a

nL

ML

r

00

0 nmz

L

-

-; o c

QCI cLuQ

: -;

I

"

$.

999

0999

LnI

a;

4

.8

,

c,.

0l

t'

oo

tooo~

o~

0.DL

4.~~.

lo4'"t

10

0 :-

V

Cf -.

N

-4

I

0

-

I N N

-

0

C,

0

- *' - N 0

- --. -

*0

* - I N -

o 0 -.-- .

- C

* C

C.3-

I-

VI 'a

N

-

- 0

U

- -I.

I CI

'0. 01

0 -

0

I-

- ,- N I- -

0

0

0

-

CI

LU

Lu 0

I-

U.,

-

----

- - -


45/92

I1'In

Ulf

-

Cl.

C.C

10

0

0

U

-~.,~

2

C-4,

0

000

0~

;

CO

0

.

10

-u

.7) .U

C

CI~CI

0

00

In~

z..

-3

0

il

gu:L

C4


46/92

M

-

0

- C

'0

'0 : Q

10

1

0'tC

0C

3c r. -

i

.0

.0

.0

.0

.0

.0

'

0 N '

0 -

In'~

n "I

0

0 '

0 '0

'

i

1.0

-a v00 '

0 N

N N

N

N ~

za

aD o

co

a

n

n

'0 ~

~

~

C

70

0

'

0

0 0

0 0 0

N

In

-

-.

*

~ ~ ~

~

~ ~ 1f

-"

N

0

'

~ N '

z'c

W

go.

.

I=

D

ooo

~

-

-

0

'

-

-

-

-

o

o

3

0

c0

; 0; 0;

u

c

0 0

0

-;.-0

0 N

N 0

-

'0 N

c;

c;

c;

r-

Nc:r

i

'

'

.

N .

0~u

c; c.

N

'

12 NN

0 '0 '

. '


47/92

.

0 C C C

*- - t t::-. N W

cro

4

Ln

Ln

Ln,

, m

-13

ItI

-- - - - - - N - - - -0 -

- - N -

r4

N

l

N -

-

-

1.4 S i3 S R S

..

w - -a

M , Go- n I

f-r

- c C% m m w m

C

LA. N

- SR

~ C.

~ SdS N

.-

.......

N

Q

2

'

SR N

- 0 0 C 0

~ N 0 C C

n

f7N' 7 7 f

SI

-~~~~

~

t

cc;S

~

~

0 N W S N 0 C N N .

a u I.-~.

S

~ ~ ~V

U-

InR S ~

C 0 . R S R

~

S

InC

N S R SR S

R R S R S

F~ *Ac

Na

:-j a.

.? 0 R CN0N ~

I N

'

L6

.0 S R

0Nj*

N

S

N ' N N2N

o C3S 0

C C 0

-

0 0

SRt

R

C

R C S R R S

- -

N

CS S

- N SR

-

N


48/92

I-

Ca4

e4

>'

0n

0

C;I

=.

s.

0 0

e.0

0

-2

o =s.I

a

L.~

-

v,

o.

c;.

C

.;

4

v

+1(' I

-04

ao+

-f

.

r-

z1 o*

-'In

U)N

V(Lt

LL f

0

4w

4u 0

('1 U.

OLe 0.

10 01.

0~

rd

r

::o

r4

t-u

-uC;C

va.

0.4

0

0 '

.

~In

.. ..

R

-3

0.

= .5

nJ

go

#A u.

e40

q.


49/92

j

...

.

.

.

9

.22

i

-02.

7L

CNC

I

In

In

o

1

ci

i

c

ir

c

oi

a

i

uII

it

Ln:

-

0

T

-0t-

Lu

~0

plane strain fracture toughness data handbook for metals

Documents