AlllOO TflflMTM

NBS

PUBLICATIONS

NAT-L INST OF STANDARDS & TECH R.I.C.

A111 00988494 /NBS monograph QC100 .U5^ V13:1960 C.1 NBS-PUB-C 1959

DATE DUE

384

CAYLORD PRINTCOINU.S.A.

UNITED STxA^TES DEPARTMENT OF COMMERCE • Frederick H. Mueller, Secretary NATIONAL BUREAU OF STANDARDS • A. V. Astin, Director

Mechanical Properties of Structural

Materials at Low Temperatures

A Compilation from the Literature

R. Michael McClintock and Hugh P. Gibbons

National Bureau of Standards Monograph 13

Issued June 1, 1960

For sale by the Superintendent of Documents, U.S. Government Printing Office Washington 25, D.C. - Price $1.50 (Buckram)
^ Rafeal Bureau # Sts:?dardi KC 2 9 1960

Foreword

The advent of space vehicles which utilize cryogenic fluids for propellants has

greatly increased activity in the field of cryogenic engineering in recent years. Large capacity gas liquefaction plants have become necessary to supply cryogenic

fluids in the amounts needed for rocket testing. With these plants and the rockets themselves has come the need for associated cryogenic equipment such as valves, pumps, liquid transfer lines, flov^ indicators, pressure switches, temperature and

level sensing devices, and, in fact, all the equipment used in handling liquids at other more convenient temperatures.

Intelligent design of reliable cryogenic equipment such as this requires the

existence of data on the mechanical properties of structural solids at low temperatures ; data which are all too scattered or too scarce to suit most designers. This

book, therefore, is issued to help fill the need for a compilation of useful design

figures.

Contents

Page

Introduction

Scales for interpolation

Graphs for:

III IX Aluminum and its alloys

Copper and its alloys

Nickel and its nonferrous alloys

Titanium and its alloys

Magnesium alloys Austenitic stainless steels Ferritic and hardenable stainless steels Low alloy constructional steels Superalloys (alloys of Co, Ni, Cr, W, Mo)

Brazing and soldering metals___

Miscellaneous alloys and pure metals

36

6272

7993

120 128

148

154

160

175 177

1

Nonmetallic materials. References

II
Mechanical Properties of Structural Materials

at Low Temperatures

A Compilation from the Literature

R. Michael McClintock and Hugh P. Gibbons

The tensile strength, yield strength, tensile elongation, and impact energy

of about two hundred materials, metallic^ and nonmetallic, are given graphically

as functions of temperature between 4° and 300° Kelvin. Introduction

The designer of equipment which must operate at very low temperatures is faced at some time in the design with the problems of making

material selections and of performing initial stress calculations.

This is no less true, of course, when a device is being designed for use at other temperatures, but the dearth of data on the mechanical

properties of commercial materials at low temperatures must certainly

be disconcerting to the design engineer who is looking for a material

to act as a structural member in a cryogenic device. It is hoped that

this compilation of some of the mechanical properties of materials

will assist the designer by making available in one publication reliable

data which have appeared in the literature or which, in some cases, have not yet been published.

The selection of a material for fabrication of a part can usually be

made in several ways, but very often the simplest method involves

the establishing of some figure of merit for the application at hand,

and comparing materials on the basis of this figure. For example,

double shell, vacuum insulated, cryogenic storage containers often

require tension support members for their inner shells. Since it is desirable that such members conduct as little heat as possible into

the inner shell from the surroundings of the vessel, an obvious figure

of merit for the material to be selected is its yield strength divided by

its mean thermal conductivity. (The appropriate yield strength

figure is the lowest value for the material over the temperature range

in which it operates.) ^A^ien the most promising materials have

been compared on the basis of these figures of merit, then the more

qualitative aspects can be examined. These may include such things

as the ease of fabrication or the weldability of the material. In some

cases, it may even be desirable to assign arbitrary values to the qualitative properties of the materials, and so to construct fairly complex

figures of merit for the purpose of material selection. Following the choice of a proper material, the designer will make

initial stress calculations in order to get an idea of the size of the

structural components necessary to sustain the working loads. Here

again the mechanical properties of the materials must be known.

It is to assist these two phases of low temperature equipment design

that the present compilation of properties is especially presented.

The data are presented with the idea that an engineer who is making initial calculations on equipment for operation at cryogenic

temperatures is more interested in obtaining quickly a definite figure

than he is in evaluating the experimental data given in several

detailed reports on the same material. The graphs and tables pre- sented here, consequently, represent an attempt by the authors to

III
perform an evaluation of data which have appeared in the literature

and to present the design engineer with the result. The curves

therefore appear as lines representing the mechanical properties

as functions of temperature, and not as bands representing maximum

and minimum values reported.

Such an evaluation process is bound to be somewhat subjective. If

it were not, the reduction of data to line graphs could better be per- formed by the most convenient digital computer programed to provide

the best fitting polynomial of degree "n." Unless the data were

weighted judiciously, such a curve would be little more than a mathematical delight and perhaps in poor keeping with the known or suspected behavior of the properties of materials with temperature.

The curves in this book, therefore, have been constructed from data

which the authors found to be the best documented and the most

consistent with that of other investigators. In most cases whatever

errors remain after such an abridgement will be adequately compensated by the designer's use of a "safety factor" in his stress analysis.

Where they are not, and greater confidence is required, the references

should be consulted for more detail. The references will also disclose the fact that not all the available

materials have been included in this volume. Different metals or

different heat treatments of the same metal, for example, have in some

cases been omitted where it was thought that they were not the most

representative of currently available materials. Omissions were also

made in a few cases where the trend of a mechanical property as a function of some metallurgical variable w^as thought to be adequately

demonstrated by those data selected for inclusion.

It should be remembered that any reduction of scattered mechanical

properties data to a smooth curve is an attempt to represent the "most

probable" relationship between ordinate and abscissa from among

the samples tested. Specific samples may lie above or below the curve, however, and the discrepancies caused by commercial variation in

chemical composition, heat treatment, dimensional and experimental

errors, etc., are normally condensed into a "safety factor" by the designer, whereby he sidesteps costly quality control, or more complicated mathematics in the case of complex devices. The use of a safety factor is properly the province of the design engineer since he

knows the use to which the equipment will be put, and the reliability

desired. It should therefore be subject to the designer's complete

knowledge, and not, as is sometimes the case, be applied to experimental data by the authors of such reports as this and the results presented as a table of "permissible stresses". This not only misplaces the responsibility for safety or reliability, but in complex cal- culations the safety factor can be compounded unintentionally. The

point of mentioning this is merely that the data in this book should

be used with caution for designs in which safety factors must be small

(as in cases of restricted weight or size) , since low temperature properties are often sensitive to variations in thermal and mechanical his- tory and chemical composition which are allowable within commercial specifications.

In addition to these variations, limitations in experimental accu- racy may account for some of the apparent inconsistencies which

appear in graphs in this book. For example, the tensile strength of

annealed type 803 stainless steel, which appears on page 98, lies IV
slightly above that of the same material which has been cold drawn

10 percent ; and at 20° K, the same effect reappears in types 310 and 316

stainless steels. It is conceivable that such an effect is real, but the

authors' first inclination is to ascribe the difficulty to differences in

strain rate between observers, or to other experimental limitations.

In any event, having no better knowledge, the authors have thought

it best simply to include the curv^es derived from the experimental

results and to let the apparent inconsistencies stand for the present.

The same philosophy applies to the graph of the strength of tita- nium alloys on page 74, although the drop in tensile strength of the

two alloys at 20°K can probably be attributed to experimental error

in this case. The elongation of these two alloys is zero at 20°K, and

brittle materials are extremely sensitive to accidental surface imperfections or other stress raisers, even such as the radius commonly

present at the ends of the reduced section of a tensile specimen.

The mechanical properties presented in this compilation as functions of temperature are tensile strength, yield strength at 0.2 percent

offset (unless otherwise noted), elongation, and impact energy. In

a few instances the reduction of area of a tensile specimen is presented

as an indication of ductility. The first three properties were obtained from short time tension tests of smooth specimens which were

generally cut from bar or plate one-eighth inch thick or thicker.

Thinner sheet material is noted on the graphs. Some investigators

report "yield point'' (usually obtained by the "drop of the beam"

method) rather than yield strength. In these cases the graphs are

so noted, and the upper yield point is the one referred to. The impact energy is the energy absorbed by a standard specimen

in breaking under an impact load. In every case the type of impact

specimen is indicated on the graph by a note wliich identifies it with

one of the specimens described in test method E23-56T of the American Society for Testing Materials. The notation "Charpy V" re- fers to the type "A" specimen having the V-notch, "Charpy K" refers

to the type "B'' specimen with the keyhole notch, and "Charpy U"

refers to the type "C" specimen with the U-shaped notch. Izod speci- mens are type "D" in the ASTM specifications.

The Kelvin temperature scale is so Avidely used in cryogenics that

all data have been converted to these units for consistency. For the

convenience of those to whom a Fahrenheit temperature means more,

extra scales have been included on pages ix and x. These may

be cut out and held along the abscissa to allow interpolation as well

as direct reading in degrees Fahrenheit. The extra scales also contain divisions corresponding to the ordinate mechanical properties

for interpolation.

Adjacent to each curve are several numbers in brackets. These

numbers correspond to the references in the bibliography at the end

of the graphical section and indicate the sources of data from which

the curve was constructed. On graphs where two or more curves appear for the same material, the reference numbers given for one

curve apply to the rest. Because of the scarcity of published data, some of the references quoted are from unpublished records.

In most cases smooth curves are used to represent the behavior of

the mechanical properties as functions of temperature. These curves

represent interpolation between experimental data points as mentioned before. In some cases, however, the data are joined by

V
straight lines, and intermediate or end points are indicated. Where

this occurs, it is because either a scarcity of data or a doubt on the

part of the authors cautioned against drawing a smooth curve. The authors have tried to use nomenclature which is consistent with

etforts of the various technical societies and manufacturers' asso- ciations to classify and standardize metal specifications. When ambiguities might still exist, nominal or reported compositions have

been used in addition to the name of a material. In a few cases proprietary names have been given when they have become so commonly

used that other designations might be confusing.

Throughout the book several abbreviations are used on the graphs.

These correspond with usual metallurgical practice in this country

stress is given in psi (pounds per square inch), impact energy in ft-lb (foot-pounds), and tensile elongation in percent in 4D (four diameters) where this ASTM recommendation Avas adhered to. The per- centage of cold drawing or cold reduction given on many of the

graphs refers to reduction of area rather than reduction of diameter.

"OQ & T" means "oil quenched and tempered", "WQ & T" means

"waterquenched and tempered", "AC" means "air-cooled", "RB" and

"RC" mean "Rockwell B hardness" and "Rockwell C hardness",

respectively. Heat treating temperatures are given in degrees Fahrenheit, which is common in metallurgy in this country. Also w^henever

the metallurgical condition of the specimens was stated in the litera- ture, it is appended to the curves. It is surprising, by the way, to

find in the literature data derived from material described only as

"soft yellow brass" or "soft bronze". An attempt was made to extract meaning from these data, but for the most part the value of such

information is not great. Laboratory analysis of the materials tested

and careful control of the thermal and mechanical history of the

materials investigated would help immensely to establish the reliability

and the usefulness of mechanical properties data.

Probably the first thing learned by a newcomer to the cryogenic

field about the properties of materials is that some materials become

brittle at low temperatures and are therefore miusable in many struc- tural applications at these temperatures. The literature is studded

with accounts of spectacular brittle service failures which would not

have occurred at higher temperatures. There are certain applications, however, in which it would be a mistake to apply the ductility

criterion in the selection of a material for low temperature service.

Springs are an example. The authors are aware of an instance in

which the most suitable material for a low temperature coil spring was not considered because it would be brittle at the service temperature. The ductility criterion should not generally be applied in such

cases since a smooth coil spring having no re-entrant comers is care- fully designed to act as an elastic member and usually need not possess any ductility for its satisfactory service. Professor Collins at the Massachusetts Institute of Technology, for example, has success- fully used carbon steel valve springs in expansion engines for the

liquefaction of nitrogen and helium.

For most structural applications, however, the engineer would like some assurance that the material he selects will not be brittle at the

service temperature. If it were, his hardware would be liable to catastrophic failure in the event of accidental impact or vibration loads

at a point where local stresses occurred in excess of those for which he

VI
has allowed. "Ductile" materials, of course, are capable of redistributing local stresses in excess of their yield strength by the mechanism of

plastic floAY. One great difficulty, however, has been that of devising

a laboratory test which will predict satisfactorily whether a material

will behave in a ductile or a brittle manner in service. The plastic

elongation of a tensile specimen is not a satisfactory index, since many

materials which show plastic deformation in a tensile test at a given

temperature have been known to fail in a J>rittle manner in service at the same (or even higher) temperatures. Ordinary low carbon steel, for example, which Eldin and Collins ^ find to be completely brittle in a tensile test only below 65 °K, has a record of many service failures at temperatures only moderately below room temperature. Obviously

the behavior of a material under the conditions of uniaxial stress present in the usual tensile test does not provide a sufficiently good

prediction of its behavior under multiaxial stress conditions.

The beam impact test, in which a standard-size bar is subjected to a

high-velocity blow, while popular because of its convenience, is also

deficient in some respects as an index of performance of a material in

ser\dce. A correlation has been obtained between service performance

and impact energy for steels by Jaffee et al.,^ but such a correlation

applicable to all materials has not yet been found. One difficulty seems

to be that light metals pay an unjust penalty in the impact test. Magnesium alloys, for example, exhibit low impact strength, but have been

satisfactorily used in the aircraft industry in structural applications in

which they receive impact loads. So whereas the tensile elongation

of a material seems to be too optimistic an indication of service

ductility, the energy absorbed in an impact test seems in some cases to give information which is too pessimistic.

The energy absorbed in an impact test can be deceptive for still other reasons. For example, the energy value is affected considerably

by incomplete breakage of a very ductile specimen. When this occurs,

a portion of the energy recorded in a Charpy test is the result of forc- ing the specimen through the supports of the machine. Consequently

this occurrence, along with other supplementary information such as the character of the fracture surface, is sometimes of even greater

importance than the absolute value of the energy absorbed.

As a simple laboratory test which will provide a suitable analogy

to the service performance of a material, the notch tensile test is gaining acceptance for some purposes. The test is performed either at low

strain rates in tensile equipment or at high strain rates, usually in

impact machines which have been modified for this use. "Notches"

almost always exist, of course, in any manufactured part in the form

of weld craters, rivet holes, re-entrant comers, or simply accidental

scratches ; and the notch-tensile test provides an indication of the abil- ity of a material to sustain working stresses in the presence of such

stress raisers. A properly designed notch-tensile specimen also contains an area of bi-axial or tri-axial stress as well, so information can

be gained about the performance of the material under these

conditions.

There are other types of laboratory tests which have been devised

to predict the performance in service of structural materials, each a

1 See reference 29.

2 Jaffee, Kosting. Jones, Bluhm, Hurlich, and Wallace, Impact tests help engineers

specify steel, SAE Journal, March 1951. VII
compromise between simplicity and universality on the one hand, and

degree of applicability to the service requirement on the other. For

the most part, airframe and component manufacturers make the compromise in the latter direction. Their test specimens consequently

consist of subassemblies, complete components, or even entire complex

assemblies. In industries in which weight is not a prime consideration, and larger safety factors can be used, the tendency is toward the

simpler tests. Obviously, economic considerations make the simple

experiment the more desirable, and until a simple test is devised which

is a reliable index of service performance, most design engineers will content themselves Avith the less desirable information provided by

the usual tensile and impact tests in the first stages of design.

The greatest amount of information in the literature which indi- cates something about the ductility of a material is in the form of

tensile elongation or impact data. Therefore, while not the most sat- isfactory indications of ductility, these two mechanical properties are reported in addition to yield and tensile strengths in this book.

The authors take pleasure in acknowledging the assistance of L. J. Ericks in the preparation of this book. His careful drafting is re- sponsible for the final appearance of the graphs.

VIII
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X
Aluminum and Its Alloys

50 100 150 200 250 300

TEMPERATURE, K

YIELD STRENGTH OF 1 100 ALUMINUM
2
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120

100

80

60

40

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50 100 150 200 250 300

TEMPERATURE/K

IMPACT ENERGY OF 5154 ALUMINUM
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10"

50 100 150 200 250 300

TEMPERATURE

STRENGTH OF 5356 ALUMINUM

50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF 5356 ALUMINUM

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40

c 20

Q 10 o

v_Q.

]

H

i2l [l] -

0 50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF 5456 ALUMINUM
25

70x 10^-

65

60

55

50

T4[4.43]

45

Q.

YIELD

I I I I I 50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF 6053 ALUMINUM
26

^0[4,43

4 [4,43]

/T6[4, 43]

50 100 150 200 250 300

TEMPERATURE , K

ELONGATION OF 6053 ALUMINUM

CHARPY K

\t6[-rs]

^ 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF 6053 ALUMINUM

28

55

50

45

40

35

Q

vcf 30 c

25 c

a>o

20

Q.

15

10

5

>,43,7l]

r4[4.43]

/T6[ 4,43,71, IC )3]

50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF 6061 ALUMINUM

15

10

CI HARPY K

\T6[7f), 103]

50 100 150 200 250 300

TEMPERATURE/K

IMPACT ENERGY OF 6061 ALUMINUM
Q 40

c 30

§ 20

AL L SPECirvIENS PRC)M EXTRLiSIONS

/T42[43] /0[4,^;3]

/ T5[4,43] —

1t6[ 4,43]

0 50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF 6063 ALUMINUM
30

70x10'

60

50

Q.- 40

(O

(/) UJ

q: 30

20

10

/T6, F()RGED[4;

1

TENSILE

YIELD

1 50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF 6151 ALUMINUM

1rJ, FORGED [4]

50 100 150 200 250 300

TEMPERATURE, K

ELONGATION OF 6151 ALUMINUM
31

Q.

(/)

if) UJ

a:

lo--

)

) /T6, SHE iT [43, 71] —1 /T6, RO 43 7 1 103]

) ^

/ V

fje, EXTF

N.^4^

FUSIONS

57] ^^^^^ ) T6, SHE et/

\ *—

)

1

^T6, ROD

)

)

,43]

I

)

TENSILE

—-YIELD

1 50 100 150 200 250 300

TEMPERATURE, *»K STRENGTH OF 7075 ALUMINUM
10

^ 5

/T6, R

//

"^^ DD, CHARF

, EXTRUS

IZOD

K [103]

IONS [57];

\T6.f?0D, CHAF PY V[7l]

> 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF 7075 ALUMINUM
100 150 200 250

TEMPERATURE,*»K

STRENGTH OF 7079 ALUMINUM

300

CVJ

c8

Q.

20

15

10

5

-T6, FOF?GED [65]

50 100 150 200 250 300

TEMPERATURE,°K

ELONGATION OF 7079 ALUMINUM

10 CHARP> 1 -T6, FORGED [^S]

50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF 7079 ALUMINUM
70 X 10

50 100 150 200

TEMPERATURE, °K

STRENGTH OF SAND CAST

ALUMINUM ALLOYS

250 300
35

0

5

CURVE ALLOY REF.

1 4 3 [ 1 ] 2 142 - T77 [ 1 ] 3 355 - T5I [ 1 ] 4

56

355

356

356

- T 7

. TCI T 51

- T7

r 1 1

[

' ]

h

' 4_^—

^^3 2/

TEMPERATURE,°K

ELONGATION OF SAND CAST

ALUMINUM ALLOYS

10

5

CHAR PY K

^195 - T6 [75]

^356 - T6 [75]

50 100 150 200 250 300

TEMPERATURE ."K

IMPACT ENERGY OF SAND CAST

ALUMINUM ALLOYS
Copper and Its Alloys

36

X 10"

^COLD DRAWN , H [71]

lARD

A

[9,17,

NNEALED

33,70,71,6^3, 88,90]

^NNEALED [33,"rol

TE

Yl INSILE

ELD

50 100 150 200 250 300

TEMPERATURE, ^'K STRENGTH OF OXYGEN FREE

HIGH CONDUCTIVITY COPPER
0 50 100 150 200 250 300

TEMPERATURE, ^'K ELONGATION OF OXYGEN FREE

HIGH CONDUCTIVITY COPPER

^ 40

-ANNEAL.ED [67]

NNEALEC [17] ^

CHARPY K — IZOD

i 0 50 100 150 200 250 300

TEMPERATURE, "K

IMPACT ENERGY OF OXYGEN FREE

HIGH CONDUCTIVITY COPPER
300 X

10^ 38

TREATMENT

SOLUTION TREATED

SOLUTION TREATED 8 AGE HARDENED

COLD DRAWN - HALF HARD

CD. HALF HARD 8 AGE HARDENED

NOMINAL COMPOSITIONS

A WROUGHT - Be 2, Co .3, Cu BAL o CAST - Be 2, Co .6, Cu BAL

100 150 200

TEMPERATURE , STRENGTH OF BERYLLIUM COPPER

300
70

60

•5 50 c 40

c 30

o

a>Q. 20

10

0

39

COMPOSITIONS a TREATMENTS SAME AS

GIVEN ON PAGE 38.

.r^^-kH-Z GAGE LENGTH.

' [71]

A^HT[80]

O AT [80]

50 100 150 200

TEMPERATURE,

250 300

ELONGATION OF BERYLLIUM COPPER

120

100

80

x> 60

40

20

COMPOSITIONS f GIVEN ON PAGI

1

35 TREATf

E 38.

\/IENTS S AME AS

CH

CH

ARPY K

ARPY V

A[t10]

-a|h [8 0]

T[80] —

s

^AAT[80] ^

-O AT [80] 50 100 150 200 250 300

TEMPERATURE. **K IMPACT ENERGY OF BERYLLIUM COPPER

540232 O - 60 -4
40

X 10

/-A Be -Zn, ^HT [80]

A Be-Co, ^HT[80]

^AE e-Zn,^H T

t-j DC >^>'t ^

DC k^O, A

[80]

r /

I y

A Be-Co,

[71]

TfY

ENSILE

ELD

NOMINAL COMPOSITIONS

BERYLLIUM - COBALT BRONZE!

A WROUGHT — Be .6, Co 2.6, Cu BAL. OCAST -Be .4, Co 2.3, Cu BAL. BERYLLIUM -ZINC BRONZE!

A WROUGHT - Be I.L Zn .9, Cu BAL. CONDITION TREATMENT

AT SOLUTION TREATED 8 AGE HARDENED.

VzH COLD DRAWN TO HALF HARD CONDITION. /2HT CD. HALF HARD AND AGE HARDENED.

'/4HT CD. QUARTER HARD AND AGE HARDENED.

50 100 150

TEMPERATURE

200 250 300

STRENGTH OF BERYLLIUM BRONZES
41

60

50

g 40

c

c 30

S 20

0)

COMPOJ

GIVEN

5ITI0NS a TREAT^

ON PAGE 40.

/lENTS S AME AS

\

-ABe-Co, Ah - 2"g

[71]

)TH

V

4-HT fsol

ABe-Co,^HT[8

A Re-Zn

/ , ^ ^ ^

o Be-Co, AT[80]

50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF BERYLLIUM BRONZES

COMPOSITIONS £ GIVEN ON PAGi TREAT

E 40.

MENTS S>AME AS —CH^

ch;

\RPY K \RPY V /-ABe-C<),iHT[7i ]

jHT[80]

ABe-Zn,:^ HT

[80] ^ oBe-Co, AT [80]

\

1

j 50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF BERYLLIUM BRONZES
80

^70

UJ

cr 60

50

40

30

25

67-33, ANNEALED

(YELLOW BRASS)

[15]

60-39+1 7o Sn,

ROLLED [90]

(NAVAL BRASS)

70-30, ANNEALED,

(CARTRIDGE BRASS)[l7]

TENSILE

'yield point

the beam) except as noted

NAVAL BRASS

1 "ROLLED

70-30, ANNEALED, I ^^J^

\J (.l7o OFFSET YIELD '^'^^^ ^ ^1 STRENGTH)

t

50 100 150 200 250 300

TEMPERATURE, K

STRENGTH OF SOME ALPHA BRASSES
80

70

60

50

cvi40 c

c 30

o

Q)^20

10

43

-70-30, ANNEALED [l?]^ (CARTRIDGE BRASS).

67-33, ANNEALEDr7

(YELLOW BRASS)

/

[15]

60-39+ I % Sn,

ROLLED [90]

(NAVAL BRASS)

67-33, 40 7o CD. [l5],

(YELLOW BRASS) | 50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF ALPHA BRASSES

100

80

£ 60 ^ 40

20

CHARPY V

IZOD CHARPY K

67-33, ANNEALED [is]

NAVAL BRASS, CD. HARD [49]

0 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF ALPHA BRASSES
44

COMPOSITIONS

ALLOY %Cu 7o Pb %Sn %Zn

A FREE CUTTING MUNTZ METAL 58.7 1.3 BAL. B ARCHITECTURAL "BRONZE" 57.6 3.0 .55 BAL. C FREE CUTTING BRASS 61 3 36

120 X 10

110

100

90

80

70

60

50

40

30

20

10

V)

if)

(/) LU

\-

0.5 % OFFSET

YIELD STRENGTI

'A" COLD DRAWN 12% [l5]

/B',' ANNEALED [9]

A. COLD DRAWN 12%

A. ANNEALED

TENSILE

YIELD POINT BY DROP OF BEAM EXCEPT AS NOTED.

I

I \ L \ 50 100 150 200 250

TEMPERATURE , «K

STRENGTH OF LEADED BRASSES

300
CVJ

cOu

a>Ql

60

50

40

30

20

10

COMPOSITION AS

GIVEN ON PAGE 44.

45

FREE CUTTING MUNTZ METAL,

ANNEALED [is] + (ARCHITECTURAL "BRONZE"

ANNEALED [9

FREE CUTTING MUNTZ METAL,

COLD DRAWN 12% [is]

FREE CUTTING BRASS

ROLLED [90] I 50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF LEADED BRASSES

60

50

40

30

20

10

GHARRY V

GHARRY K

FREE CUTTING BRASS,

ANNEALED[49] FREE CUTTING MUNTZ METAL,

ANNEALED [iS] i

FREE CUTTING MUNTZ METAL,

COLD DRAWN 12% [is]

^FREE CUTTING BRASS,

COLD DRAWN, HALF HARD

\ \ [49]

50 100 150 200 250 300

TEMPERATURE, «K

IMPACT ENERGY OF LEADED BRASSES
46

UJ

140

130

120

110

100

90

80

70

q:^ 60

50

40

30

20

10

0

xlO 1 1 '

1 NOMINAL COMPOSITION : 60 Cu - 40 Zn

LD DRAW N 257o[i 5]

ANNE

[15 ALED-^

]

^^AN NEALED

TENSILE

YIELD POIh

, 1 JT BY DRC)P OF BEiIXM 50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF MUNTZ METAL
47

60;

S

50 u

•£ 40

CJ

•E 30 c

<1> S 20

Q.

10

7

'ANNEAL iD Ll5j

, pni n / UULU nRAVAyM UnAWPM PRO/., r 1 «^"

1 NOMINAL COMP

1 OSITION : 60 Cu - 40 Zn

0 50 100 150 200 250 300

TEMPERATURE

,

ELONGATION OF MUNTZ METAL

T 30

CHARF V ANNEALE D[i5]

OLD DRAWN 25% [15]

NOMI NAL COM POSITION : 60 Cu - 40 Zn

:—i 50 100 150 200 250 300

TEMPERATURE , IMPACT ENERGY OF MUNTZ METAL
48

160 X 10

150

140

130

120

I 10

100

Q.

^90

(n

(/) UJ 80

70

60

50

40

30

20

10

U r - -" -T 1

1 COMPOSITIONS COMPLY WITH ASTN

BI50-54 AND BI48-52

1 1 1

1A DESIGN ATIONS

WATEF

AND T

< QUENCH

EMPERED

ED FROM I650°F

AT 1200 °F

1\LLOY 9D

HEAT TR

CAST AN

EATED. [4" D

']

v,/ALL0Y9D, CAST AND

^^..^ANNEALED [47]

t\LLOY 9 A AND AN CAST

NEALED [a 7]

ALLOY 3

,

AND ANNEWROUGHT

:ALED [47]

9D, HEAT TREATEC

^^9D, ANNEALEC) 9A, ANNE i\LED\^

3, ANNEA

TENSILE

YIELD STREN

1 GTH (0.5 °/

'o OFFSET)

50 100 150 200 250 300

TEMPERATURE, **K STRENGTH OF ALUMINUM BRONZES
49

60

50

40

30

20

10

/ALLOY

/ ANN

3, WROU

lALED [47

(jH 1 AND

1

COMPOSITIONS AS

SHOWN ON PAGE 48. /ALLOY 9A , Zl. / ANNEALED

^ST AND

/\LLOY 9D

ANNEALE

CAST AN

D [47] —

D

\alloy

HEAT T9D, CAST

REATED * AND [47]

50 100 150 200 250 300

TEMPERATURE, ^'K

ELONGATION OF ALUMINUM BRONZES

80

70

60

50

40

30

20

10

CHAF

' ?PY V

ALLOY 3, ANNEAL

WROUGHl

ED [47]

AND

COMPOSITIONS AS

SHOWN ON PAGE 48.

ALLOY 9 ANNEAL

A, CAST A ED [47]^

ND

ALLOY S ANNEA

D, CAST /s LED [47],ND

^ALLOY ? HEAT

3D, CAST 1. TREATED ^\ND

' [47]

50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF ALUMINUM BRONZES
50

150 X 10

140

130

120

I 10

100

"Ih 90

Q.

(/T 80

70

60

50

40

30

20

10

cn

0^ 1 COM

DESIGNA

-POSITION

TION B 1 S COMPL

50-54 F(Y WITH / DR WROU

!\STM

GHT AL BRONZE

/ ALLC

/ AS f)Y No. 1-0RGED[9(

ALLOY N ROLLED i3t ANNEAL IDv

\LLOY No. 1 |— /-N I~J /-* f— l~\ , FORGED

/\LLOY No.l (YIELD S

, ROLLED

TRENGTH,

a ANNEAL

0.1% OFFS ET)

Ylf NSILE

ELD POINT , EXCEPT AS INDIC/^TED

50 100 150 200 250 300

TEMPERATURE, »K

STRENGTH OF 8% ALUMINUM BRONZE
51

70

60

a> 50

o

c 40

CVJ .E 30 cS 20

Q. 10

COMPOSITIONS AS

SHOWN ON PAGE 50.

ASTM ALLOY No.l AS FORGED [90] ASTM A ROLLED

_LOY HoA

a ANNEAL ED\

[•7]

-

50 100 150 200 250 300

TEMPERATURE, °K

ELONGATION OF 8% ALUMINUM BRONZE

CHARPY K IZOD

COMPOSITIONS AS

SHOWN ON PAGE 50

\ASTf

(HA

^ ALLOY r RDNESS K

^0.1 , ROLL

52 DPH) [4 ED,

9]

^ASTM

ROLLE

ALLOY No. :D a ANNElALED [l?;

^ 50 iOO 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF 8% ALUMINUM BRONZE
52

140

130

120

I 10

100 — 90

Q. en 80

en

cn 70

60

50

40

30

20

10

COMPOSITIONS

CAST LEADED

Cu 5 7. 7 % 5 6. 5 %

Mn .5 1.4 Sn .6 .9 Fe 1.2 I.I Pb — 1.3 Al 1.0 —

Zn BAL. BAL.

. 1 FA DED, ROLL NEALED [l _ED AND

7]

>^S CAST [Qnil /

0^

\S CAST [90] H

zLEADED, F (YIELD S OLLED AN

TRENGTH

D ANNEAL

AT 0.1% 0

ED [17]. FFSET)

TENSILE

YIELD POINT

_.. r.„, I EXCEPT A S INDICAT ED 50 100 150 200 250 300

TEMPERATURE,*»K

STRENGTH OF MANGANESE BRONZES
53

50

V) 40

o

£ 30

CVJ c 20

§ 10

V.

a;Q.

COMPOSI

GIVEN 0

TIONS AS

N PAGE 52 /\S CAST [<90] \ ^ L EADED, R ANNEALED

OLLED AN

[17] —

j

D X

^

50 100 150 200 250 300

TEMPERATURE, '^K ELONGATION OF MANGANESE BRONZES

30

25

20

10

5

COMPOSITIONS

COMMON NAME Cu Sn Pb Zn Other

A -OUNCE METAL 85 5 5 5 B -*SEMI - PLASTIC BRONZE 70 5 25

C -BEARING a BUSHING " 80 10 1 0

D -LEADED MANGANESE " 56.5 .9 1.3 38.8 1.4 Mn

* NOMINAL. COMPOSITIONS ONLY.

ROLLED A MD ANNEA LED [17]

Ch

IZMRPY K OD

C, AS CAST

[49]

,A. AS CAST [49]

^B, AS CAST [49]

50 100 150 200 250

TEMPERATURE,

IMPACT ENERGY OF SOME

MISCELLANEOUS BRONZES

300
54

180 X 10

170

160

150

140

130

120

Q.I 10

CO[SlOO

QC

\-

iD 90

80

70

60

50

40

30

20

COMPOSITIONS - 7o CAST WROUGHT

Cu 88,4 90.3

Sn 10.0 8.2 P — .06 Zn 1.6

.D DRAWN , HARD [7 IJ

\a S CAST b

TE:nsile

ELD

50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF PHOSPHOR BRONZE
' 50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF PHOSPHOR BRONZE

540232 O - 60 - 5
140 X

10^

130

120

MO

100

90

80

Q.

.70

(/) ^60

56

50

40

30

20

10

0

ACT

/ COL

KAM TVDC 1 YrL

.D DRAWN

AA,

42% [8 8]

ASTM T

QUARTE

[71] \

T PE A , ^

R HARD^

AoA C T K>l

1 M

QUARTE

' V DC A T r L A , R HARD

TE

YII NSILE

ELD

50 100 150 200 250 300

TEMPERATURE

STRENGTH OF SILICON BRONZES
10

^ 50 100 150 200 250 300

TEMPERATURE, '^K ELONGATION OF SILICON BRONZES

CHAR PY V

ASTM

COLD DlTYPE A,

=?AWN, HA

[67]

RD

0 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF SILICON BRONZES
58

ALL SPECIMENS ROLLED AND ANNEALED

140 \

130

120

I 10

100

(0.1% OFFSET)

10 ^ h— TENSILE

YIELD 50 100 150 200 250 300

TEMPERATURE, *K

STRENGTH OF CUPRO-NICKELS
ALL SPECIf

IZOD

VIENS RO LLED AND ANNEAL.ED

Ni [l7]

20 % Ni [17]

0 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF CUPRO-NICKELS
I50x 10"

100 150 200

TEMPERATURE, <»K STRENGTH OF NICKEL SILVERS
^30 % Ni ROLLED

[17], a ANNEAL.ED

COMPOSITIONS AS

GIVEN ON PAGE 60. IZOD

' 50 100 150 200 250 300

TEMPERATURE, *»K IMPACT ENERGY OF NICKEL SILVERS
Nickel and Its Nonferrous Alloys

62

150x10

140

130

120

110

100

^90

80

70

60

50

40

30

20

10

J

- " ^AS FORGED :2.]

1

HOT ROLLED

ANNEALE

[17,83, ICID'

)0]

HIGH PUF

ANNEAL

{ITY(99.8

ED [33]

5Ni);^

„.„/

/ANNEAL.ED [lOO]

HK3H PURIT Y, ANNEA

[3

lE)"^""

3] — TENSILE

YIELD

: I 50 100 150 200

TEMPERATURE, «K

STRENGTH OF COMMERCIALLY

PURE NICKEL

250 300
50 100 150 200 250 300

TEMPERATURE, »K

ELONGATION OF COMMERCIALLY

PURE NICKEL
64

^COLD DRAWN [30] , (AMOUNT NOT STATED)

ANNEALED [17]

AS CAST [45],

(NOTCH NOT GIVEN)

50 100 150 200 250 300

TEMPERATURE, *K

IMPACT ENERGY OF COMMERCIALLY

PURE NICKEL
65

180

170

160

150

140

130

S.I20

ISiiO

cr

h-^ 100

90

80

70

60

50

40

30

u /COLD [)RAWN 5C)%[69,82

V /COL D DRAWN 10 % [71 ]

HOT =?OLLED[<>9]

COLD DR/\WN 10% [71]

»

_

TENSILE

YIELD

50 100 150 200 250 300

TEMPERATURE, *»K STRENGTH OF INCONEL
50 100 150 200 250

TEMPERATURE, K

ELONGATION OF INCONEL

300

240

220

'200

CHARPY V

HOT ROLLED [30]

180

^ 40

CHARF>Y V

^

OLD DRA\/VN 50 % '69,82]

INCONEL X, A(3E HARDE NED [45]

( CAST [45]

NOTCH NOT GIVEN)

1 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF INCONEL
67

150

140

130

120

110

100

(A

CO

UJ

or 80

cn 70

60

50

40

30

20

10

0"

1

AS FORGEID [21,45]

.^^HOT ROLLE ) [83]

N^A SINEALED

[17,33,45

*** 71] ^

AS FO RGED^

>V HOT FPOLLEDN —

NNEALEl

PENSILE

HELD

50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF MONEL
68

70

60 w 50

a>O

.E 40

.E 30 c

<f 20

Q.

10

1

1 ^ANNEALED [l7.33.45]

HOT ROL _ED [83]

\S FORGED [21,45]

50 100 150 200 250 300

TEMPERATURE, <»K ELONGATION OF MONEL

220

200

180

^160

s- 140

120

100

80

ANNEALED-"^

[30] \hot ROLLED U 0]

CHARPY V

IZOD

/ ANN(EALED [i"

50 100 150 200 250 300

TEMPERATURE, *»K IMPACT ENERGY OF MONEL
69

210

(/) CO

Ul

or

h180

170

160

150

130

120

110

100

60

10^

1:OLD DRyWN 45*= [71]

I V—

FDa

Y

J

FE^

EN

Cc^

D^

A^

COLD DRAWN

45 % [71]

1

' REF [45]

A - AMMCAICn

B - ANNEALED AND AGE HARE C - HOT FINISHED

)ENED

' U - MUI l-lNlbMtU ANU Abt MAKUtlMtU

E- COLD DRAWN 1 F - COLD DRAWN AND AGE HARDENED

TENSILE

YIELD

\ 1 50 100 150 200 250 300

TEMPERATURE, *>K STRENGTH OF K MONEL
50 100 150 200 250 300

TEMPERATURE, *K

ELONGATION OF K MONEL

60

J. 30

CHARPY SP ECIMENS , NOTCH NOT GIN/EN

H MONEL , AS CAS T [45]

Mor^EL,AS CAST [45]

^ 50 100 150 200 250 300

TEMPERATURE, *»K IMPACT ENERGY OF MISCELLANEOUS MONELS
200 X 10^ 71

180

160

0)140

Q.

g>l20

100

80

60

40

20

TENSILE

YIELD

WATER QUENCHED

FROM I832°F [2l]

COMPOSITION %

Ni 7 8.9 Cr 18.9 Mn 1.4 C .3 50 100 150 200 250

TEMPERATURE,

STRENGTH OF NICKEL -CHROMIUM

RESISTANCE ALLOY

300

40

o

c- 30

20 ^ 10

Q.

WATER QUENCHED

FROM 1832 ° F [21

50 100 150 200 250

TEMPERATURE, ^'K ELONGATION OF NICKEL-CHROMIUM

RESISTANCE ALLOY

300

540232 O - 60 - 6
Titanium and Its Alloys

72

190x10^-

\ ~1 1 \ \ INTERSTITIALSlC+OtHtN) =.30% (NORMAL) =^

INTERSTITIALS(C+0+H + N) = .l27o (LOW) O

ALL SPECIMENS ANNEALED

COMMERCIAL GRADE RS-70 (.032"SHEEtT

100 150 200

TEMPERATURE, **K STRENGTH OF UNALLOYED

TITANIUM

300
73

CM

45

40

35

30

25

4- 20 c

0)o^ 15

0)Q.

10

/0[3I]

1 • [32]

/ \ COMMERC

(.032" SH

r'GAGE L

:iAL GRA

EET),

.ENGTH

DE RS-7

ALL SPECIMENS ANNEALE D • INTERSTITIALS (C+O + H+N) = .30

O INTERSTITIALS (C + O+H+N) = .12

1 1 1 %

%

50 100 150 200

TEMPERATURE, ^'K 250 300

ELONGATION OF UNALLOYED TITANIUM

20

15

10

5

coMr

INTE^ERCIALLRSTITIAL

Y PURE

S NOT Gl VEN

0[3I]^

[8SJ . A M M C A 1 cn • [32]^ — CHARPY V — CHARPY K ^ 50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF UNALLOYED TITANIUM
280 X 10 270

260

250

240

230

220 ^ 210

CO

UJ

cc

I- 200

190

180

170

160

150

140

130

120

100 150 200 250 300

TEMPERATURE, K

STRENGTH OF TITANIUM ALLOYS
30

25

20

c

\_Q. 10

7o IN 2 INCHES % IN I INCH

% IN !/2 INCH

75

3V-'ll Cr -SAi [7l](.032" SHEET)-\^

4 Al - 4 Mn [12] 6 Al - 4 V [19]

100 150 200

TEMPERATURE, °K

ELONGATION OF TITANIUM ALLOYS

300

35

30

25

^20 ^ 15

10

NON-STD. CHARPY V SPECIMENS

.788" WIDE X .197" THICK I NOTCH WAS STD. SHAPE. BUT V2 STD. DEPTH

I

I

0

l3V-IICr- 3 Al," ANNEALED [19] 4 Al -4 Mn , ANN EALED [|2]

50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF TITANIUM ALLOYS

280 X 10^- 77

270

260

TEMPERATURE,

STRENGTH OF 5 Al -2.5Sn TITANIUM
280 X !0^ 270

260

250

240

230

220

Q-210

CO[3200

cr

h-^ 190

180

170

160

150

140

130

120

78

\\

\\U-

\\

V-

\

\

^HEAT TREATED [l9],

yy 1725 op, 1 HOUR, WQ,

<r / AGED 1050 °R 2 HOURS J

\ \

X

\ \

1 COOLED.

\ \

\ \

\ — ^

\

: V- V v X

i \

\ A X-

\ \

\ —

\ >v

ANNEALED-

|[65] • \ > \

\

{ 064 SHEE T)

\

^ \

N—

\ V > ^ X,

\ \

^ \

s

\

>v \

'' TENSILE

YIELD

1 50 100 150 200 250 300

TEMPERATURE, K

STRENGTH OF 6 Al - 4V TITANIUM
Magnesium Alloys

79

90x10

80

70

°- 60

(/)

Ijj a:

h-cn 50

40

30

20

13

63, AS E)(TRUDED 1 64] - s^y^QA

"TA 54 [4

AS EXTR

MIA[42

HARD R(

2].

^

3LLED-^

]• ^

\

\

N

^•^

MIA/

OMMERCIA

AS EXTRU

_LY PURE

DED [8l] —TE

YIE

^JSILE LD

0 50 100 150 200 250 300

TEMPERATURE, °K

STRENGTH OF MAGNESIUM AND

SOME MAGNESIUM ALLOYS
80

40

35

30

cn

a>

OJc 20

c

<^ i 5

V.<DQ.

10

5

4, AS EX"FRUDED ^2]\ J

COMMER

AS EX- CIALLY P FRUDED [i UREa

\MIA, h;\RD ROLL

1 ED [42]

50 100 150 200 250 300

TEMPERATURE, *K

ELONGATION OF MAGNESIUM AND

SOME MAGNESIUM ALLOYS

10

L 5

CHARPY K

^COMMERCIALLY PURE,

AS CAST [49]

COMMERCIALLY PURE,

AS EXTRUDED [49]

0 50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF MAGNESIUM AND

SOME MAGNESIUM ALLOYS
81

60

50

20

10

13

^AS EX TRUDED [ 25,64,81, 03]

[71]

HOT ROLl

^LATE)[

.ED 42]y

HC T ROLLED

AS EXlRUDED^

•«««• ^

MINIMI r Ai en /

TE

YIE

hJSILE

LD

50 100 150 200 250 300

TEMPERATURE, "K

STRENGTH OF AZ3I B

MAGNESIUM ALLOY
40

35

30 ^ 25

o

c

CVJ 20

c? '5 o

V.CL 10

82

ANNEALf:D L7lJ

I^S EXTRUDED [2 5,81,103]

^ '\ HO"^ ROLLED,(PLATE)[42]

1 50 100 150 200 250

TEMPERATURE, ^'K ELONGATION OF AZ 31 B

MAGNESIUM ALLOY

300

10

CHARPY V

CHARPY K

ANNEALED [7l]

'\"aS extruded [49, 103]

50 100 150 200 250

TEMPERATURE,

IMPACT ENERGY OF AZ3IB

MAGNESIUM ALLOY

300
83

90x10"
84

90x10^

80

70

_ 60

i/i CL- 50

O)

(/)

LlI a: 40

cn 30

20

10

80-T5I [i] , EXTRUDED AND

1 AGED

-T5[42]

AS EXTRU <UlJtD ANL

[42,8!]-

DED^.>Sn^

/AZ. OU

^4^EXTF

1) AGED

^

^"^^

Mac A 7 0 U" 1 o :>-

AS E xtruded/

1 A7 Qn.Tc;i/

/

TENSILE

YIELD

50 100 150 200 250

TEMPERATURE,

STRENGTH OF AZ80

MAGNESIUM ALLOY

300

20

o 15 c

CVJ c 10

-—

en 5

o

\-<DQ.

AZ 80--

EXTRUC

r5 [42],

)ED AND A AS E GED\

:XTRUDED y

'^I 80-

EXTRU[

T5I [i],

)ED AND AGED

50 100 150 200

TEMPERATURE, °K

ELONGATION OF AZ 80

MAGNESIUM ALLOY

250 300
85

50

10

1 V

3 \

HM 3IA- F, AS EXT

[25,

RUDED

71]

HM 31 A

AS EX1 / rRUDED/ ^^^

1 HM 21 / ^HM 21 A-T8

1 "ENSILE

riELD

50 100 150 200 250 300

TEMPERATURE, "K

STRENGTH OF THORIUM -MANGANESE

MAGNESIUM ALLOYS
86

/ HM 31 / AS e: A-F [25

KTRUDED

JHM 21 A T8 [71].

50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF THORIUM -MANGANESE

MAGNESIUM ALLOYS

10

T 5

CHA RPY V

/HM 3

/ AS E

1 A-F [71

XTRUDEC

],

)

/

SPECIM

A-T8[7l]

EN I STD. WIDTH

1 ^ 50 100 150 200 250 300

TEMPERATURE , "K

IMPACT ENERGY OF THORIUM- MANGANESE

MAGNESIUM ALLOYS
87

70x10

60

50

^ 40

UJ

q:

I- 30

20

10

3

^HK 31 ) \ ANNEA LED [71]

/HK 31 iA-H24 [2 5]

HK 31 A

[71]

HK3I /\-H24/^

^HK3lA, ANNEALED

U 1^ "7 t / rn\ 0 1 AAID V - TC

TE

YIEMSILE

LD

50 100 150 200 250 300

TEMPERATURE, 'K

STRENGTH OF THORIUM -ZIRCONIUM

MAGNESIUM ALLOYS

540232 O - 60 - 7
88

1 HK ^1Si/ 1 A AMf

J

1 jCAi pn \l ll

HK3IA-I-i24 [25]

0 50 100 150 200 250 300

TEMPERATURE , ELONGATION OF THORIUM-ZIRCONIUM

MAGNESIUM ALLOYS

T 5

CHAfRPY V

\hK3I A , ANNEAL ED [71] ^HK 31 A-T6[7l]

50 100 150 200 250 300

TEMPERATURE, "K

IMPACT ENERGY OF THORIUM-ZIRCONIUM

MAGNESIUM ALLOYS
70 X 10^

CO

if)

60

50

q: 40

I-

(/) 30

20

-T5, EXTRUDED [SS]

TENSILE

YIELD

$ 30

o

J 20

c

10 C

0)o

0) 0

Q.

50 100 150 200

TEMPERATURE,

STRENGTH OF Z K 60 A

MAGNESIUM ALLOY

50 100 150 200 250

TEMPERATURE, °K

ELONGATION OF ZK 60 A

MAGNESIUM ALLOY

250 300

1

1

1

I -4

EXTRUDE D [65]

300

100 150 200

TEMPERATURE,

IMPACT ENERGY OF ZK60A

MAGNESIUM ALLOY

300
90

60

20

10

r3

5^E 10 XA-HII [7 ]

lOXA-HI 1

TEf

YIE

sISILE LD

0 , 50 100 150 200 250 300

TEMPERATURE, °K

STRENGTH OF ZINC-RARE EARTH

MAGNESIUM ALLOYS
91

(0U

c

CVJ

40

35

30

25

20

c 15

o

t 10

^7 F 10 ^ - Hnil1 1 r 7 r

L

' /

50 100 150 200 250

TEMPERATURE,

ELONGATION OF ZINC -RARE EARTH

MAGNESIUM ALLOYS

300

10

I 5

CHAF?PY V

^ZE lOXA HI0[7i]

50 100 150 200 250 300

TEMPERATURE, **K IMPACT ENERGY OF ZINC -RARE EARTH

MAGNESIUM ALLOYS
60 X I 50

1 40

COa

30

(/) 20

10

"1 ALL SPEC IMENS ANNEALEC

REF. [95]

V AT d~7 C ) AT o7o 0 cr

^

4 % Li 6% Li \ Ck*. / % Li

'

T ENSILE

lELD

0 50 100 150 200 250 300

TEMPERATURE, K

STRENGTH OF LITHIUM - MAGNESIUM

ALLOYS

50

^ 30

-II % Li

j-Q % Li ^4 % Li

1 AL.L SPECIMENS ANNEALED

REF. [95]

1 1 AT 675*'F 0 50 100 150 200 250 300

TEMPERATURE, "K

ELONGATION OF LITHIUM - MAGNESIUM

ALLOYS
Austenitic Stainless Steels

100 150 200 250 300

TEMPERATURE,

STRENGTH OF AISI 200 SERIES

STAINLESS STEELS

60

50 « 40

CM 30 c 20

o

Q. 10

2(D2, ANNE/! LED [62,

"^^^

^201 , CO

^ [IS LD REDUC

)] ED 40% ( HARD)

50 100 150 200 250 300

TEMPERATURE, ^'K ELONGATION OF AISI 200 SERIES

STAINLESS STEELS
94

340x10"

320

300

280

260

240

_220

(^200

LU

tt: 180

160

140

120

100

80

60

40

1

•70I-M 0\J\ l\J nL ULU KULL

SHEET) [isc r\ L U /30I CO

/ (SHE

LD ROLLE

ET) [19]

) 65 %,

301 AN

[2,4

NEALED-

]

301 { HAL

:OLD DRA

F HARD [: WN, —

^41]

301 C OLD DRAW N, HALF I- ARD^

TENSILE

YIELD

^301 AN NEALED

50 100 150 200 250 300

TEMPERATURE ,«K

STRENGTH OF AISI 301 a 301-N

STAINLESS STEEL
95

70

COLD ROLLED 60%,( TO U.T.S. 231,000 psi) [59] / 50 100 150 200 250 300

TEMPERATURE , ELONGATION OF AISI 301

STAINLESS STEEL

100

^ANNEALED [2,4l]

^COL.D DRAWN , HALF HA RD [2,41]

IZOI)

50 100 150 200 250 300

TEMPERATURE , °K

IMPACT ENERGY OF AISI 301

STAINLESS STEEL
96

300x10

280

260

240

220

200

180

c/Tieo

if) 140

120

100

80

60

40

20

1 COLD DR/Q WN,{7I % R.A.)[63]

/COLD DR> .HALF HA

\WN

RD [59,60

/COLD DR

V

[63]

AWN (49 *Vr^ R A.)

ANNE/i LED[2,I8

59,6

.21,41

0,63] ^^

s V

^ANNEALE D [2,18,2 ,41,63]

N\

\

TENSILE — YIELD

50 100 150 200

TEMPERATURE, <»K STRENGTH OF AISI 302

STAINLESS STEEL

250 300
97

1\NNEALED1

1

[2, 18,21

,

59,60.6>3] \>

r

V. [63]

IKl l^Q O/ C .A.)\^

^COLD DR/

HALF H/^RD [60]

1

OLD DRAV

[63]

C /N,(7I%R

50 100 150 200 250 300

TEMPERATURE ,«K

ELONGATION OF AISI 302

STAINLESS STEEL

\ ANNEALEC

/ANNEALED [84]

•

'^COLD DRAWN, HALf- HARD [5£•] IZOD

---CHARPY K

50 100 150 200 250 300

TEMPERATURE ,*>K

IMPACT ENERGY OF AISI 302

STAINLESS STEEL
98

280x10

260

240

220

200

180

v>Q.

^160

UJ 140

q:

(/) 120

100

80

60

40

20

1

\NNEALED [41]

10% CO LD DRAWh [71] ^

\

/I0% CO LD DRAWrl[7l]

MSB ^

ANNE ALED [41] TENSILE

YIELD

1 50 100 150 200

TEMPERATURE ,*»K

STRENGTH OF AISI 303

STAINLESS STEEL

250 300
120

60

/(.28% S),ANNEALED [41]

A (.3 4%Se+.l ^t7oP),AN SIEALED

IZOD

50 100 150 200 250 300

TEMPERATURE, "K

IMPACT ENERGY OF AISI 303

STAINLESS STEEL
100

280

260

240

220

200 w 180

Q.

[2160

(T

I-

(/) 140

120

100

80

60

40

20

1 /COL ) DRAWN,

l[89]

TO UXS. 2 10,000 psi)

EALED [2, A1 1 CO 7

1, ,DO, J l,96J ^

\j\Jl-U u (TO U.T. 3. 210,000 psi)

^ANNE/^LED

**

TENSILE

-YIELD

1 50 100 150 200

TEMPERATURE,*>K STRENGTH OF AISI 304

STAINLESS STEEL

250 300
01

70

60

50

40

0)o

c

c

*. 30

c

O

Q. 10

ANNEALEC [2,41,62,7

:OLD DRAV/N,{TO U.T S. 210,000 psi)[89]

DRAWN,(TO U.T.S. 161

1 ,000 psi) [59]

COLD DRAWN,/

(TO UTS. 192,000^ psi) [59] 50 100 150 200

TEMPERATURE , K

ELONGATION OF AISI 304

STAINLESS STEEL

250 300

140

120

100 ^ 80

60

40

20

—CH

~IZ(

ARPY K ^

ANN EALED [2 41,96]

y

ANN EALED [6 D, 62,84]

COLD DRA\^N,(TO U.T.;3.210,000 F)si)[89]

50 100 150 200 250 300

TEMPERATURE ,»K

IMPACT ENERGY OF AISI 304

STAINLESS STEEL
280x10^

240

-200

Q.

102

120

80

40

^ / 15 To COLD Dl n A \kt k 1 ["Til xAWN L'

.I5%CC)LD DRAWr 1

TENSILE

YIELD

1 50 100 150 200

TEMPERATURE, *»K STRENGTH OF AISI 308

STAINLESS STEEL

250 300

^ 60

\l5% COL D DRAWN [71]

50 100 150 200 250 300

TEMPERATURE, °K

ELONGATION OF AISI 308

STAINLESS STEEL
103

280x10*

240

220

200

180

160

if)

liJ 140

in 120

100

80

60

40

20

1

/COLD DRAWN,( 7

[71] 0 U.T.S. 95, 000 psi)

ANN tALt

[71]

V

N

CULU U <AWN ^ ^

a -^ANNEAL

"--^

ED —TE

Yl£ NSILE

:ld

50 100 150 200

TEMPERATURE,*»K

STRENGTH OF AISI 310

STAINLESS STEEL

250 300

540232 O -60 -8
104

ANNEALED [7l], \ INCH GAGE LENGTH)

COLD DRAWN.dO UTS. 95,000 psi)[7l],

(I '4 INCH GAGE LENGTHtCOLD ROLLED

COLD ROLLED,( TO UTS. 159,000 psi) [59]

50 100 150 200

TEMPERATURE,

ELONGATION OF AISI 310

STAINLESS STEEL

250

ANNEALED [59]

50 100 150 200 250 300

TEMPERATURE, ^'K IMPACT ENERGY OF AISI 310

STAINLESS STEEL

106

rANNEALED [2,^H,7l]

\COLD Dl

( 1 INCHRAWN 25°/

GAGE LEN

'o[7l],

GTH)

50 100 150 200 250 300

TEMPERATURE , «K

ELONGATION OF AISI 316

STAINLESS STEEL

^AfJNEALED [2,41]

^ANNEALED [59] —CHARPY K

IZOD

1 50 100 150 200 250 300

TEMPERATURE, "K

IMPACT ENERGY OF AISI 316

STAINLESS STEEL
107

280x10^

260-

200

180

if) CLI60

CO(2l40

tr

I-<^I20

100

80

60

40

20

)

) /ANNEA .ED [41,6 3,71 ,98]

'ANNEALE D [41.63, 71,98]

v

' * ,

YIELD

1 50 100 150 200

TEMPERATURE

STRENGTH OF AISI 321

STAINLESS STEEL

250 300
50 100 150 200 250 300

TEMPERATURE, °K

ELONGATION OF A I SI 321

STAINLESS STEEL

ANNE/S LED[4i] •

CHARPY V

DD

50 100 150 200 250 300

TEMPERATURE, "K

IMPACT ENERGY OF AISI 321

STAINLESS STEEL
109

300x10

280

260

200

180

V)a.

140

120

80

60

40

20

10^

I. / COLD DRAWN l( ) %[7I]n^

V—

A MMP

[2.41 ,60,63,71] A

y COLD DRAWN 10 %» [711 N

ANNEicuIed'/^""

[2,41. S0,63.7l]

(

——TENSILE

YIELD

50 100 150 200

TEMPERATURE,

STRENGTH OF AISI 347

STAINLESS STEEL

250 300
110

80 I

\ ] r- 70

50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF AISI 347

STAINLESS STEEL —T^ANNEALE:D [2.41]

\anneaLED [79] —CH

^IZ(

ARPY K

0 50 100 150 200 250 300

TEMPERATURE, "K

IMPACT ENERGY OF AISI 347

STAINLESS STEEL
Q.

CO

UJ

a:

200

180

160

140

120

100

80

60

40

20

10

xANN

\/ (S/s EALED,

iME AS PA GE 96)

AIR COOLED FROM 1920 ^F,^

(SENSITIZED) [73],

(BRITISH SPEC. En 58a)

NEALED

SENSITI ZED-^^

[73]

TENSILE

---YIELD

L 50 100 150 200 250 300

TEMPERATURE,

EFFECT OF SENSITIZATION ON

STRENGTH OF AISI 302 STAINLESS

(0o

c

80

60

40

20

AIR COOLED FROM 1920 °F

(SENSITIZED) [73] , .(BRITISH SPEC. En 58a)

ANNEALED,

(SAME AS PAGE 96 )

50 100 150 200 250 300

TEMPERATURE, K

EFFECT OF SENSITIZATION ON

ELONGATION OF AISI 302 STAINLESS
12

100

90

80 ^ 70

s-S 60

LUO 40 - 30

20

10

CH/\RPY K —— cc

cc

O/ AO Oil OIK k 1 )LD WORKED, THEN SENSITIZED

REF [84]

/

V

/

-0%

/

20%^

^20%

/

50 100 150 200 250 300

TEMPERATURE ,*'K

EFFECT OF SENSITIZATION ON

COLD WORKED AISI 302 STAINLESS
113

\ 1 CHARPY K —CO ^

CO

LD WORK

LU WUKK

100 HRS

ED ONLY, % AS $ ED, THEN SENSITI

AT 1020 ^'F REF [84]

jHOWN.

ZED

yl 0 %

i

^10%

i 0%

/

/ /

> /

50 100 150 200 250 300

TEMPERATURE,

EFFECT OF SENSITIZATION ON

COLD WORKED AISI 304
'302

CHARPY K

ANNEALED

h- SENSITIZED AT

1000-1200 °F

50 100 150 200 250 300

TEMPERATURE, '^K IMPACT ENERGY OF SENSITIZED

WROUGHT STAINLESS STEELS
115

70

65

60

55

50 ^ 45

^^40

trUJ 35

LLi

S 25

20

15

10

5

47

318.

347\

^

3

AM

c:harpy h

• —SENSITIZED, 1350- 1650 ^'F

1 REF. [59] 1 50 100 150 200 250 300

TEMPERATURE, ^'K EFFECT OF THE SIGMA PHASE

ON WROUGHT STAINLESS STEELS
50

40

30

20

10

16

CHARPY K

REF. [50] 1250 °F-30MIN.^>^^

ANNEALED>

I035°F- ^OMIN. l035°F-4£

I250°F-48HR.

50 100 150 200 250 300

TEMPERATURE, **K IMPACT ENERGY OF SENSITIZED

CAST ACI-CF-8T STAINLESS STEEL

90

80

70

60

50

40

30

20

10

5

CHARf

RE

K

:F [50]

1035 ''F - 30 Mlh

A^JNEALED^

1035 <>F - 3 MIN.\

1250 °F- 3 MIN.\

i IO35OF- ^ 1250 OF - ;50 MIN.^

1250 °F- 48 HR\^

50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF SENSITIZED

CAST ACI -CF-20 STAINLESS STEEL
117

I 200x10

i 180

cl

if) en

UJ

or 80

60

40

20

10"

)

)

) ^ .ANfSIEALED [5 1]

I

) /ANNEAL ED

) ^

I

)

TENSILE

YIELD

50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF CASTACI-CF-8

STAINLESS STEEL

8 60

20

\annealED [51]

50 100 150 200 250 300

TEMPERATURE, "K

ELONGATION OF CAST AC! -CF 8

STAINLESS STEEL
118

80

70

60

50

40

30

20

10

rWARPV

RE

' K

F. [50]

ANNEALE

l035°F-3

I035°F- 2OMIN.—

\ MIN.^

1 250°F-30

I250°F - 3 MIN.-^

I250°F -48HR^^

I035°F -48HR--^

50 100 150 200 250 300

TEMPERATURE, ^'K IMPACT ENERGY OF SENSITIZED

CAST ACI-CF-8 STAINLESS STEEL

50

40

30

20

10

CHARPY K REF [50] 1250 OF- 30 MIN.~ 1035 OF - 30 MIN.^y^^^^^

100 150 200 250 300

TEMPERATURE, <»K IMPACT ENERGY OF SENSITIZED

CAST ACI-CF-8C STAINLESS STEEL
540232 O - 60 -9
Ferritic and Hardenable Stainless Steels

120

a.

320

3CX)

280

260

240

220

200

c/) 180

LU

QC

CO 160

140

120

100

80

60

40

:XTRA HA

[19]

^D, A(RC 51)

/j-SOAKlED A

^

'J

NV

>

{3TD. h TEMP

EAT TRE/

ERED AT

65] (0.06^

\T CYCLE

850 )

[ ^" SHEET)

^ COLD ROLLED BEFORE FINAL TEMPERING

A SOAKED 7'/2 MR AT /Y^K, WARMED TO ROOM

TEMPERATURE, THEN HELD AT TEST TEMP

ERATURE HR BEFORE TESTING.

TENSILE

. YIELD

50 100 150 200

TEMPERATURE, ^'K

STRENGTH OF HARDENABLE

AM- 350 STAINLESS STEEL

250 300
121

TEMPERATURE, °K

ELONGATION OF HARDENABLE

AM 350 STAINLESS STEEL

• 20

CHARPY V

STD. HEAl

(TEMPER

TREAT

ED AT 8eCYCLEtx>0°F) \

[3 ]

50 100 150 2 00 250 300

TEMPERATURE, "K

IMPACT ENERGY OF HARDENABLE

AM 350 STAINLESS STEEL
122

280x10*

260

240

220

200

180

^160

[2 140

cr^ 120

100

60

40

20

1

/QUENCHED AND T ^

[41]

EMPERED TO RC 39

C 39

/QUENCHE

^•^^^v^EM?

:D AND

ERED TO

^[41]

RC 23^^'

^'^^'^-^^.^NNEAL-ED [2]

ANNEALED

TENSILE

YIELD

1 200

o 0 ' 50 100 150

TEMPERATURE, ^'K STRENGTH OF AISI 410

STAINLESS STEEL

250 300
123

50 100 150 200 250 300

TEMPERATURE, *»K ELONGATION OF AISI 410

STAINLESS STEEL

100

80

60

40

20

IZ( CH

DD

ARPY K

[7 9]

410, OIL QUENCHED AND TEM

1 1 431, OIL QUENCHED AND TEM

PERED AT

pered at

II50°F —

IIOO°F\.^^

4I0,ANNE ALED[2]

[79] - /

r

50 100 150 200 250 300

TEMPERATURE, ^'K IMPACT ENERGY OF AISI 400

SERIES STAINLESS STEEL
124

140x10

130

120

I 10

100

90

CO^ 70

a:^ 60

50

40

30

20

10

1r'

/ANN EALED [2 .41]

\V

ANrJEALED--^

N

\\

\SV

TENSILE

YIELD

1 50 100 150 200

TEMPERATURE,

STRENGTH OF AISI 430

STAINLESS STEEL

250 300
125

40

50 100 150 200 250 300

TEMPERATURE, »K

ELONGATION OF AISI 430

STAINLESS STEEL
126

280x10

260

240

_220

Q.

.200

cn

C/) LUS 180

160

140

120

100

J \ JDITION H

If r

n

-875 [5] AMJ5-5644 (r

NDITION T ^ [65"

7-J PH

)

H-1050

AMS

(17- -5644,--7PH)

AN

(17

1S-5643E

-4 PH)

TENSILE

YIELD

1 0 50 100 150 200 250

TEMPERATURE, '^K STRENGTH OF PRECIPITATION

HARDENING STAINLESS STEELS

300

cc

Q)O

\_

<L> Q.

20

15

10

5

AMS 5643 B,(I7-4PH

CONDITION H-875

[5]

AMS-5644,(I7-7PH)/

CONDITION TH-1050

65]

50 100 150 200 250

TEMPERATURE, ^'K

ELONGATION OF PRECIPITATION

HARDENING STAINLESS STEELS

300
127

140

130

120

110

100

90

80

70

60

50

40

30

20

10

1 K^n IZ(

Mnr T V

VMS 5643

CONDITION

8,(17-4 PH H-II50

J 'V

FV52

OVER

UTS. 1

iOB[72],

AGED TO

46,000 ps —

i

AMS 5643 B[5] , - CONDITION H-875

! AMS5644,(17-7PH)-

CONDITION TH-II50

[6] ^AMS-56^'^4,- CONDI TION TH-IC 50[6]

50 100 150 200 250 300

TEMPERATURE , *»K IMPACT ENERGY OF PRECIPITATION

HARDENING STAINLESS STEELS
Low Alloy Constructional Steels

128

180 X 10 1 .. 1 1 CONDITION AS RECEIVED"

(PROBABLY COLD ROLLED)

-1040 [3'

10 ^0^

% \ —\

.\_^ \\

, \ \ \

\ \

\

\\

\ \

\

\

\

\

> \

\

\

V \

\

N

,

\

V 1010- \ [37]

TENSILE

YIELD

1

10 50 100 150 200 250

TEMPERATURE, <>K STRENGTH OF SOME AISI -SAE

PLAIN CARBON STEELS

300
60

50

29

c 30

0*o 20

Q. 10

\ T 1 CONDITION "AS RECEIVED"

(PROBABLY COLD ROLLED)

1010 [3 7l

K)40 [37]

50 100 150 200 250 300

TEMPERATURE, *»K ELONGATION OF SOME AISI-SAE

PLAIN CARBON STEELS

60

50

40

T 30

20

10

NC

i:)RMALIZE

70D

D

102

[2(i' 1030

[28]

1050

[28]

50 100 150 200 250

TEMPERATURE, K

IMPACT ENERGY OF AISI-SAE

PLAIN CARBON STEELS

300
200 X 10^-

190

30

COMMERCIAL HEATS WERE TESTED. | COMPOSITIONS WERE NOT GIVEN, BUT

"DIFFERENCES PROBABLY ACCOUNT FOR

THE SPREAD OF VALUES, ESPECIALLY

AT THE LOWEST TEMPERATURES.

100 150 200 250 300

TEMPERATURE,

STRENGTH OF AISI -SAE 1020 STEEL
80

70

60

50

ALLOY

STEEL C

c

- .21 %

Mn - .91 Si - .48

P

- .020

s

- .032

Ni -. 3 1 Cr - .34

Mo -

. 1 1

A B

C

- 25% .19 7o

Mn - .45 .43

Si - .054 .036

P

- .005 .01 1 s

- .025 .028

(PROBABLY NORMALIZED)

50 100 150 200 250 300

TEMPERATURE, ^'K TENSILE STRENGTH OF SHIP PLATE ft

LOW ALLOY CONSTRUCTIONAL STEEL

380 X 10^

360

340

320

300

280

</> 260

Q.

^240

LJ

cr

h- 220

200

180

160

140

120

100

0^

300 M ( rRICENT)

)Q a DOU

HEAT TRE

3LE TEMP

ATED [65l ERED)

N

"hy-tu F,"hEAT 7 [89]

•REATEO/

\

^ T

TENSILE

YIELD

0 50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF SOME SPECIAL

PROPRIETARY CONSTRUCTIONAL STEELS
134

25

if) ^ 20

300N1 (TRICEN" ) HEAT T =?EATED 55] \

/

L -"hy-tuf HEAT T REATED

[89]

^ 50 100 150 200 250 300

TEMPERATURE, ^ K

ELONGATION OF SOME SPECIAL

PROPRIETARY CONSTRUCTIONAL STEELS

20

Ch- CH

MRPY K ARPY V

"T - 1 HEAT TREATED

[11]

-

"HY - TUF

HEAT TR

"[89]."^

EATEDx ^ 300 M(TRICENT)

HEAT TREATED

[65]

o— —

^ 50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF SOME SPECIAL

PROPRIETARY CONSTRUCTIONAL STEELS
70 1 —^ \ \ \ J 0 50 100 150 200 250 300

TEMPERATURE,

TENSILE STRENGTH OF NICKEL ALLOY

CONSTRUCTIONAL STEELS

8.60 %Ni (.IOC), DOUBLE NORMALIZED

50 100 150 200 250 300

TEMPERATURE, «K

ELONGATION OF SOME NICKEL ALLOY

CONSTRUCTIONAL STEELS

540232 ,0 - 60 - 10
136

70

60

40

30

10

NOMir

9%

^AL COMf

Ni - .11 POSITION

7o C

CHARPY K CHARPY V

1

4 /

//

HE/

LOI\

!\T TREAT

GITUDINAL [77]^

/

f /

/

/

1 /

/

HEAT

[86]

rREAT'^2 \\

/

/

L 1 i

/

1 IFAT TRE[8,45,77,

!\T ^ 1 \ 86,I03]\

<^

\heat

TRAN

TREAT "^1,

SVERSE [77]

/

/

"^NHEAT TREAT "^1,

HEAT TRE:atment '^1 -DOUBL

TRANSVERSE [77]

i 1 E NORMALIZED FROM 1650

1 AND I450°F, THE

HEAT'TREATMENT# 2 - QUEN

N STRESS RELIEVED AT 1050 ^F. CHED a TEMPERED AT 1050 ^F.

I 1\ 1\ \ 1\ 1\ . I 0 50 100 150 200 250 300

TEMPERATURE ,*'K

IMPACT ENERGY OF 9 % NICKEL ALLOY

CONSTRUCTIONAL STEELS
137

OIL QUENCHED a TEMPERED

1 HOUR AS SHOW

V N

1320, 80C

RC-33 [f35] \^

/^I320,

\ RC-44

300*»F,

^[85^

^1340, 300 *F, RC-53[85]

1 0 50 100 150 200 250 300

TEMPERATURE, " K

IMPACT ENERGY OF AISI -SAE 1300 SERIES

CONSTRUCTIONAL STEELS

CHARPY K

5-

N(

/o Ni - .I0»> DRMALIZE[

'oC,-\

) \

13% Ni - .l07oC:

NORMALIZED

7^2

/

^ 7oNi- .I5»i FORMALIZE:d p[44]

" 50 100 150 200 250 300

TEMPERATURE , " K

IMPACT ENERGY OF SOME NICKEL ALLOY

CONSTRUCTIONAL STEELS
138

QUENCHED 8

"

1 HR. AS SHOV\

1 LMrtKtu

CH ARPY V ARPY K

2315,

RC 2 W Q , T 100

7 [66]

0°Fv

A

^2315,

^ NOR^

RB 90 [6( /lALIZED —

340, OQ

l200°F,-~-

?C 22 [66] —A

/

1

1

1

1 ^2330, OQ [89],

//

T925° F, RC32

r

u

J 2320,00,

RC42 li T400°F,

35] 2330^ y^' to(

0, ooaT/

^C48 [85]

tOO°F^^^

2340^ y

/

^

2330 [< NORMALIZ

37], / ED^/

/

/

/

/

RC

, 0Q,T40

54 [85]

0°F,

50 100 150 200 250 300

TEMPERATURE, *K

IMPACT ENERGY OF AISI -SAE 2300

SERIES CONSTRUCTIONAL STEELS
139

1 HR.AS

_CHARPY

1 tMrtntl

SHOWN

' V

J

3120, 30CfF RC43[85

\ >

3120,

RC35[85]

i —

3140, 300«'F,

RC52 [85]

1 0 50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF AISI - SAE 3100

SERIES CONSTRUCTIONAL STEELS

CHARP>' K

L _ -4023, NORMALIZED ft

, STRESS RELIEVED

\ AT lOOC^F. I ^

\ RB

\

83 [66]

0 50 100 150 200 250 300

TEMPERATURE , "

K

IMPACT ENERGY OF AISI - SAE 4000

SERIES CONSTRUCTIONAL STEELS
140

380 X 10' I

\

\ OQ a TEMPERED 4 HRS AT 450 ° F

100 150 200

TEMPERATURE,

STRENGTH OF AISI-SAE 4340

ALLOY CONSTRUCTIONAL STEEL

300

30

0, 25

o

.E 20

CVJc 15 £ 10

o

\_

<D^ 5

OQ a TEMPERED . . AT 1200 °F TO RC 34 [89]

OQ a TEMPERED 4 HRS AT 450 ° F a TEMPERING REPEATED. [^5]

100 150 200

TEMPERATURE,

ELONGATION OF AISI- SAE 4340

ALLOY CONSTRUCTIONAL STEEL

300
141

120

100

80

60

40

20

OQ a TEMPERED

1 HR. A

CHARP

S SHOWN

Y V

412 0, 1200 °F

4130, 900

RC 39 [66

O rr''1

41R

20, 1000 ' C 31 [85]

'F, — 4140,

RC 53

300 "F,

[85]

50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF AISI - SAE 4100

SERIES CONSTRUCTIONAL STEELS

60

50

40

30

20

10

OQ a TEMPERED

I HR. AS SHOWN

CHARPY V

CHARPY K 4320, 1000 ° F RC 33 [85]

4340, 1200 ^'F,^

RC 34 [89]

4320, 3000F,

RC 43 [85]

^4340, 300 °F

RC 54 [85]

4340, TEMPERED 4 HRS AT 450OF

a TEMPERING REPEATED L653 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF AISI - SAE 4300

SERIES CONSTRUCTIONAL STEELS
142

OQ a TEMPERE

1 HR. AS SHOWN

1

\j CHARPY V

RC 19 [e 0°F,\

15] \

/ A 620, 80C

RC 34 [Qt

'\

4620, 3C

RC 42 [e 0 °F,\

^4640, 3C RC 54

)0°F [85],

50 100 150 200 250 300

TEMPERATURE, *»K

IMPACT ENERGY OF AISI -SAE 4600

SERIES CONSTRUCTIONAL STEELS

OQ a TEMPERED

I HR. AS SHOWN

V- 48!5, IIOO°F,

RC 20 [40]

CHARPY V

7

. 50 100 150 200 250 300

TEMPERATURE, »K

IMPACT ENERGY OF AISI - SAE 48CX)

SERIES CONSTRUCTIONAL STEELS
143

OQ a TEMPERt

1 HR AT TEMP'S

iD

;. SHOWN

\

' CHARPY V

3120, I20(

RC 22 [8

J r 5] /

/

^

10, 800 °f C 38 [85]

-5120, 40C

RC 45 [ )°F,

35]

50 100 150 200 250 300

TEMPERATURE ,°K

IMPACT ENERGY OF AISI -SAE 5000

SERIES CONSTRUCTIONAL STEELS

N - NOF

IZOD

?MALIZED

6150, N [28]\

e 135, N [2 ^\

^6120, N [28]

50 100 150 200 250 300

TEMPERATURE,°K

IMPACT ENERGY OF AISI -SAE 6100

SERIES CONSTRUCTIONAL STEELS
220 X 10^- 144

200

180

<5 160

Q. CO^ 140

UJ

q:CO 120

00

80

60

/ '^^

\ TEMPER

850 «>F TC ED

) RC 34 [a 9, 103]

NORMA

[l03

LIZED

]

TENSILE

YIELD

1 50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF AISI-SAE 8630

ALLOY CONSTRUCTIONAL STEEL

25

20

cvj 15 c

Q>O

k 5

-NORMALI ZED [103 ]

-OQ a TE

AT 850

MPERED

op TO RC 30 [89]

r 50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF AISI-SAE 8630

ALLOY CONSTRUCTIONAL STEEL
145

100 150 200 300

TEMPERATURE, «K

IMPACT ENERGY OF AISI-SAE 8600

SERIES CONSTRUCTIONAL STEELS

30

25

20

15

10

5

OQ a TEMPEREC

CHARPY K

) 1 HR. AS SHOWN

8750, IOC RC 42 [66>] \

50 100 150 200 250 300

TEMPERATURE, «K

IMPACT ENERGY OF AISI-SAE 8700

SERIES CONSTRUCTIONAL STEELS
146

UU a 1 CHARPY

LMrLK

K

J 1 HK. A

1

k c OLJ r\\ki N

9260, 8S RC 47 [6>6] \ _

50 100 150 200 250 300

TEMPERATURE, »K

IMPACT ENERGY OF AISI-SAE 9200

SERIES CONSTRUCTIONAL STEEL

QUENCH

CHARPY

iED a TE

K :mpered 1 HR.AS SHOWN

9420,

RC 2 WQ, 1000

7 [66] \^

\944

RC

0, OQ, 90C

40 [66]

50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF AISI-SAE 9400

SERIES CONSTRUCTIONAL STEELS
147

8IB40, RC43, LOW CHEMISTRY ^ 50 100 150 200 250 300

TEMPERATURE, *K

IMPACT ENERGY OF BORON STEELS
Superalloys (Alloys of Co, Ni, Cr, W, Mo)

260 X 10

240

148

220

200 — 180

CL

CO

LlI 140

CO 120

100

80

60

1. I800°F,WQ a AGED 16 HRS. AT 1325 °F, AC

2. I900°F, WQ a AGED 16 HRS AT I300°F, AC

3. 1850 °F, OQ + 4 HRS. AT I550°F, AC a AGED 16 HRS. AT 1300 °F, A.C.

I I I 50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF SUPERALLOYS
149

80

70

60

50

40

30

20

10

0

1. HOT ROLLED 8 STRESS RELIEVED AT 2200 °F.

2. 1800 °F, WQ a AGED 16 HRS. AT 1325 ^F, A.C.

3. ANNEALED AT 1800 °F, A.C.

4. WARM WORKED 8 STRESS RELIEVED AT 1200 °F

5. COLD DRAWN 8 STRESS RELIEVED.

50 100 150 200 250 300

TEMPERATURE, °K

IMPACT ENERGY OF SOME SUPERALLOYS
300 X 10^

280

260

240

220

200

180

CL

C/)

liJ 140

cr^120

100

80

60

40

20

J 150

HEAT TREATMENTS \

'

1. HOT ROLLED a STRESS RELIEVED AT 2200 °F

2. 2350 °F, 00 a AGED 46 HRS. AT I400°F

3. 22 50 °F, WQ a AGED 16 HRS. AT 1400 °F, A.C

100 150 200

TEMPERATURE,

STRENGTH OF COBALT BASE

SUPERALLOYS

300
151 70

60

50

40

OJc

§ 30

a>Q.

20

HEA1

GIVE

r TREAT^

EN ON P/3^ENTS S/

^GE 150.

\ME AS

1 "haynES" ALLOY No. 25 (L'

HT. TR.*I [71; 605)

S- 81 HT.T

o [3],

R.*3 \

- 36 1 HI TR *3 >^

*Bf

hRITISH [73]^—^TTR.*2

50 100 150 200 250

TEMPERATURE, °K

ELONGATION OF COBALT BASE

SUPERALLOYS

300

540232 O - 60 - 11
152

180

170

160

150

140

C;>I20

NO

100

90

80

70

60

50

40

0^

RC)LLED AND ANNEALED

y'HAST ELLOY"B [66]

/HASTELLOY"C [ 66]

"HA STELLOV

h reel ] \

\

' X'MSTELL 3Y"C

HASTELL

B s —

V

^-v HASTEL .oy"a/ *^

"^^ ~—

—— TEINSILE

ELD

50 100 150 200 250 300

TEMPERATURE, »K

STRENGTH OF SOME PROPRIETARY

NICKEL- BASE SUPERALLOYS
153

70

60

g 50

C

CVJ 40

c

c 30

o

S 20

ID

"HASTE

- LLOY"B [ 66] \

\STELLO'r"A [66]

/

/

^STELLO^ '"C [66]

F OLLED AND ANNEALED

50 100 150 200 250 300

TEMPERATURE, <»K ELONGATION OF SOME PROPRIETARY

NICKEL-BASE SUPERALLOYS

80

70

60

50

40

30

20

^"HASTELL

CHARPY

1 .OY"X [67 V

] \

•^"haste

CHAR

lloy'c [ PY V 67]^ ^^^^^\STELLO

CHARPY

r"B[67] - U

\"HAS TELLOY"

.ED AND / E NOTCH r RELIEVEC

A [66]

\NNEALED

JOT GIVEN ^ HOT Fpolled AN ) AT 2200

ROLl

(TYP

D STRESS

)op

50 100 150 200 250 300

TEMPERATURE, *»K IMPACT ENERGY OF SOME PROPRIETARY

NICKEL-BASE SUPERALLOYS
30x10^

Brazing and Soldering Metals

154

100 150 200 250 300

TEMPERATURE,

TENSILE STRENGTH OF TIN - LEAD

SOLDERS

120

100

80

cp 60

a. 40

20

%l

%

ELONGATION IN 2 INCHES

DEDUCTION OF AREA

ALLOYS AS

CAST.

50 S 25 Sn - n -50Pb[

75 Pb[58

46]^ ^^^-^ 5 Sn-9 5 Pb[46]^^ —

^50Sn-5 OPbLse]

50 Sn -4C)Pb [58]

'

r 50 100 150 200 250 300

TEMPERATURE,

DUCTILITY OF TIN - LEAD SOLDERS
155

30

25

20

15

10

5

1 1 CHARPY V

ALLOYS AS CAST

y5Sn -95Pb[4€

lOSn-S 0Pb[^6]v

\

^15 Sn-85 Pb [46]

50Sn-50Pb[46]N

50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF TIN-LEAD

SOLDERS

30

25

20

CHARPY V

ALLOYS AS CAST

.2.5 Ag-97.5 Pb [46]

15

' 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF SILVER -LEAD

SOLDERS
156

12 X 10

10

8

</) Q.

(n 6

CO

01

^1.6 A(3 10 on cB3.4 Pb, AS CAST

[46]

1 l.5Ag-l.0Sn-97.5Pb^

[54],

\g-97.5 P

AS CAS

3 [46],

T COND

PRE^

TION NOT

pUMED AS

GIVEN,

CAST.

50 100 150 200 250 300

TEMPERATURE, *K

TENSILE STRENGTH OF SILVER- LEAD

SOLDERS

60

50

o

c 40

c 30

§ 20

v.Q.

10

5Ag-97.5

f\S CAST

Pb[46],

1.6 Ag-15 S AS CAS

In -83.4 P

>T

5 [46],

50 100 150 200

TEMPERATURE, ''K 250 300

ELONGATION OF SILVER - LEAD

SOLDERS
O 50 \00 150 200 250 300

TEMPERATURE , STRENGTH OF MISCELLANEOUS SOLDERS

14 X 10^

50 100 150 200 250 300

TEMPERATURE, K

STRENGTH OF INDIUM SOLDERS
158

140 X lO

130

120

110

100

90

0)^ 80

(/)

IJJ 70

60

50

40

30

20

10

yJ\J U U 930°

-50 Zn [lOO] F ANNEALED

^45Ag -30 Cu - i^5 Zn

[58] AS CAST

1 '

1 ^70Ag-20Cu-IOZn [58]

AS C AST

\s—

0 Cu - 50 Zn

TENSILE

YIELD

1 50 100 150 200 250 300

TEMPERATURE , **K STRENGTH OF BRAZING ALLOYS
159

60

50

40

30

20

10

1 %EL

%RE

1 ' 1 ONGATIO

:duction

1

N

OF ARE/!

1 50 Cu-50Zr

930 **F ANN

1 [100].

EALED \

45 Ag -30Cu -2 5 Zn [58] AS CAST —

\70Ag -20CU-I OZn [58],

AS CAST

50 100 150 200 250 300

TEMPERATURE,

DUCTILITY OF BRAZING ALLOYS
Miscellaneous Alloys and Pure Metals

160

METAL

ANNEAL

TEMR,**R

TENSILE STRENGTH

p s i 7o ELONGATION,

.79"GAGE LTH.

300 *»K 90 K 300 ^'K 90*»K

Ag 147 2 30,900 40,700 23.0 38.0

Cd 392 6,500 20,600 42.0 18.0

Co 2012 61,100 104,400 4.0 5.0

Mo 2012 76,100 108,500 20.0 0.2

Sn 302 5,400 15,800 52.5 3.6

Tl 302 1,120 3,170 56.0 32.0

Zn 302 16,500 14,200 44.0 0.6

REF. [26]

STRENGTH AND DUCTILITY OF SOME

COLD WORKED AND ANNEALED

PURE METALS
161

160

140

120

Q.IOO

(/> 80

UJ

q:en 60

40

20

^>|cHOT ROLLED [ \—

\\ ^

V\ ACOM p. %

.C - 1.40

Mn - 12. 1

Si - .12

P - .060

S - .012

TENSILE

YIELD

50 100 150 200 250 300

TEMPERATURE, K

STRENGTH OF AUSTENITIC Mn STEEL

60

^ 50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF AUSTENITIC Mn STEEL
162

200 X 10-

.-180

Q. CO 160

140

120

100

u

-AM

AN

3 5624,

NEALED [ 20]

T ENSILE

50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF HIGH EXPANSION STEEL

80

60 ^ 40

c

0) 20

Q.

A^

ANN

/IS 5624,

EALED [2(

50 100 150 200 250 300

TEMPERATURE,^K

ELONGATION OF HIGH EXPANSION STEEL

120

100

80

60

40

CHARP^ K AMS 5 ANNEALE

624.-^

:d [20] ^

50 100 150 200 250 300

TEMPERATURE, ^'K IMPACT ENERGY OF HIGH EXPANSION STEEL
163

I

100

90

80

70

60

50

40

30

20

10

specimens: 1.2" DIA.STD. CAST IRON

ARBITRAT!0^

UNNOTCHED.

J bar; as IZOD TY; CAST,

PE TEST.

S AUSTEN

[99] TICx

(D AUSTENITIC [99]

^ii-Mo AC! :ULAR [99

PEARLITIC

1 GRAY IR(DN [99]

50 100 150 200

TEMPERATURE, «K

NOMINAL compositions:

250 300

iron 7oC %Si 7oMn 7oNi 7oCr OTHER

© 3.2 2.0 1.2 3.0 1.9 . 7 1.6 .5 Mo

® 2.7 1.9 1. 1 14.5 2.2 6.3 Cu ® 2.3 1.5 1.0 34.5 3.0 IMPACT ENERGY OF SOME

FLAKE GRAPHITE CAST IRONS

30x10-

LiJ 20

50 100 150 200 250 300

TEMPERATURE, K

TENSILE STRENGTH OF A GRAY CAST IRON
164

SPECIMI

UNNO

ENS ANNEALED,!'

TCHED. CHARPY 1 SQUARE

^YPE TES

c 2^"SPAN

T. R EF. [35]

IRON

IRON*

T^IR 0N*3N^/-f

/ /\|F?0N*4

compositions:

specimen

IRON I IRON 2 IRON 3 IRON 4

50 100 150 200

TEMPERATURE, '^K %C %Si

3.63

3.52

3.33

3.29

.93 2.03

2.73

2.09

.35 .37

.40

.38

%S

.010

.013

.013 .014

.024

.028

.028

.162

250

%Ni

.60

.7 1 .71 .72

300

%Mg

.042

.055

.057

.049

IMPACT ENERGY OF SOME

FERRITIC NODULAR CAST IRONS
165

150 X 10*

140

130

120

110

100

90

(/>

(/) 70

UJ

q:CO 60

50

40

30

20

10

^ 1 NOMINA!

composition:

C - .025

Mn- .030

Si - .003

P - .003

S - .025

"COLD DF?AWN 24 % [34]

V-

\

N ANNLALE

[34] \\\

V. \\\

\

^ \

T ROLLED

[17,21.34,37]

V^^HOT ROLLED

TF

YIELD POINT

YIELD STRENGTH, (O.J

1 1 1 Vo OFFSET)

50 100 150 200

TEMPERATURE, *K

STRENGTH OF INGOT IRON

250 300
1 ZOD

-JHOT ROLLEC r n 1

/

1

0 50 100 150 200 250 300

TEMPERATURE,

IMPACT ENERGY OF INGOT IRON
15 X 10^

S. 10

of

UJ 5

or

167

J, 76 ],AS CAST

50 100 150 200 250 300

TEMPERATURE,

TENSILE STRENGTH OF COMMERCIALLY

PURE LEAD

40

o

.E 30

CVJ 20

c

Q.

/ [58, 76 ],AS CAST

50 100 150 200 250 300

TEMPERATURE,

ELONGATION OF COMMERCIALLY

PURE LEAD

50r40-

£ soil 20-

10-

CHARPY K /76]

50 100 150 200 250

TEMPERATURE

,

IMPACT ENERGY OF COMMERCIALLY

PURE LEAD

300

540232 O - 60 - 12
240x10^

220

200

180

168

160

Q.

-140

in

if)

LlI q: 120

H

100

80

60

40

20

nlon r

REF.

IDI TV 1 IC Unl 1 T Ur

;i04]

<ANIUM + ^ /o MUL

"' —

V DnCMI IK -Y DULNU^

1 c

/-TEN*>iLE a Yl ELD

B

^^"^

B

' B ^ > V. A

E

E

TENSILE

YIELD

50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF A MOLYBDENUMURANIUM ALLOY

HEAT TREATMENTS

As cast.

B. Solution treated 3 hrs. at 850® C, water quenched.

C. Solution treated 3 hrs. at 850® C, water quenched, aged I hr. at 450 ®C.

D. Solution treated 3 hrs. at 850*0, furnace cooled at 5**C/min. E Solution treated 3 hrs. at 850® C, furnace cooled to 580®

and held 2 hrs.,then reheated to 625 ®C, held 2 hrs., water

quenched.
169

1— « t I HIGH PURITY URANIUM + 2% MOLYBDE

|REF. [104] 1

1 NUM

HEAT TF EATMENTS> SAME AS GIVEN ON PAGE 168. E-

^ B

" C

50 100 150 200 250 300

TEMPERATURE, " K

ELONGATION OF A MOLYBDENUM

URANIUM ALLOY

1 1 1 HIGH PURITY URANIUM t 2 7o M

CHARPY V . REF. [i04]

OLYBDEN UM

E^ ^

B

C

50 100 150 200 250 300

TEMPERATURE, "K

IMPACT ENERGY OF A MOLYBDENUM

URANIUM ALLOY
Ql

280

260

240

220

200

180

160

in

CO

IaJ 140

CO 120

100

80

60

40

20

10 ——

FROM 147

AMMPAI CP

2*^ [21]

1 ^^^^ /

A|HL_l_U 1 HYT RD J FROM 147

MIM AMMFAi IN C_Mi_CiJ rn 2°F [21]

a

k

ALLOY B \S

ALLOY C, \ ^\ALLOY D, AS FORGEl

ROM

922° F [2 ^[21]

\

LLOY D- ^ i;^—N Y

t

COMPOSITIONS

ALLOY Ni C Mn Si A 24.5 .16 1.00 .30

B 3L4 .70 .82 —

C 35.8 .16 .86 .08 D 57.5 .34 1.31 .14

E. 58.8 .27 1.64 28

TENS

YIELC

ILE

) 50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF NICKEL- IRON ALLOYS
U 50 100 150

TEMPERATURE

ELONGATION OF NICKEL

200 250 300

IRON ALLOYS

80

70

60

50

I 40

30

20

10

CHAR PY K

/ NORM

r E , FOF

ALIZED F GEO a ROM 1700 •F [74]

4

A9.4 Ni [l€ NNEALED

1 AL -OY E, AS5 FORGED

35. AN3Ni [i6]r

NEALED

AniniCAL.C.1 ^25.9 N ANNEA

Ii[i6],

LED

50 100 150 250 300

TEMPERATURE

IMPACT ENERGY OF NICKEL-IRON ALLOYS

200
172

160x10^

140

120

g^lOO

[2 80

tr

h-^ 60

40

20

0"

< .010",

ILQF MINU ANin Y1 SHEET,

UM ANNE

[78]

\

\

> VVACU

N \-

:aled

\ \

ANN EALED[iC

TENSILE

YIELD

50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF COMMERCIALLY

PURE TANTALUM
140 X 10^

130

120

110

100

90

^80

CO

C/) 70

a:^ 60

50

30

20

10

COLD WORKED 50%

[38]

ANNEALED

AT 1472 **F [38]

HIGH PURITY

VACUUM ARC REMELTED [lOO],

40|—ANNEALED I400«F IN ARGON

TENSILE

YIELD

50 100 150 200 250 300

TEMPERATURE,

STRENGTH OF COMMERCIALLY

PURE ZIRCONIUM
174

50

40

30

CMc

c 20

Q>O

\_Q.

10

V HIbH PUKI 1 Y VACUUM ARC REf

ANNEALED 1400

vIELTED,

IN AR(SON

^^ANN EALED 14 72 **F [38

^COLD WORKED 5 0 7o [38]

50 100 150 200 250 300

TEMPERATURE, ^'K ELONGATION OF COMMERCIALLY

PURE ZIRCONIUM

30

20

10

CHARPY

1

' V

/HOT RO LLED AT 1200 *»F [38]

50 100 150 200 250 300

TEMPERATURE, »K

IMPACT ENERGY OF COMMERCIALLY

PURE ZIRCONIUM
Nonmetallic Materials

40xlC?

35

30

25

Q.

20

en^ 15

q: 10

5

0

175

1. POLYETHYLENETEREPHTHALATE ("MYLAR")

2. POLYTETRAFLUOROETHYLENE ("TEFLON")

3. POLYTRIFLUOROMONOCHLOROETHYLENE ("KEL-F")

4. POLYVINYLCHLORIDE , 5. NYLON i DEGREE OF CRYSTALLINITY NOT STATED

©[71

100 150 200

TEMPERATURE, ^'K TENSILE STRENGTH OF PLASTICS

300

o

CVJ

25

20

15 ^ 10 c

Q>O

0) 5

Q.

1 1

1 (VALUES ARE REPORTED

FROM 20 TO 120 7o ) \

©[27

NOTE: REF [27] REPORTS "NIL" FOR PLASTICS (2) & ® AT 198 a BELOW.

50 100 150 200

TEMPERATURE , ELONGATION OF PLASTICS

250 300
15x10^

toQ.

-10

(/) UJ

a:

h-

(/)

<

UJ

crm

AT VAF AS SHC

(lOUS RAT

)WN, psi p REF [61]

ES OF LO

er sec,

1

'—' AOING

A- 80 D

/-lO

I -1

50 100 150 200 250 300

TEMPERATURE

STRENGTH OF ABRADED

BOROSILICATE OPTICAL GLASS
References

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2. Allegheny Ludlum Steel Corp., Stainless Steel Handbook (1951).

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179
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Boulder, Colo., August 3, 1959.

180 U.S. GOVERNMENT PRINTING OFFICE: 1960 O—540232

^1