Mechanical Properties of Structural Materials at Low Temperatures a Compilation from the Literature R

AlllOO TflflMTM

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

tures ; 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 III Scales for interpolation IX Graphs for: Aluminum and its alloys 1 Copper and its alloys 36 Nickel and its nonferrous alloys 62 Titanium and its alloys 72 Magnesium alloys 79 Austenitic stainless steels 93 Ferritic and hardenable stainless steels 120 Low alloy constructional steels 128 Superalloys (alloys of Co, Ni, Cr, W, Mo) 148 Brazing and soldering metals___ 154 Miscellaneous alloys and pure metals 160 Nonmetallic materials. 175 References 177

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 presented 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 performed 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 mathe- matical 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 compen- sated 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 com- plicated 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 mis- places the responsibility for safety or reliability, but in complex calculations 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 history 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 titanium 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 imper- fections 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 Amer- ican Society for Testing Materials. The notation "Charpy V" refers 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 specimens 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 con- tain 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 men- tioned 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 am- biguities 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 diame- ters) 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 Fahr- enheit, which is common in metallurgy in this country. Also w^henever the metallurgical condition of the specimens was stated in the literature, 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 structural 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 pos- sess 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 redistribut- ing 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. Mag- nesium 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 gain- ing 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 con- tains 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 considera- tion, 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 satisfactory 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 11

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 ! 1 1 M 1 1 1 1 I I I 1 -460 -370 -280 -I90 "100 -I0 80 ° TEMPERATURE , F -o- AlH3d0ad nV0INVHD3l/y -31VNiad0 06 08 OL 09 OS 0^ OC OZ 01 0

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 I 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 M h M 1 1 ml

1 M M M 1 1 1 M M M 1 M M 1 M M 1 M M 1 1 1 1 1 1 i M 1 M M M M 1 1 1 1 1 1

-460 -370 -280 - 190 "100 -I0 80 -o- TEMPERATURE, ° F Ald3d0dd nV0INVH03t/\l - 3ivNiaao 02 SI 01 S 0

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 I 1 i

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 M 1 1 i 1 M 1 1 1 M 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 II 1 1 1 1 1 1 1 -460 -370 -280 "190 - 100 -I0 80 -o- TEMPERATURE, °F Aia3doad nvoiNVH03i/\i - 3ivNiad0 081 091 Ot^l OZI 001 08 09 01? OZ 0

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 II II M 1 1 1 M 1 M 1 M 1 1 1 -460 -370 -280 "190 "100 -I0 80 -o- TEMPERATURE, °F Ald3d0dd nV0INVH03l/\l - 3ivNiaao S^ Ot7 S£ 0£ SZ OZ SI 01 s 0

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 M M M M 1 1 1 ill

SCALES FOR INTERPOLATION ON GRAPHS IN THIS COMPILATION

IX l |lllllll l l ll lll l ll l ll l!lll l ll l ll llll | | | | 0 50 100 150 200 250 300 TEMPERATURE ° K , Ald3dOad nV0INVH03l^ -31VNiaH0 06 08 01 09 09 Oi7 02 OZ 01 0

I I I I I I I I I I I I I I I I I I I I I I I I I I I I M I I I I I I I I I I I I I I I I

Ald3d0dd nVDINVH33l/\l - SlVNIOdO 02 SI 01 9 0

I I I 1 I 1 \ L_J lJ I I I lJ LJ \ lJ-

|IIIIIIIII|MIIIIIII {IIIIMII|||IIII|||||III||||||||||||||||| 0 50 100 150 200 250 300 TEMPERATURE, ® K

Aia3d0dd nVDINVH03l/\l - 31VNiaa0 081 091 0t7l 021 001 08 09 Ol7 OZ 0

llllllllllillillilllllilliilillllllliiiliiiiliiiiliiiiliiiiliiiiliiiil

I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I

I I I I I I I 0 50 100 150 200 250 300 -o TEMPERATURE, ° K Aia3dOdd nVDINVH03IAI - 31VNiadO St^ Ot7 S£ 0£ S2 OZ SI 01 Q 0

I I I I I I I 1 I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I

SCALES FOR INTERPOLATION ON GRAPHS IN THIS COMPILATION

X Aluminum and Its Alloys

50 100 150 200 250 300 TEMPERATURE, K

YIELD STRENGTH OF 1 100 ALUMINUM 2 3

100 150 200 300 TEMPERATURE, *>K ELONGATION OF 2011 ALUMINUM 90x10^

80 3], ROLLEC 1, FORGED ROLLED, GORGED, EXTRUD ED 70

4 cl 50 cn cn LiJ 40

ROLLED , DRAWN ^0[4] , 30

10 TENSILE YIELD

1 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 2014 ALUMINUM

4J, ROLLE:d, drawn

T4 [4,43] FORGED, T4[4], F{OLLED,DF{AWN .EXTRUDE

-AT6[4,43],FtOLLED, F( )RGED

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 2014 ALUMINUM 40

4,90] c 20

§ 10

50 100 150 200 250 300 TEMPERATURE ,«K ELONGATION OF 2017 ALUMINUM 80x10 ^2018- T6I[4]

70 22|8-T( >l[4] ^ 60 __^^2on3-T6I

•^5 50 Q. i2l8-T6l

10 TENSILE YIELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 2018 AND 2218 ALUMINUM ALLOYS

2218 T6I [4] 20 ^ Q vl- 15 \ JO ^2018-T 61 [4] c 10 o

^ 5

50 100 150 200 250 300 TEMPERATURE, *»K ELONGATION OF 2018 AND 2218 ALUMINUM ALLOYS 540232 O -60 -2 50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF 2024 ALUMINUM 80x10 • CONDIT ION OF SP ECIMEN IN REF. [58] S NOT ST ATED

BUT IS. PRESUME D TO BE A NNEALED. 70

If5 L82,94j^ 60 d ^ANNEAl.ED [58,66>]

w 50

UJ o or 30

10 TENSILE YIELD

1 50 100 150 200 250 300 TEMPERATURE, <>K STRENGTH OF 2025 ALUMINUM

T6 [ 32,94] o

ANNE \LED [66]

^ANNEALE d[58]/^

50 100 150 200 250 300 TEMPERATURE, K ELONGATION OF 2025 ALUMINUM 10

1 70x10^-

^ HIS [4 ,43] w 40 Q.

^F, AS RO LLED [ 4] cn (PLAT E) (/) UJ [4,66] c/) 30 ^ H 18 0[4,4

20 H

TE NSILE YllELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 3003 ALUMINUM II 60

LJ 1 O AS ROLLE ""^^LAT! ^ 30

§20 - H I8[4,. V.

^ 10

50 100 150 200 250 300 TEMPERATURE, ^'K ELONGATION OF 3003 ALUMINUM

30 c HARPY K

25 /HI2 75]

' 50 100 150 200 250 300 TEMPERATURE, «K IMPACT ENERGY OF 3003 ALUMINUM —

12 80 X 10

60 F AS ROL LED 8 [4] (PLATE) 4] w [ 50 J Q. cn »w^_lH38\ [2 40 0[4J'r y 1

C/> 30

/ F 20

10 TENSILE YIELD 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 3004 ALUMINUM —

13 80x10

70 5 [4]

^50 —

CO [S40 (r ^ 30

10 TENSILE ——YIELD 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 4032 ALUMINUM

S 10 o \_ CL ^

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 4032 ALUMINUM 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 5050 ALUMINUM

50 /0[I 40 Q ^ 30 .H34[l] 20 c 38[l] 0)o i> 10 Q.

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 5050 ALUMINUM 80x10'

TENSILE YIELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 5052 ALUMINUM

—

17 90x10"

80 / H38 70 i_l -I/; r H OH [ J 60 H 3i (A Q. 50 0 [43]^ crT CO 40 — n o*t CO 30 /O

10 TENSILE YIELD

1 50 100 150 200 250 300 TEMPERATURE, *»K STRENGTH OF 5056 ALUMINUM

0[43 ^ 40 o c

CVJ 30 c -H34[i], IN 4D 20 O \ H38[^ 3] k 10

0 50 100 150 200 250 300 TEMPERATURE, <»K ELONGATION OF 5056 ALUMINUM H 113 CO 40 LU H 30 if)

10 TENSILE YJELD

50 100 150 200 250 300 TEMPERATURE ^^'K STRENGTH OF 5083 ALUMINUM

40 [1] 30

>-H 113 [

o> 10 cl

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 5083 ALUMINUM

20 70

60 - ^ r 1 ^0 L ^ 50 o c 40 CM -H32 [l] c % IN 4D 30

^20 Q. -HII2 [52 ] 10

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 5086 ALUMINUM

SPECIAL CHARPY V SPECIME ViS - ASTM STANDARD E XCEPT W IDTH WA< 25 r\KI IN/ 1 KC llkl/^ LJ

T 15

-T -0 [71] 10

50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF 5086 ALUMINUM

22 60

1,71] S 50 o c 40 H32[7l] 30 , r ii H 38 L'J H 3^\ LU IN % 4 D % 1 N 4D \ o 20 \-

Q. 10

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 5154 ALUMINUM

120 CHARP r V

100 0[7l]- 80

50 100 150 200 250 300 TEMPERATURE/K IMPACT ENERGY OF 5154 ALUMINUM 80 X 10"

50 100 150 200 250 300 TEMPERATURE STRENGTH OF 5356 ALUMINUM

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 5356 ALUMINUM

54023E O - 60 -3 :

24 90 X lO"u

80 r -H 321 L u 70

Q. 0 ."] " 50 CO

cr 40 1 321 30

10 T ENSILE lELD 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 5456 ALUMINUM

]

c 20 - H i2l [l]

Q 10 o v_ Q. 0 50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 5456 ALUMINUM 25

70x 10^-

T4[4.43] 45

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 >,43,7l]

r4[4.43] 35 Q vcf 30 c /T6[ 4,43,71, IC )3] 25 c a>o 20 Q.

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 6061 ALUMINUM

15 CI HARPY K

\T6[7f), 103]

50 100 150 200 250 300 TEMPERATURE/K IMPACT ENERGY OF 6061 ALUMINUM 1

AL L SPECirvIENS PRC)M EXTRLiSIONS

/0[4,^;3]

/T42[43 ] Q 40

T5[4,43] c 30 /

§ 20 — 1t6[ 4,43]

0 50 100 150 200 250 300 TEMPERATURE, ELONGATION OF 6063 ALUMINUM 30 70x10'

60 /T6, F()RGED[4; 50

Q. 1 - 40 (O (/) UJ q: 30

10 TENSILE YIELD

1 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF 6151 ALUMINUM

1r-

J, FORGED [4]

50 100 150 200 250 300 TEMPERATURE, K ELONGATION OF 6151 ALUMINUM —

31 lo--

)

) /T6, SHE iT [43, 71]

— /T6, RO 43 7 1 103] 1

/ V

) ^ fje, EXTFFUSIONS N.^4^ 57] Q.

(/) if) ^^^^^ UJ ) a: T6, SHE et/ * — ) \ ^T6, ROD

) ,43]

)

TENSILE —-YIELD

1 50 100 150 200 250 300 TEMPERATURE, *»K STRENGTH OF 7075 ALUMINUM 10

/T6, R DD, CHARF K [103] / "^^ , EXTRUS IONS [57]; / IZOD

^ 5

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

> 50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF 7075 ALUMINUM 100 150 200 250 300 TEMPERATURE,*»K STRENGTH OF 7079 ALUMINUM

15 [65] CVJ -T6, FOF?GED 10 c 8 5

Q. 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

50 100 150 200 250 300 TEMPERATURE, °K STRENGTH OF SAND CAST ALUMINUM ALLOYS 35 CURVE ALLOY REF.

1 4 3 [ 1 ]

- 2 142 T77 [ 1 ]

- 3 355 T5I [ 1 ] 4 355 - T 7

. TCI 5 356 T 51 r 1 1

' 6 356 - T7 [ ]

h ' 4_^— ^^3 2/

TEMPERATURE, °K ELONGATION OF SAND CAST ALUMINUM ALLOYS

10 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 , HlARD [71]

ANNEALED [9,17, 33,70,71,6^3, 88,90]

^NNEALED [33,"rol

TEINSILE Yl 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

-ANNEAL.ED [67]

NNEALEC [17] ^

^ 40

CHARPY K — IZOD

i 0 50 100 150 200 250 300 TEMPERATURE, "K IMPACT ENERGY OF OXYGEN FREE HIGH CONDUCTIVITY COPPER 38 300 X 10^ 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

100 150 200 300

TEMPERATURE , STRENGTH OF BERYLLIUM COPPER s

39 70 COMPOSITIONS a TREATMENTS SAME AS GIVEN ON PAGE 38. 60

•5 50 c

40 .r^^-kH-Z GAGE LENGTH. ' [71] c 30 o a> Q. 20

10 A^HT[80] O AT [80] 0 50 100 150 200 250 300 TEMPERATURE, ELONGATION OF BERYLLIUM COPPER

120 COMPOSITIONS f35 TREATf\/IENTS S AME AS GIVEN ON PAGIE 38. 100 1 CH ARPY K CH ARPY V A[t 10] 80

x> 60

40 -a|h [8 0]

20 ^AAT[80] -O AT [80 T[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 ^

r /

k^O, I DC A y [80]

A Be-Co, [71]

TfENSILE Y 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. 50 100 150 200 250 300 TEMPERATURE STRENGTH OF BERYLLIUM BRONZES 41 60 COMPOJ5ITI0NS a TREAT^/lENTS S AME AS GIVEN ON PAGE 40. 50 \ -ABe-Co, Ah - 2"g )TH g 40 V [71] c c 30 A Re-Zn 4-HT fsol

S 20 ABe-Co,^HT[8 0) ^ / , ^ ^ o Be-Co, AT[80]

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF BERYLLIUM BRONZES

COMPOSITIONS £i TREAT MENTS S>AME AS GIVEN ON PAG E 40. CH^\RPY K — ch;\RPY V /-ABe-C<),iHT[7i ]

jHT[80]

ABe-Zn,:^ HT [80] ^ oBe-Co, AT [80]

50 100 150 200 250 300 TEMPERATURE, °K IMPACT ENERGY OF BERYLLIUM BRONZES —

60-39+1 7o Sn, ROLLED [90] (NAVAL BRASS)

80 67-33, ANNEALED (YELLOW BRASS) [15]

^70

70-30, ANNEALED, UJ (CARTRIDGE BRASS)[l7] cr 60

TENSILE 'yield point 40 the beam) except as noted NAVAL BRASS 1 "ROLLED

70-30, ANNEALED, I ^^J^'^'^^^ 30 ^\J (.l7o OFFSET YIELD ^1 STRENGTH)

25 t 50 100 150 200 250 300 TEMPERATURE, K STRENGTH OF SOME ALPHA BRASSES /

43 80

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

60 67-33, ANNEALEDr7 (YELLOW BRASS) 50 [15]

60-39+ I % Sn, cvi40 ROLLED [90] c (NAVAL BRASS)

c 30 o ^20Q)

10 67-33, 40 7o CD. [l5], (YELLOW BRASS) | 50 100 150 200 250 300 TEMPERATURE, ELONGATION OF ALPHA BRASSES

CHARPY V 67-33, ANNEALED [is] 100 IZOD CHARPY K

£ 60

^ 40

NAVAL BRASS, CD. HARD [49] 20

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 [l5] V) 'A" COLD DRAWN 12% /B',' ANNEALED [9] 80 if) (/) LU 70 \- 60

50 0.5 % OFFSET A. COLD DRAWN 12% YIELD STRENGTI 40

A. ANNEALED 20

10 TENSILE YIELD POINT BY DROP OF BEAM EXCEPT AS NOTED.

I \ I \ L 50 100 150 200 250 300 TEMPERATURE , «K STRENGTH OF LEADED BRASSES 45 60 FREE CUTTING MUNTZ METAL, ANNEALED [is] 50 + (ARCHITECTURAL "BRONZE" ANNEALED [9 40 COMPOSITION AS GIVEN ON PAGE 44.

CVJ 30 FREE CUTTING MUNTZ METAL, COLD DRAWN 12% [is] c 20 O u a> 10 Ql FREE CUTTING BRASS

ROLLED [90] I

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF LEADED BRASSES

60 GHARRY V GHARRY K 50

40 FREE CUTTING BRASS, ANNEALED[49] FREE CUTTING MUNTZ METAL, ANNEALED [iS] 30

FREE CUTTING MUNTZ METAL, 20 COLD DRAWN 12% [is] i 10 ^FREE CUTTING BRASS, COLD DRAWN, HALF HARD [49]

\ \ 50 100 150 200 250 300 TEMPERATURE, «K IMPACT ENERGY OF LEADED BRASSES 46

1 xlO 1 1 '

NOMINAL COMPOSITION : 60 Cu - 40 Zn

140

130

120

110

100 LD DRAW N 257o[i 5]

70 UJ ANNEALED-^ q: [15 ] ^ 60

40 ^^AN NEALED 30

10 TENSILE YIELD POIhJT BY DRC)P OF BEiIXM

, 1 0 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF MUNTZ METAL ,

47 60; 7 50 S 'ANNEAL iD Ll5j u •£ 40 CJ

•E 30 «^" , pni n nRAVAyM PRO/., r 1 / UULU UnAWPM c S<1> 20

Q. 10

- NOMINAL COMP OSITION : 60 Cu 40 Zn

1 0 50 100 150 200 250 300 TEMPERATURE ELONGATION OF MUNTZ METAL

CHARF V ANNEALE D[i5]

OLD DRAWN 25% [15] T 30

- NOMI NAL COM POSITION : 60 Cu 40 Zn :—i 50 100 150 200 250 300

TEMPERATURE , IMPACT ENERGY OF MUNTZ METAL ,

48 -" 1 r - 1 160 X 10U -T 1 COMPOSITIONS COMPLY WITH ASTNA DESIGN ATIONS BI50-54 AND BI48-52 150 1 1 1 WATEF< QUENCH ED FROM I650°F AND T EMPERED AT 1200 °F 140 1 \LLOY 9D CAST AN D HEAT TR EATED. [4"'] 130

120 v,/ALL0Y9D, CAST AND ^^..^ANNEALED [47]

I 10 t\LLOY 9 A CAST AND AN NEALED [a 7] 100 ALLOY 3 WROUGHT Q. AND ANNE:ALED [47] ^90 (n (/) 9D, HEAT TREATEC UJ 80

^^9D, ANNEALEC) 60 9A, ANNE i\LED\^

3, ANNEA 40

10 TENSILE

°/ YIELD STREN GTH (0.5 'o OFFSET)

1 50 100 150 200 250 300 TEMPERATURE, **K STRENGTH OF ALUMINUM BRONZES 49 60 /ALLOY 3, WROU (jH 1 AND / ANN lALED [471 50 COMPOSITIONS AS SHOWN ON PAGE 48. 40 /ALLOY 9A Zl.^ST , AND / ANNEALED 30 /\LLOY 9D CAST AN D ANNEALE D [47] — 20

\alloy 9D, CAST AND [47] HEAT T REATED * 50 100 150 200 250 300 TEMPERATURE, ^'K ELONGATION OF ALUMINUM BRONZES

80 ' CHAF?PY V 70 ALLOY 3, WROUGHl AND ANNEAL ED [47] 60 COMPOSITIONS AS SHOWN ON PAGE 48. 50

30 ALLOY 9 A, CAST A ND ANNEAL ED [47]^ 20 ALLOY S D, CAST /s ND ANNEA LED [47], 10

^ALLOY ?3D, CAST 1.\ND HEAT TREATED ^' [47] 50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF ALUMINUM BRONZES ,

150 X 100^ 1

COM -POSITION S COMPLY WITH /!\STM

DESIGNA TION B 1 50-54 F(DR WROU GHT AL BRONZE 140

130

120

/ )Y ALLC No. 1

/ AS f-0RGED[9(

I 10 ALLOY N

ROLLED i3t ANNEAL IDv 100

"Ih 90 Q.

(/T 80

70 |— /-N I~J /-* f— l~\ \LLOY No. 1 FORGED cn , 60

/ No.l a \LLOY , ROLLED ANNEAL 20 (YIELD S TRENGTH, 0.1% OFFS ET)

10 NSILE

YlfELD POINT , EXCEPT AS INDIC/^TED

50 100 150 200 250 300 TEMPERATURE, »K STRENGTH OF 8% ALUMINUM BRONZE 51 70 COMPOSITIONS AS SHOWN ON PAGE 50. 60

a> 50 ASTM ALLOY No.l o c AS FORGED [90] 40 CVJ ASTM A _LOY HoA ROLLED a ANNEAL ED\ .E 30 - [•7] c S 20

Q. 10

50 100 150 200 250 300 TEMPERATURE, °K ELONGATION OF 8% ALUMINUM BRONZE

CHARPY K COMPOSITIONS AS IZOD SHOWN ON PAGE 50

\ASTf^ ALLOY r^0.1 , ROLL ED, (HA RDNESS K52 DPH) [4 9]

^ASTM ALLOY No. ROLLE:D a ANNElALED [l?;

^ 50 iOO 150 200 250 300 TEMPERATURE, °K IMPACT ENERGY OF 8% ALUMINUM BRONZE 52 COMPOSITIONS CAST LEADED 140 Cu 5 7. 7 % 5 6. 5 % Mn .5 1.4 130 Sn .6 .9 Fe 1.2 I.I Pb — 1.3 120 Al 1.0 — Zn BAL. BAL.

I 10

100

. 1 FA DED, ROLL_ED AND NEALED [l 7] — 90 Q. en 80 en Qnil / >^S CAST [ 70 cn 60

\S CAST [90] 40 0^

30 H

20 zLEADED, F OLLED AN D ANNEAL ED [17]. (YIELD S TRENGTH AT 0.1% 0 FFSET)

10 TENSILE YIELD POINT EXCEPT A S INDICAT ED

_.. r.„, I 50 100 150 200 250 300 TEMPERATURE,*»K STRENGTH OF MANGANESE BRONZES j

53 50 COMPOSI TIONS AS GIVEN 0 N PAGE 52 /\S CAST [<90] \ V) 40 o £ 30 ^ ^ L EADED, R OLLED AN D X CVJ ANNEALED [17] — c 20

§ 10 V. a; Q.

50 100 150 200 250 300 TEMPERATURE, '^K ELONGATION OF MANGANESE BRONZES

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 30 * NOMINAL. COMPOSITIONS ONLY.

25 ROLLED A MD ANNEA LED [17]

20 ChMRPY K IZ OD

C, AS CAST ,A. AS CAST [49] [49] 5

^B, AS CAST [49] 50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF SOME MISCELLANEOUS BRONZES 54 180 X 10 COMPOSITIONS - 7o CAST WROUGHT 170 Cu 88,4 90.3

Sn 10.0 8.2 160 P — .06

Zn 1.6 150

[7 IJ .D DRAWN , HARD 140

130

120

Q.I 10

CO [SlOO QC \- iD 90

50 \a S CAST b 40

30 TE:nsile ELD 20 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 56 140 X 10^

130

120

MO ACT KA TVDC A M 1 YrL A, / COL.D DRAWN 42% [8 8] 100

90 ^ ASTM T T PE A , QUARTE R HARD^ 80 [71] \

Q. .70

(/) ^60

40 A C T K>l ' V DC A Ao 1 M T r L A , QUARTE R HARD 30

10 TE NSILE YIIELD 0 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 TYPE A, [67] COLD Dl=?AWN, HA 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 ^ TENSILE h— YIELD

50 100 150 200 250 300 TEMPERATURE, *K STRENGTH OF CUPRO-NICKELS ALL SPECIfVIENS RO LLED AND ANNEAL .ED IZOD

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 [17], ROLLED 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 150x10J - "

140 ^ AS FORGED :2.] 130

120 1

110

100

^90 HOT ROLLED

80 ANNEALEID'

[17,83, IC)0] 70

60 HIGH PUF{ITY(99.8 5Ni);^ ANNEALED [33] 50

30 /ANNEAL.ED [lOO] 20 „.„/

HK3H PURIT Y, ANNEAlE)"^"" 10 [3 3] — TENSILE YIELD

: I 50 100 150 200 250 300 TEMPERATURE, «K STRENGTH OF COMMERCIALLY PURE NICKEL 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 u

/COLD [)RAWN 5C)%[69,82 180

170

160

150

140

V /COL D DRAWN 10 % [71 ]

130

S.I20

ISiiO cr HOT =?OLLED[< >9] h- ^ 100

COLD DR/\WN 10% [71]

60 »

40 TENSILE YIELD 30 50 100 150 200 250 300 TEMPERATURE, *»K STRENGTH OF INCONEL 50 100 150 200 250 300 TEMPERATURE, K ELONGATION OF INCONEL

240 CHARPY V 220

HOT ROLLED [30] '200

180

CHARF>Y V ^ OLD DRA\/VN 50 % '69,82] ^ 40 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 0"

150 AS FORGEID [21,45] 140

.^^HO T ROLLE ) [83] 130

120

110

N^A SINEALED 100 [17,33,45 71] ^ (A ***

CO AS FO RGED^ UJ or 80 cn 70

60 > HOT FPOLLED- 50 — VN 40 NNEALEl 30

10 PENSILE HELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF MONEL 68 70 1

1 ^ANNEALED [l7.33.45] 60 HOT ROL _ED [83] w 50 a> O .E 40 \S FORGED [21,45]

.E 30 c

50 100 150 200 250 300 TEMPERATURE, <»K ELONGATION OF MONEL

220 ANNEALED-"^ 200 [30] \hot ROLLED U 0]

180 CHARPY V IZOD ^160 s- 140

120

/ ANN(EALED [i" 100

80 50 100 150 200 250 300 TEMPERATURE, *»K IMPACT ENERGY OF MONEL 69 10^

1 :OLD DRyWN 45*= [71] 210

I V— Da Y

180 J

170

F 160 E^

150

(/) CO Ul or h- EN Cc^ 130 D^ A^ 120

110 COLD DRAWN 45 % [71]

1001 ' REF [45] A - AMMCAICn B - ANNEALED AND AGE HARE)ENED C - HOT FINISHED - ' U MUI l-lNlbMtU ANU Abt MAKUtlMtU

E- COLD DRAWN 1 F - COLD DRAWN AND AGE HARDENED TENSILE YIELD 60\ 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

CH ARPY SP ECIMENS , NOTCH NOT GIN/EN

H MONEL , AS CAS T [45]

J. 30

Mor^EL,AS CAST [45]

^ 50 100 150 200 250 300 TEMPERATURE, *»K IMPACT ENERGY OF MISCELLANEOUS MONELS 71 200 X 10^

180 WATER QUENCHED FROM I832°F [2l] 160

0)140 Q. g>l20

100

80 COMPOSITION % 60 Ni 7 8.9 Cr 18.9 40 Mn 1.4 TENSILE C .3 YIELD 20 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF NICKEL -CHROMIUM RESISTANCE ALLOY

40 o c - 30 WATER QUENCHED FROM 1832 ° F [21 20

^ 10 Q.

50 100 150 200 250 300 TEMPERATURE, ^'K ELONGATION OF NICKEL-CHROMIUM RESISTANCE ALLOY

540232 O - 60 - 6 Titanium and Its Alloys

\ 1 \ ~1 \ 190x10^- INTERSTITIALSlC+OtHtN) =.30% (NORMAL) =^ INTERSTITIALS(C+0+H + N) = .l27o (LOW) O ALL SPECIMENS ANNEALED COMMERCIAL GRADE RS-70 (.032"SHEEtT

100 150 200 300 TEMPERATURE, **K STRENGTH OF UNALLOYED TITANIUM 73 45

40 /0[3I] 35

30 • [32] 1

CM 25

4- 20 c o0) ^ 15 0) / \ :iAL GRA DE RS-7 Q. COMMERC (.032" SH EET),

r'GAGE L.ENGTH 10

ALL SPECIMENS ANNEALE D • INTERSTITIALS (C+O + H+N) = .30 % O INTERSTITIALS (C + O+H+N) = .12 %

1 1 1 50 100 150 200 250 300 TEMPERATURE, ^'K ELONGATION OF UNALLOYED TITANIUM

20 coMr^ERCIALL Y PURE INTE RSTITIAL S NOT Gl VEN 15 0[3I]^

10 [8S

5 J . A M M C A 1 cn — CHARPY V • [32]^ — 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 75 30 7o IN 2 INCHES 3V-'ll Cr -SAi [7l](.032" SHEET)-\^

% IN I INCH 4 Al - 4 Mn [12] IN !/2 INCH 25 % 6 Al - 4 V [19]

20 c

\_ Q. 10

100 150 200 300 TEMPERATURE, °K ELONGATION OF TITANIUM ALLOYS

35 NON-STD. CHARPY V SPECIMENS

.788" WIDE X .197" THICK I 30 NOTCH WAS STD. SHAPE. BUT V2 STD. DEPTH I I

^20

^ 15

l3V-IICr- 3 Al," ANNEALED [19] Al -4 4 Mn , ANN EALED [|2] 0 50 100 150 200 250 300 TEMPERATURE, °K IMPACT ENERGY OF TITANIUM ALLOYS

77 280 X 10^-

270

260

TEMPERATURE, STRENGTH OF 5 Al -2.5Sn TITANIUM V

78 280 X !0^

270

260 \\ \\ 250 U- \\ 240 V- \ ^HEAT TREATED [l9], op, \ yy 1725 1 HOUR, WQ, v ANNEALED- \ > \ |[65] • \ 170 { 064 SHEE T) N— \ ^ \ \ V > 160 ^ X, \ \ ^ \ 150 >v \ s \ 140

130 '' TENSILE YIELD 120 1 50 100 150 200 250 300 TEMPERATURE, K STRENGTH OF 6 Al - 4V TITANIUM Magnesium Alloys

1 3 90x10

- 80 63, AS E)(TRUDED s^y^QA 1 64]

°- 60 "TA 54 [4 2]. ^ AS EXTR

(/) Ijj a: MIA[42 ]• \ h- ^ \ HARD R(3LLED-^ cn 50 N

^•^ 40 MIA/

OMMERCIA _LY PURE AS EXTRU DED [8l] 30

— TE ^JSILE YIE LD 20 0 50 100 150 200 250 300 TEMPERATURE, °K STRENGTH OF MAGNESIUM AND SOME MAGNESIUM ALLOYS 80 40

30 cn a>

OJ 4, AS EX"FRUDED ^2]\ J c 20

c <^ i 5 COMMER CIALLY P V. UREa

\MIA, h;\RD ROLL ED [42]

1 50 100 150 200 250 300 TEMPERATURE, *K ELONGATION OF MAGNESIUM AND SOME MAGNESIUM ALLOYS

CHARPY K

L 5 ^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

1 3

^AS EX TRUDED [ 25,64,81, 03] 60

[71] 50 HOT ROLl.ED ^LATE)[ 42]y

HC T ROLLED

AS EXlRUDED^

•«««• ^

MINIMI r Ai en /

TE hJSILE YIE LD

50 100 150 200 250 300 TEMPERATURE, "K STRENGTH OF AZ3I B MAGNESIUM ALLOY 82 40

^ 25 o c ANNEALf :D L7lJ

CVJ 20 c I^S EX TRUDED [2 5,81,103] ? '5 o V. CL 10

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

1 50 100 150 200 250 300 TEMPERATURE, ^'K ELONGATION OF AZ 31 B MAGNESIUM ALLOY

10 CHARPY V CHARPY K

ANNEALED [7l]

'\"aS extruded [49, 103]

50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF AZ3IB MAGNESIUM ALLOY 83 90x10" 84 90x10^

80 [i] 80-T5I , EXTRUDED AND AGED

70 1 /AZ. OU -T5[42] 1 AS EXTRU DED^.>Sn^ ^4^EXTF- a: 40 AS E xtruded/ cn /

1 30 A7 Qn.Tc;i//

10 TENSILE YIELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF AZ80 MAGNESIUM ALLOY

o 15 c AS E:XTRUDED AZ 80-- r5 [42], CVJ EXTRUC)ED AND AGED\ y c 10

-— en 5 o \- '^I 80-T5I [i],

1 V 3 \

HM 3IA- F, AS EXT RUDED [25, 71]

50 ^^^ HM 31 A AS EX1rRUDED//

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 A-F [25 / AS e:KTRUDED

JHM 21 A T8 [71].

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF THORIUM -MANGANESE MAGNESIUM ALLOYS

10 CHA RPY V

/HM 3 1 A-F [71 ],

/ AS E XTRUDEC) T 5

A-T8[7l] SPECIM EN STD. WIDTH / I

1 ^ 50 100 150 200 250 300

TEMPERATURE , "K IMPACT ENERGY OF THORIUM- MANGANESE MAGNESIUM ALLOYS 87

3 70x10

^HK 31 ) \ ANNEA LED [71]

/HK 31 iA-H24 [2 5]

^ 40 HK 31 A [71] UJ q: I- 30 HK3I /\-H24/^

^HK3 lA, ANNE ALED

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

TE MSILE YIE LD

50 100 150 200 250 300 TEMPERATURE, 'K STRENGTH OF THORIUM -ZIRCONIUM MAGNESIUM ALLOYS

540232 O - 60 - 7 88

^1 A AMfjCAi pn 1 HK Si/ 1 1 \l ll J

HK3IA-I-i24 [25]

0 50 100 150 200 250 300 TEMPERATURE , ELONGATION OF THORIUM-ZIRCONIUM MAGNESIUM ALLOYS

CHAfRPY V

T 5

\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^

50 CO [SS] if) -T5, EXTRUDED q: 40 I- (/) 30 TENSILE YIELD 20 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF Z K 60 A MAGNESIUM ALLOY

30 $ 1 o 1

20 1 J EXTRUDE D [65] c -4 10 I C o0) 0) 0 Q. 50 100 150 200 250 300 TEMPERATURE, °K ELONGATION OF ZK 60 A MAGNESIUM ALLOY

100 150 200 300 TEMPERATURE, IMPACT ENERGY OF ZK60A MAGNESIUM ALLOY 90 r- 3

5^E 10 X A-HII [7 ]

lOXA-HI 1

TEfsISILE YIE LD

0 , 50 100 150 200 250 300 TEMPERATURE, °K STRENGTH OF ZINC-RARE EARTH MAGNESIUM ALLOYS 91 40

(0 U 25 c

CVJ 20 - ^7 1 1 r 7' r F 10 ^ nilH L c 15 o / t 10

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF ZINC -RARE EARTH MAGNESIUM ALLOYS

10 CHAF?PY V

I 5 ^ZE lOXA HI0[7i]

50 100 150 200 250 300 TEMPERATURE, **K IMPACT ENERGY OF ZINC -RARE EARTH MAGNESIUM ALLOYS "1 60 X I V AT d~7 C 0 c ALL SPEC IMENS ANNEALEC) AT o7o r REF. [95] 50

^ 4 % Li 1 40

CO 6% Li 30 a \ Ck*. /

' (/) 20 % Li

10 T ENSILE lELD

0 50 100 150 200 250 300 TEMPERATURE, K STRENGTH OF LITHIUM - MAGNESIUM ALLOYS

-II % Li

^ 30 j-Q % Li

^4 % Li

1 AL.L SPECIMENS ANNEALED AT 675*'F REF. [95]

1 1 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

50 2(D2, ANNE/! LED [62, « 40

CM 30 c 20

o ^201 , COLD REDUC ED 40% ( HARD)

^ [IS)] Q. 10 "^^^

50 100 150 200 250 300 TEMPERATURE, ^'K ELONGATION OF AISI 200 SERIES STAINLESS STEELS 94

1 340x10"

320 •70I-M n c r\ 0\J\ l\J L ULU KULL L U /30I CO LD ROLLE ) 65 %, SHEET) [is / (SHE ET) [19] 300

280

260

240 301 AN NEALED- [2,4 _220 ]

(^200 — 301 {:OLD DRA WN, LU HAL F HARD [:^41] tt: 180

160

140

120

100

301 C OLD DRAW N, HALF I- ARD^ 80 TENSILE ^301 AN NEALED YIELD 60

40 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

^ANNEALED [2,4l] 100

^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

1 300x10 COLD DR/Q WN,{7I % R.A.)[63] 280 /COLD DR>\WN .HALF HA RD [59,60 260

240

/COLD DRAWN (49 *Vr^ R A.) [63] 220 V

200

180 ANNE/i LED[2,I8 .21,41 ^ 59,6 0,63] ^ c/Tieo if)

140

120 s V ^ANNEALE D [2,18,2 ,41,63] 100 N \ \ 80

20 TENSILE — YIELD

50 100 150 200 250 300 TEMPERATURE, <»K STRENGTH OF AISI 302 STAINLESS STEEL ,

\NNEALED [2, 18,21 59,60.6>3]

11 \> 1 r IKl O/ C V. l^Q .A.)\^ [63]

^COLD DR/ HALF H/^RD [60]

C OLD DRAV/N,(7I%R [63]

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

1 280x10

260

240

220

200

\NNEALED [41] 180 v> Q. ^160 ^ 10% CO LD DRAWh [71]

UJ 140 q:

(/) 120

100

80 \ /I0% CO LD DRAWr l[7l] 60

40 MSB ^ ANNE ALED [41] 20 TENSILE YIELD

1 50 100 150 200 250 300 TEMPERATURE ,*»K STRENGTH OF AISI 303 STAINLESS STEEL /(.28% S),ANNEA LED [41]

120

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

/COL ) DRAWN, TO UXS. 2 10,000 psi) 280 l[89]

260

240

220

A 1 CO 7 1 J EALED [2, 1, ,DO, l,96J ^ 200

w 180 Q. \j\Jl-U u

(TO U.T. 3. 210,000 psi) [2160 (T I- (/) 140

120

100

80 ^ANNE/ ^LED 60

** 40

20 TENSILE -YIELD

1 50 100 150 200 250 300 TEMPERATURE, *>K STRENGTH OF AISI 304 STAINLESS STEEL 01 70

60 ANNEALEC [2,41,62,7 0) 50 o c 40 c :OLD DRAV/N,{TO U.T S. 210,000 psi)[89] *. 30 1 c DRAWN,(TO U.T.S. 161 ,000 psi) O [59]

10 COLD DRAWN,/ (TO UTS. 192,000^ psi) [59]

50 100 150 200 250 300

TEMPERATURE , K ELONGATION OF AISI 304 STAINLESS STEEL

140 — CHARPY K ~IZ( ^ ANN EALED [2 41,96] 120

100 y ANN EALED [6 D, 62,84] ^ 80

COLD DRA\^N,(TO U.T.; 3.210,000 F)si)[89] 40

20 50 100 150 200 250 300 TEMPERATURE ,»K IMPACT ENERGY OF AISI 304 STAINLESS STEEL U

102 280x10^

240

n A \kt k 1 ["Til ^ / 15 To COLD Dl xAWN L' -200 Q.

120

.I5%CC)LD DRAWr 1 80

40 TENSILE YIELD

1 50 100 150 200 250 300 TEMPERATURE, *»K STRENGTH OF AISI 308 STAINLESS STEEL

^ 60

\l5% COL D DRAWN [71]

50 100 150 200 250 300 TEMPERATURE, °K ELONGATION OF AISI 308 STAINLESS STEEL 103

1 280x10*

240

220

200

180 /COLD DRAWN,( 7 0 U.T.S. 95, 000 psi)

[71] 160 ANN tALt if) [71] liJ 140 in 120

100 V CULU U

80 N

a 60 -^ANNEAL ED "--^ 40

20 TE NSILE — Yl£:ld 50 100 150 200 250 300 TEMPERATURE,*»K STRENGTH OF AISI 310 STAINLESS STEEL

540232 O -60 -8 104

ANNEALED [7l], \ INCH GAGE LENGTH)

COLD DRAWN.dO UTS. 95,000 psi)[7l], (I '4 INCH GAGE LENGTHt-

COLD ROLLED

COLD ROLLED,( TO UTS. 159,000 psi) [59] 50 100 150 200 250 TEMPERATURE, ELONGATION OF AISI 310 STAINLESS STEEL

ANNEALED [59]

50 100 150 200 250 300 TEMPERATURE, ^'K IMPACT ENERGY OF AISI 310 STAINLESS STEEL

106

rANNEALED [2,^H,7l]

\COLD DlRAWN 25°/'o[7l],

( 1 INCH GAGE LEN GTH)

50 100 150 200 250 300 TEMPERATURE , «K ELONGATION OF AISI 316 STAINLESS STEEL

^AfJNEALED [2,41]

^ANNEAL ED [59]

— CHARPY K IZOD

1 50 100 150 200 250 300 TEMPERATURE, "K IMPACT ENERGY OF AISI 316 STAINLESS STEEL 107

280x10^

260-)

)

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

200

180

if) CLI60

CO (2l40 tr I- <^I20

100

'ANNEALE D [41.63, 71,98] 80 v

60 ' * , 40

20 YIELD

1 50 100 150 200 250 300 TEMPERATURE STRENGTH OF AISI 321 STAINLESS STEEL 50 100 150 200 250 300 TEMPERATURE, °K

ELONGATION OF A I SI 321 STAINLESS STEEL

ANNE/S LED[4i] •

CH ARPY V DD

50 100 150 200 250 300 TEMPERATURE, "K IMPACT ENERGY OF AISI 321 STAINLESS STEEL (

109

1 300x100^

280

260

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

200 V—

180 V) A MMP a. [2.41 ,60,63,71] A

140

120

y COLD DR AWN 10 %» [711 N

40 ANNEicuIed'/^"" [2,41. S0,63.7l]

20 ——TENSILE YIELD 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF AISI 347 STAINLESS STEEL 110

80 \ ] r- I

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF AISI 347 STAINLESS STEEL

—T ^ANNEALE:D [2.41]

\annea LED [79]

— CH ARPY K ^IZ(

0 50 100 150 200 250 300 TEMPERATURE, "K IMPACT ENERGY OF AISI 347 STAINLESS STEEL 10

200 xANN EALED, \/ (S/siME AS PA GE 96) 180

160 AIR COOLED FROM 1920 ^F,^ (SENSITIZED) [73], 140 (BRITISH SPEC. En 58a)

Q. 120 CO UJ a: 100

80 NEALED

60 SENSITI ZED-^^ [73] 40 TENSILE ---YIELD 20 L 50 100 150 200 250 300 TEMPERATURE, EFFECT OF SENSITIZATION ON STRENGTH OF AISI 302 STAINLESS

80 (0 AIR COOLED FROM 1920 °F (SENSITIZED) [73] , o 60 .(BRITISH SPEC. En 58a) c 40 ANNEALED,

(SAME AS PAGE 96 ) 20

50 100 150 200 250 300 TEMPERATURE, K EFFECT OF SENSITIZATION ON ELONGATION OF AISI 302 STAINLESS 12

CH/\RPY K —— cc O/ AO Oil OIK k 1 cc)LD WORKED, THEN SENSITIZED

REF [84]

100

80 /

^ 70 V s- / -0% S 60 / LU 20%^

O 40

- 30 ^20% 20 / 10

50 100 150 200 250 300 TEMPERATURE ,*'K EFFECT OF SENSITIZATION ON COLD WORKED AISI 302 STAINLESS 113

\ 1 CHARPY K

— CO LD WORK ED ONLY, % AS $jHOWN. ^ COLU WUKK ED, THEN SENSITI ZED 100 HRS AT 1020 ^'F REF [84]

yl 0 %

^10% i 0%

i / / /

> /

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 47

60 318. 55

50 ^ 347\ ^ 45

^^40 tr UJ 35

LLi

3 S 25

• c:harpy h 5 AM — 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 16 50 CHARPY K REF. [50] 1250 °F-30MIN.^>^^ 40

A NNEALED> 30

I035°F- ^OMIN. 20 l035°F-4£

10 I250°F-48HR.

50 100 150 200 250 300 TEMPERATURE, **K IMPACT ENERGY OF SENSITIZED CAST ACI-CF-8T STAINLESS STEEL

90 CHARf K RE:F [50] 80 1035 ''F - 30 Mlh

70 A^JNEALED^ 60

40 1035 <>F - 3 MIN.\ 1250 °F- 3 MIN.\

30 i IO35OF- ^

- 1250 OF ;50 MIN.^ 20

1250 °F- 48 HR\^ 10 5 50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF SENSITIZED CAST ACI -CF-20 STAINLESS STEEL 117

I 200x1010"

180)

) ^ .ANfSIEALED [5 1]

)

cl I

if) en UJ ) or /ANNEAL ED 80) ^

60I

40)

20 TENSILE YIELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF CASTACI-CF-8 STAINLESS STEEL

8 60

\annealED [51] 20

50 100 150 200 250 300 TEMPERATURE, "K ELONGATION OF CAST AC! -CF 8 STAINLESS STEEL ^

118 80 rWARPV' K

RE F. [50] 70

ANNEALE 50

40 l035°F-3 OMIN.—

I035°F- 2\ MIN.^ 30

1 250°F-30 20

I250°F - 3 MIN.-^ 10 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 CHARPY K REF [50] 1250 OF- 30 MIN.~ 40

1035 OF - 30 MIN.^y^^^^^ 30

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

:XTRA HA ^D, A(R C 51) 320 [19]

3CX)

/j-SOAKlED A ^

280 'J

260

240 N 220 V

> a. 200

3TD. h EAT TRE/\T CYCLE

{ TEMPERED AT 850 ) c/) 180 ^" LU [ 65] (0.06^ SHEET) QC

CO 160

140

120

BEFORE FINAL TEMPERING 100 ^ COLD ROLLED A SOAKED 7'/2 MR AT /Y^K, WARMED TO ROOM TEMPERATURE, THEN HELD AT TEST TEMP 80 ERATURE HR BEFORE TESTING.

60 TENSILE

. YIELD 40 50 100 150 200 250 300 TEMPERATURE, ^'K STRENGTH OF HARDENABLE AM- 350 STAINLESS STEEL 121

TEMPERATURE, °K ELONGATION OF HARDENABLE AM 350 STAINLESS STEEL

CHA RPY V

STD. HEAl TREAT CYCLEtx (TEMPER ED AT 8e>0°F) \

[3 ]

• 20

50 100 150 2 00 250 300 TEMPERATURE, "K IMPACT ENERGY OF HARDENABLE AM 350 STAINLESS STEEL 122

1 280x10*

260

240 /QUENCHED AND T EMPERED TO RC 39 ^ [41] 220

200 C 39

180

^160 /QUENCHE:D AND ^•^^^v^EM? ERED TO RC 23^^' ^[41] [2 140 cr ^'^^'^-^^.^NNEAL-ED [2]

^ 120

100 ANNEALED

20 TENSILE YIELD

0 ' 50 100 150 200 250 300 o TEMPERATURE, ^'K STRENGTH OF AISI 410 STAINLESS STEEL 123

50 100 150 200 250 300 TEMPERATURE, *»K ELONGATION OF AISI 410 STAINLESS STEEL

100 IZ(DD CHARPY K 80

60 [7 9] 410, OIL QUENCHED AND TEM PERED AT II50°F —

1 1 431, OIL QUENCHED AND TEM pered at IIOO°F\.^ 40 - ^ [79] / 4I0,ANNE ALED[2] 20 r 50 100 150 200 250 300 TEMPERATURE, ^'K IMPACT ENERGY OF AISI 400 SERIES STAINLESS STEEL 124

140x10r'

130

120

I 10

100 /ANN EALED [2 .41] 90 \V ANrJEALED--^ CO ^ 70 a: N ^ 60 \ \ \ S 50 V

10 TENSILE YIELD

1 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF AISI 430 STAINLESS STEEL 125 40

50 100 150 200 250 300 TEMPERATURE, »K ELONGATION OF AISI 430 STAINLESS STEEL n )

126 280x10J

260 If r \ JDITION H -875 [5] 240 AMJ5-5644 (r7-J PH NDITION T H-1050 [65" _220 ^ -5644,-- Q. AMS (17- 7PH) .200 cn C/) LU S 180 AN1S-5643E (17 -4 PH) 160

140

120 TENSILE YIELD

100 1 0 50 100 150 200 250 300 TEMPERATURE, '^K STRENGTH OF PRECIPITATION HARDENING STAINLESS STEELS

15 AMS 5643 B,(I7-4PH CONDITION H-875 10 [5] c AMS-5644,(I7-7PH)/ CONDITION TH-1050 c Q) 5 65] O \_ Q. 50 100 150 200 250 300 TEMPERATURE, ^'K ELONGATION OF PRECIPITATION HARDENING STAINLESS STEELS 127

140 K^n Mnr T V IZ( 130

120

110 VMS 5643 8,(17-4 PH CONDITION H-II50 100 J 'V 90

80 70 — 60 FV52iOB[72], OVERAGED TO

UTS. 1 46,000 ps i 50

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

20 ! AMS5644,(17-7PH)- CONDITION TH-II50 10 [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 10 YIELD

1 50 100 150 200 250 300 TEMPERATURE, <>K STRENGTH OF SOME AISI -SAE PLAIN CARBON STEELS 29

\ 60 T 1 CONDITION "AS RECEIVED" (PROBABLY COLD ROLLED) 50

1010 [3 7l c 30

0*o 20 K)40 [37] Q. 10

50 100 150 200 250 300 TEMPERATURE, *»K ELONGATION OF SOME AISI-SAE PLAIN CARBON STEELS

60 NC)RMALIZE D

i:70D 50 102

[2( 40

T 30

20 i' 1030 [28] 10 1050 [28]

50 100 150 200 250 300 TEMPERATURE, K IMPACT ENERGY OF AISI-SAE PLAIN CARBON STEELS 30 200 X 10^- COMMERCIAL HEATS WERE TESTED. | COMPOSITIONS WERE NOT GIVEN, BUT 190 "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 ALLOY STEEL C c - .21 % Mn - .91 Si - .48 P - .020 s - .032 - Ni . 3 1 Cr - .34 - Mo . 1 1

A B 70 C - 25% .19 7o Mn - .45 .43 Si - .054 .036 60 - P .005 .01 1 s - .025 .028 (PROBABLY NORMALIZED) 50 50 100 150 200 250 300 TEMPERATURE, ^'K TENSILE STRENGTH OF SHIP PLATE ft LOW ALLOY CONSTRUCTIONAL STEEL

380 X 10^0^

360

340

300 M ( rRICENT) HEAT TRE ATED [65l )Q a DOU 3LE TEMP ERED) 320

300 N

280

260 Q. "hy-tu F,"hEAT 7•REATEO/ \ ^240 [89] LJ cr h- 220

200 ^ T

180

160

140

120 TENSILE YIELD 100 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

Ch-MRPY K CH ARPY V

- "T 1 HEAT TREATED

- [11]

"HY - TUF "[89]."^ HEAT TR EATEDx

^ 300 M(TRICENT) [65] HEAT TREATED 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

NOMir^AL COMfPOSITION 9% Ni - .11 7o C

CHARPY K / 4 CHARPY V / 1 / HE/!\T TREAT / LOI\ GITUDINAL [77]^ 70 f / / / 1 HEAT rREAT'^2 \ / [86] 60 / \ / / L

IFAT / TRE !\T ^ 1 \ 1 [8,45,77, 86,I03]\

30 <^ \heat TREAT "^1, TRAN SVERSE [77]

/ "^NHEAT TREAT "^1, / TRANSVERSE [77]

i 1 ' HEAT TRE:atment ^1 -DOUBL E NORMALIZED FROM 1650 AND I450°F, THE N STRESS RELIEVED AT 1050 ^F. 1 HEAT'TREATMENT# 2 - QUEN CHED a TEMPERED AT 1050 ^F.

10 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 N V

1320, 80C RC-33 [f35] \^

/^I320, 300*»F, \ RC-44^[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-/o Ni - .I0»>'oC,-\ N(DRMALIZE[) \

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 LMrtKt u

1 HR. AS SHOV\

CH ARPY V ARPY K

T 100 0°Fv 2315, W Q , RC 2 7 [66]

^2315, RB 90 [6( ^ NOR^/lALIZED — A / 340, OQ l200°F,-~- ?C 22 [66] 1 1 1 —A 1 ^2330, OQ [89], T925° F, RC32 / / r J 2320,00, T400°F, RC42 u li35] ooaT/tOO°F^^^ 2330^ 0, y ^' to(^C48 [85] y 2340^ / / ^ 2330 [<37], / NORMALIZ ED^/ / / / 0Q,T400°F, , RC 54 [85]

50 100 150 200 250 300 TEMPERATURE, *K IMPACT ENERGY OF AISI -SAE 2300 SERIES CONSTRUCTIONAL STEELS K

139

1 tMrtntl J

1 HR.AS SHOWN _CHARPY' V

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 , " IMPACT ENERGY OF AISI - SAE 4000 SERIES CONSTRUCTIONAL STEELS 140

10' \ X \ 380 I OQ a TEMPERED 4 HRS AT 450 ° F

100 150 200 300 TEMPERATURE, STRENGTH OF AISI-SAE 4340 ALLOY CONSTRUCTIONAL STEEL

0, 25 OQ a TEMPERED . . o AT 1200 °F TO RC 34 [89] .E 20 OQ a TEMPERED 4 HRS AT 450 ° F CVJ a TEMPERING REPEATED. [^5] c 15

£ 10 o \_

100 150 200 300 TEMPERATURE, ELONGATION OF AISI- SAE 4340 ALLOY CONSTRUCTIONAL STEEL 141 OQ a TEMPERED 120

1 HR. AS SHOWN CHARPY V 100 412 0, 1200 °F

80 O rr 4130, 900 ''1 RC 39 [66 60

40 41 20, 1000 ''F, R C 31 [85] 20 — 4140, 300 "F, RC 53 [85] 50 100 150 200 250 300 TEMPERATURE, °K IMPACT ENERGY OF AISI - SAE 4100 SERIES CONSTRUCTIONAL STEELS 60 OQ a TEMPERED

I HR. AS SHOWN 50 CHARPY V 4320, 1000 ° F CHARPY K RC 33 [85] 40

30 4340, 1200 ^'F,^ 4320, 3000F, RC 34 [89] RC 43 [85] 20 ^4340, 300 °F RC 54 [85] 10

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 \j

1 HR. AS SHOWN

1 CHARP Y V

0°F,\ / A 620, 80C '\ RC 19 [e15] \ RC 34 [Qt

4620, 3C 0 °F,\ RC 42 [e

^4640, 3C)0°F [85], RC 54 50 100 150 200 250 300 TEMPERATURE, *»K IMPACT ENERGY OF AISI -SAE 4600 SERIES CONSTRUCTIONAL STEELS

OQ a TEMPERED 48!5, IIOO°F, I HR. AS SHOWN RC 20 [40] V- CHARPY V

. 50 100 150 200 250 300 TEMPERATURE, »K IMPACT ENERGY OF AISI - SAE 48CX) SERIES CONSTRUCTIONAL STEELS 143

OQ a TEMPERtiD

1 HR AT TEMP'S;. SHOWN

\ CHARPY V

3120, I20(J r RC 22 [8 5]

/ 10, 800 °f / ^ C 38 [85]

-5120, 40C)°F, RC 45 [ 35] 50 100 150 200 250 300 TEMPERATURE ,°K IMPACT ENERGY OF AISI -SAE 5000 SERIES CONSTRUCTIONAL STEELS

N - NOF?MALIZED IZOD

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 144 220 X 10^-

200 \ TEMPER ED

'^^ 850 «>F TC) RC 34 [a 9, 103] / 180

<5 160 Q.

CO ^ 140 UJ NORMA LIZED q: [l03 ] CO 120

80 TENSILE YIELD 60 1 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF AISI-SAE 8630 ALLOY CONSTRUCTIONAL STEEL

-NORMALI ZED [103 ] 20

15 cvj -OQ a TE MPERED c AT 850 op TO RC 30 [89]

OQ> k 5

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

OQ a TEMPEREC) 1 HR. AS SHOWN CHARPY K 25 8750, IOC RC 42 [66>] \ 20

50 100 150 200 250 300 TEMPERATURE, «K IMPACT ENERGY OF AISI-SAE 8700 SERIES CONSTRUCTIONAL STEELS t

146

k c OLJ r\\ki UU a 1 LMrLK J 1 HK. A N CHARPY K

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

50 100 150 200 250 300 TEMPERATURE, »K IMPACT ENERGY OF AISI-SAE 9200 SERIES CONSTRUCTIONAL STEEL

QUENCHiED a TE:mpered 1 HR.AS SHOWN CHARPY K

9420, WQ, 1000 RC 2 7 [66] \^

\944 0, OQ, 90C RC 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)

148 260 X 10

240

220

200

— 180 CL

CO LlI 140 CO

120

100

1. I800°F,WQ a AGED 16 HRS. AT 1325 °F, AC 80 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 60 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF SUPERALLOYS 149 80

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. 0 50 100 150 200 250 300 TEMPERATURE, °K IMPACT ENERGY OF SOME SUPERALLOYS 150 J 300 X 10^ ' HEAT TREATMENTS

1. HOT ROLLED a STRESS RELIEVED AT 2200 °F 280 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 260

240

220

200

180

C/) liJ 140 cr ^120

100

100 150 200 300 TEMPERATURE, STRENGTH OF COBALT BASE SUPERALLOYS 151 70 HEA1r TREAT^^ENTS S/\ME AS GIVEEN ON P/3^GE 150.

60 1 "hayn ES" ALLOY No. 25 (L' 605) HT. TR.*I [71;

40 OJ c

§ 30 81 a> S- o [3], Q. HT.T R.*3 \

- 36 1 HI TR *3 >^

*BfRITISH [73]^—^ h TTR.*2

50 100 150 200 250 300 TEMPERATURE, °K ELONGATION OF COBALT BASE SUPERALLOYS

540232 O - 60 - 11 152

0^ RC)LLED AN D ANNEA LED

180

170 y'HAST ELLOY"B [66]

160

/HASTE LLOY"C [ 66] 150

140 "HA STELLOV

h reel ]

C;>I20

100

90 \ ' MSTELL 3Y"C 80 \ X' V HASTELL B s 70 — ^-v *^ HASTEL .oy"a/ 60 "^^ ~ —

50 —— TEINSILE ELD 40 50 100 150 200 250 300 TEMPERATURE, »K STRENGTH OF SOME PROPRIETARY NICKEL- BASE SUPERALLOYS 153

70 -

"HASTE LLOY"B [ 66] \ 60 g 50 / C \STELLO'r"A [66]

CVJ 40 c

c 30 / o ^STELLO^ '"C [66] S 20

F OLLED A ND ANNEALED

50 100 150 200 250 300 TEMPERATURE, <»K ELONGATION OF SOME PROPRIETARY NICKEL-BASE SUPERALLOYS

^"HASTELL.OY"X [67 ] CHARPY V \ 60 1 •^"haste lloy'c [ 67]^ CHAR PY V 50 ^^^^^\STELLO r"B[67] - CHARPY U 40

\"HAS TELLOY" A [66] 30 ROLl.ED AND /\NNEALED

(TYP E NOTCH rJOT GIVEN ) ^ op HOT Fpolled AN D STRESS RELIEVEC) AT 2200 20 50 100 150 200 250 300 TEMPERATURE, *»K IMPACT ENERGY OF SOME PROPRIETARY NICKEL-BASE SUPERALLOYS Brazing and Soldering Metals

154 30x10^

100 150 200 250 300 TEMPERATURE, TENSILE STRENGTH OF TIN - LEAD SOLDERS

120 %lELONGATION IN 2 INCHES % DEDUCTION OF AREA 100 ALLOYS AS CAST. 80 25 Sn - 75 Pb[58 c 50 S n -50Pb[46]^ ^^^-^ p 60 — 5 Sn-9 5 Pb[46]^^ a. 40

20 ^50Sn-5 OPbLse] 50 Sn -4C)Pb [58]

' r 50 100 150 200 250 300 TEMPERATURE, DUCTILITY OF TIN - LEAD SOLDERS 155 30 1 1 CHARPY V ALLOYS AS CAST 25 y5Sn -95Pb[4€ 20 lOSn-S 0Pb[^6]v

15 \

10 ^15 Sn-85 Pb [46]

5 50Sn-50Pb[46]N

50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF TIN-LEAD SOLDERS

30 CHARPY V ALLOYS AS CAST 25 .2.5 Ag-97.5 Pb [46]

' 50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF SILVER -LEAD SOLDERS 156 12 X 10

10 ^1.6 A(3 10 on cB3.4 Pb, AS CAST [46] 8 1

50 100 150 200 250 300 TEMPERATURE, *K TENSILE STRENGTH OF SILVER- LEAD SOLDERS

50 5Ag-97.5 Pb[46], o c 40 f\S CAST

c 30

§ 20 v. 1.6 Ag-15 SIn -83.4 P 5 [46], Q. AS CAS>T 10

50 100 150 200 250 300 TEMPERATURE, ''K 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 yJ\J U U -50 Zn [lOO] 930° F ANNEALED 90

0) ^ 80

(/) IJJ 70

- ^45Ag -30 Cu i^5 Zn 60 [58] AS CAST

' 1 1 ^70Ag-20Cu-IOZn [58] 50 AS C AST 40 \ 30 s—

0 Cu - 50 Zn 20

10 TENSILE YIELD

1 50 100 150 200 250 300

TEMPERATURE , **K STRENGTH OF BRAZING ALLOYS —

159

1 1 60 1 ' 1 %EL ONGATION %RE:duction OF ARE/! 50

50 Cu-50Zr1 [100]. 930 **F ANN EALED \ 40

45 Ag -30Cu -2 5 Zn [58] 30 AS CAST —

\70Ag -20CU-I OZn [58], 10 AS CAST

50 100 150 200 250 300 TEMPERATURE, DUCTILITY OF BRAZING ALLOYS Miscellaneous Alloys and Pure Metals

160

TENSILE STRENGTH 7o ELONGATION, ANNEAL METAL p s i .79"GAGE LTH. TEMR,**R 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 1

161 160

140

^>|cHOT ROLLED [ 120 \— \ \ ^ Q.IOO \V (/> 80 UJ A- q: en 60 COM p. % 40 .C - 1.40 - Mn 12. 1 Si - .12 20 P - .060 TENSILE S - .012 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-u

.-180 -AM 3 5624, Q. AN NEALED [ 20] CO 160

140

120 T ENSILE 100 50 100 150 200 250 300 TEMPERATURE, STRENGTH OF HIGH EXPANSION STEEL

80 A^/IS 5624, ANN EALED [2( 60

^ 40 c

0) 20 Q. 50 100 150 200 250 300 TEMPERATURE,^K ELONGATION OF HIGH EXPANSION STEEL

120 CHARP^ K

100 AMS 5 624.-^ ^ ANNEALE:d [20] 80

40 50 100 150 200 250 300 TEMPERATURE, ^'K IMPACT ENERGY OF HIGH EXPANSION STEEL 163

specimens: 1.2" DIA.STD. CAST IRON 100 ARBITRAT!0^J bar; as; CAST, UNNOTCHED. IZOD TY PE TEST. 90 S AUSTEN TICx [99] 80

70 (D AUSTE NITIC [99]

I 50

40 ^ii-Mo AC! :ULAR [99

PEARLITIC GRAY IR(DN [99]

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

SPECIMIENS ANNEALED,!' SQUARE c 2^"SPAN UNNOTCHED. CHARPY 1^YPE TES T.

R EF. [35]

IRON

IRON*

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

/ /\|F?0N*4

50 100 150 200 250 300 compositions: TEMPERATURE, '^K specimen %C %Si %S %Ni %Mg

IRON I 3.63 .93 .35 .010 .024 .60 .042

IRON 2 3.52 2.03 .37 .013 .028 .7 1 .055 IRON 3 3.33 2.73 .40 .013 .028 .71 .057 IRON 4 3.29 2.09 .38 .014 .162 .72 .049 IMPACT ENERGY OF SOME FERRITIC NODULAR CAST IRONS 165 150 X 10* ^ 1 NOMINA! composition:

140 C - .025 Mn- .030 130 Si - .003 P - .003 S - .025 120

110 "COLD DF?AWN 24 % [34] 100 V- \ N 90 ANNLALE V [34] \\\ . \\\

(/> (/) 70 UJ ^ T ROLLED q: \ \ [17,21.34,37] CO 60

40 V^^HOT ROLLED 30

10 TF YIELD POINT YIELD STRENGTH, (O.J1 Vo OFFSET)

1 1 50 100 150 200 250 300 TEMPERATURE, *K STRENGTH OF INGOT IRON 1 ZOD

-J-

1 HO T ROLLEC r n

0 50 100 150 200 250 300 TEMPERATURE, IMPACT ENERGY OF INGOT IRON ,

167 15 X 10^

S. 10 J, 76 ],AS CAST of UJ 5 or

50 100 150 200 250 300 TEMPERATURE, TENSILE STRENGTH OF COMMERCIALLY PURE LEAD

/ [58, 76 ],AS CAST o .E 30

CVJ 20 c

50 100 150 200 250 300 TEMPERATURE, ELONGATION OF COMMERCIALLY PURE LEAD

50r- 40- CH ARPY K £ so- 20- /76] il 10-

50 100 150 200 250 300 TEMPERATURE IMPACT ENERGY OF COMMERCIALLY PURE LEAD

540232 O - 60 - 12 1 C

168 "' 240x10^ — 1

IDI T V 1 IC V DnCMI IK nlon r Unl 1 T Ur

200

/-TEN*>iLE a Yl ELD 180

160 B Q. ^^"^ -140 ' in B if) B ^ > V. A LlI q: 120 H E 100

80 E

20 TENSILE YIELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF A MOLYBDENUM- URANIUM 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% MOLYBDENUM |REF. [104] 1 1

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 MOLYBDEN UM

CHARPY V . REF. [i04]

^ B

50 100 150 200 250 300 TEMPERATURE, "K IMPACT ENERGY OF A MOLYBDENUM URANIUM ALLOY 1 —

— 10 —

280 AMMPAI CP

FROM 147 2*^ [21]

260 1 A| ^^^^ / HL_l_U1 HYT DR MIMAMMFAiIN C_Mi_CiJrn J FROM 147 2°F [21] 240

220 a 200 k ALLOY B 180 Ql \ 160 S \ ALLOY D, in CO AS FORGEl IaJ ALLOY C, ^\ 140 ROM ^[21] 922° F [2 CO 120 \ 100 LLOY D- 80 ^ i;^—N Y

COMPOSITIONS 60 t ALLOY Ni C Mn Si

A 24.5 .16 1.00 .30 40 B 3L4 .70 .82 —

C 35.8 .16 .86 .08 20 D 57.5 .34 1.31 .14 TENS ILE

E. 58.8 .27 1.64 28 YIELC)

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF NICKEL- IRON ALLOYS U 50 100 150 200 250 300 TEMPERATURE ELONGATION OF NICKEL IRON ALLOYS

80 CHAR PY K

r E , FOF GEO a / NORMALIZED F ROM 1700 •F [74] 60

I 40 49.4 Ni [l€ A NNEALED

30 1

AL -OY E, AS5 FORGED 20 35. 3Ni [i6]r AN NEALED

10 AniniCAL.C.1 ^25.9 NIi[i6], ANNEA LED

50 100 150 200 250 300 TEMPERATURE IMPACT ENERGY OF NICKEL-IRON ALLOYS 172 160x10^0"

140

I F ANin Y LQ MINU 1 < .010",SHEET, 120 VVACU UM ANNE:aled \ \ [78] > g^lOO N \- \ \

[2 80 tr ANN EALED[iC h- ^ 60

20 TENSILE YIELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF COMMERCIALLY PURE TANTALUM <

140 X 10^

130 COLD WORKED 50% [38] 120

110

100 ANNEALED 90 AT 1472 **F [38]

^80

CO C/) 70 a: ^ 60

50 HIGH PURITY VACUUM ARC REMELTED [lOO], 40| —ANNEALED I400«F IN ARGON

10 TENSILE YIELD

50 100 150 200 250 300 TEMPERATURE, STRENGTH OF COMMERCIALLY PURE ZIRCONIUM 174 50

V HIbH PUKI 1 Y VACUUM ARC REfvIELTED, ANNEALED 1400 IN AR(SON 40

CM c

c 20 Q>O \_ Q. ^^ANN EALED 14 72 **F [38

^COLD W ORKED 5 0 7o [38]

50 100 150 200 250 300 TEMPERATURE, ^'K ELONGATION OF COMMERCIALLY PURE ZIRCONIUM

30 1 CHARPY' V /HOT RO LLED AT 1200 *»F [38] 20

50 100 150 200 250 300 TEMPERATURE, »K IMPACT ENERGY OF COMMERCIALLY PURE ZIRCONIUM Nonmetallic Materials

175

1. POLYETHYLENETEREPHTHALATE ("MYLAR") 40xlC? 2. POLYTETRAFLUOROETHYLENE ("TEFLON") 3. POLYTRIFLUOROMONOCHLOROETHYLENE ("KEL-F")

4. POLYVINYLCHLORIDE ,

Q. 20

en ^ 15

0 100 150 200 300 TEMPERATURE, ^'K TENSILE STRENGTH OF PLASTICS

1 1 1 (VALUES ARE REPORTED

FROM 20 TO 120 7o ) \ o 20 ©[27 CVJ 15 NOTE: REF [27] REPORTS "NIL" FOR PLASTICS (2) & ® AT 198 a BELOW. ^ 10 c OQ> 0) 5 Q.

50 100 150 200 250 300

TEMPERATURE , ELONGATION OF PLASTICS ' ' 15x10^ 1 — AT VAF(lOUS RAT ES OF LOAOING

AS SHC)WN, psi p er sec, REF [61] to Q. A- 80 D -10 (/)

UJ /-lO a: h- (/)

I -1 < UJ crm 50 100 150 200 250 300 TEMPERATURE STRENGTH OF ABRADED BOROSILICATE OPTICAL GLASS . , . . .

References

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177 ......

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179 .. . . .

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Boulder, Colo., August 3, 1959.

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