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NSRDS-NBS 61, Part V

100

. U573

Ho. 61

Part V

1902
NATIONAL BUREAU OF STANDARDS

The National Bureau of Standards' was established by an act of Congress on March 3, 1901. The Bureau’s overall goal is to strengthen and advance the Nation's science and technology

and facilitate their effective application for public benefit. To this end, the Bureau conducts

research and provides: (1) a basis for the Nation’s physical measurement system, (2) scientific and technological services for industry and government, (3) a technical basis for equity in trade, and (4) technical services to promote public safety. The Bureau's technical work is per- formed by the National Measurement Laboratory, the National Engineering Laboratory, and

the Institute for Computer Sciences and Technology.

THE NATIONAL MEASUREMENT LABORATORY provides the national system of physical and chemical and materials measurement; coordinates the system with measurement

systems of other nations and furnishes essential services leading to accurate and uniform

physical and chemical measurement throughout the Nation’s scientific community, industry,

and commerce; conducts materials research leading to improved methods of measurement,

standards, and data on the properties of materials needed by industry, commerce, educational

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provides engineering measurement traceability services; develops test methods and proposes

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acquisition, application, and use of computer technology to improve effectiveness and

economy in Government operations in accordance with Public Law 89-306 (40 U.S.C. 759), relevant Executive Orders, and other directives; carries out this mission by managing the Federal Information Processing Standards Program, developing Federal ADP standards

guidelines, and managing Federal participation in ADP voluntary standardization activities; provides scientific and technological advisory services and assistance to Federal agencies; and

provides the technical foundation for computer-related policies of the Federal Government.

The Institute consists of the following centers;

Programming Science and Technology — Computer Systems Engineering.

'Headquarters and Laboratories at Gaithersburg, MD, unless otherwise noted; mailing address Washington, DC 20234. 'Some divisions within the center are located at Boulder, CO 80303.
Physical Properties Data Compilations

Relevant to Energy Storage.

V. Mechanical Properties Data on Alloys

for Use in Flywheels

- k i c. f / "p,

* ^ —

r ^ \<p / /

:

H. M. Ledbetter

Fracture and Deformation Division

National Bureau of Standards

Boulder, Colorado 80303

JUL 1 1932

bationaj- bumau

or a'fAKOAKOt

lturaht

tlo-L Cl _ Li r

N SRP S

U.S. DEPARTMENT OF COMMERCE, Malcolm Baldrige, Secretary

NATIONAL BUREAU OF STANDARDS, Ernest Ambler, Director

Issued January 1 982
Library of Congress Cataloging in Publication Data

Ledbetter, H. M.

Mechanical properties data on alloys for use in flywheels.

(Physical properties data compilations relevant to energy storage; V)

(NSRDS-NBS; 61, pt. V)

1. Alloys. 2. Fly-wheels. I. Title. II. Series. III. Series; NSRDSNBS; 61, pt. V. QC100.U573 no. 61, pt. V 602’. 18s 81-14053 [TA460] [620. 1 ’6] AACR2

NSRDS-NBS 61, Part V

Nat. Stand. Ref. Data Ser., Nat. Bur. Stand. (U.S.), 61 , Part V. 42 page^ (Jan. 1482) CODEN: NSRDAP

(c) 1982 by the Secretary of Commerce on Behalf of the United States Government

U.S. GOVERNMENT PRINTING OFFICE

WASHINGTON; 1982
Foreword

The National Standard Reference Data System provides access to the quantitative data of physical science, critically evaluated and compiled for convenience and readily accessible through a

variety of distribution channels. The System was established in 1963 by action of the President’s

Office of Science and Technology and the Federal Council for Science and Technology, and

responsibility to administer it was assigned to the National Bureau of Standards.

NSRDS receives advice and planning assistance from a Review Committee of the National

Research Council of the National Academy of Sciences-National Academy of Engineering. A number of Advisory Panels, each concerned with a single technical area, meet regularly to examine

major portions of the program, assign relative priorities, and identify specific key problems in need of further attention. For selected specific topics, the Advisory Panels sponsor subpanels

which make detailed studies of users’ needs, the present state of knowledge, and existing data re- sources as a basis for recommending one or more data compilation activities. This assembly of advisory services contributes greatly to the guidance of NSRDS activities. The System now includes a complex of data centers and other activities in academic insti- tutions and other laboratories. Components of the NSRDS produce compilations of critically

evaluated data, reviews of the state of quantitative knowledge in specialized areas, and computations of useful functions derived from standard reference data. The centers and projects also

establish criteria for evaluation and compilation of data and recommend improvements in ex- perimental techniques. They are normally associated with research in the relevant field. The technical scope of NSRDS is indicated by the categories of projects active or being

planned: nuclear properties, atomic and molecular properties, solid state properties, thermodynamic and transport properties, chemical kinetics, and colloid and surface properties.

Reliable data on the properties of matter and materials are a major foundation of scientific and technical progress. Such important activities as basic scientific research, industrial quality control, development of new materials for building and other technologies, measuring and correcting

environmental pollution depend on quality reference data. In NSRDS, the Bureau’s responsibility

to support American science, industry, and commerce is vitally fulfilled.

Ernest Ambler, Director

III
Preface

This series of publications is aimed at providing physical properties data on materials used in energy

storage systems. It was inspired by a requirement in the Department of Energy’s Division of Energy Storage

Systems for materials property data needed by its contractors in the timely development of energy storage

devices. As prime contractor for this program, the Lawrence Livermore Laboratory (LLL) has requested the

Office of Standard Reference Data (OSRD) to manage the task of gathering the data, using its established

network of data centers and other identified sources of expertise. The OSRD monitors the progress of work,

reviews the results, and conveys the numerical data to LLL where the data are converted for entry into an automated data storage and retrieval system. Every effort is made to supply data which have been critically

examined in light of the latest knowledge concerning theory and experiment. However it must be recognized

that in a rapidly moving technology some of the data will be superseded rather quickly as new materials and

techniques are introduced. Thus access to the data via computer terminal as well as publication in this series

should help provide the practitioner with timely and useful data which he requires to solve his problems in

energy storage. Funding for this series of projects from the Department of Energy, Division of Energy

Storage, through the Lawrence Livermore Laboratory, is gratefully acknowledged.

Previous publications in the series "Physical Proper-

•ties Data Compilations Relevant to Energy Storage”:

Janz, George J., Allen, Carolyn B., Downey, Joseph R., Jr., and Tomkins, R. P. T., Physical Properties Data Compilations Relevant

to Energy Storage. I. Molten Salts Eutectic Data, Nat. Stand. Ref. Data Ser., Nat. Bur. Stand. (U.S.), 61, Part 1, 244pp. (March 1978).

Janz, G. J., Allen, C. B., Bansal, N. P., Murphy, R. M., and Tomkins,

R. P. T., Physical Properties Data Compilations Relevant to Energy

Storage. II. Molten Salts: Data on Single and Multi-Component Salt Systems, Nat. Stand. Ref. Data Ser., Nat. Bur. Stand. (U.S.), 61, Part II, 442 pp. (Apr. 1979).

Miller, G. R., and Paquette, D. G., Physical Properties Data Compilations Relevant to Energy Storage. III. Engineering Properties of Single and Polycrystalline Sodium Beta and Beta" - Alumina, Nat. Stand. Ref. Data. Ser., Nat. Bur. Stand. (U.S.), 61, Part III, 19 pp. (June 1979).

Janz, C. J., and J omkins, R. P. 1 ., Physical Properties DataCompilations Relevant to Energy Storage. 1\ . Molten Salts: Data on Additional Single and Multi-Component Salt S\stenis, Nat. Stand. Rel. Data Ser., Nat. Bur. Stand. (I .S.) .61. Part l\ , 870 pp. (July 1981 ).

IV
Contents

Page

1. Introduction 1 2. Metallurgical Descriptions of Alloys 1 3. Properties of Interest 7

4. Data Collection 8

5. Data Analysis 8

6. Results 9

7. Discussion 9

8. Acknowledgment 9

Tables 10

Appendix 1 31

Appendix 2 32

V

Physical Properties Data Compilations Relevant to Energy Storage.

V. Mechanical Properties Data on Alloys for Use in Flywheels

H. M. Ledbetter

Fracture and Deformation Division, National Bureau of Standards. Boulder. CO 80303

This report deals with the physical and mechanical properties of 21 commercial

alloys that are candidates for flywheel rotors used as inertial-energy-storage systems. Base

metals include aluminum, iron, and titanium. Alloys vary in complexity from simple

carbon steels to superalloys. Properties include: mass density. Young’s modulus, shear

modulus, bulk modulus, Poisson’s ratio, yield strength, ultimate strength, fatigue

strength, fracture toughness, and creep strength. Property values were collected from

many types of sources and were analyzed statistically to detect possible outlying values. For each alloy, the report contains typical chemical composition, typical heat treatment,

metallurgical descriptions, and typical property values. The report also shows the

variations of these properties and the relative abundances of experimental property

values.

Key words: alloy; aluminum alloy; elastic constants; fly titanium alloy.

1. Introduction

Materials considered here are candidate alloys for flywheel rotors used as inertial-energy-storage systems.

The purpose of this study was to determine values of

particular physical and mechanical properties of alloys.

This was done by compiling data from the engineeringscience literature, analyzing the data statistically,

discarding “poor" values, and in most cases identifying

the trimmed arithmetic mean as the “best” value. In all, 21 commercial alloys were examined:

(1) aluminum alloy 6061-T6

(2) aluminum alloy 7075-T6

(3) titan ium-6alum in um-4vanadium

(4) alloy steel 4340

(5) maraging steel 18Ni-300

(6) precipitation-hardened stainless steel 15-7

(7) aluminum alloy 2024

(8) carbon steel 1020

(9) carbon steel 1040

(10) precipitation-hardenable stainless steel AM 355

(1 1) hardenable stainless steel 440C

(12) wrought stainless steel custom 455

(13) tool steel H-l 1 (14) titanium-6aluminum-6vanadium

vheel; iron alloy; mass density; mechanical property;

( 1 5) titanium-8molyhdenum-8vanadium

(16) resulfurized carhon steel Cl 141

(17) austenitic Cr-Ni stainless steel 316

(18) iron-based superalloy A286

(19) maraging steel 18Ni-400

(20) iron-based superalloy V57

(21) unitemp 212.

These alloys are described metallurgically in section 2

of this report. Table 1 gives their brief descriptions,

chemical compositions, and usual heat treatments.

2. Metallurgical Descriptions of Alloys

Aluminum alloy 6061-T6. This alloy has intermediate strength but excellent corrosion resistance and high

plane-strain fracture toughness. It is readily welded by

either the GTA or GMA process and with 4043 filler reheat treated welds has approximately the same tensile strength as the parent metal. Fusion welds have excellent corrosion resistance. Resistance welding is difficult and requires special care. Typical applications of 6061

are heavy-duty structures requiring h>gh resistance to corrosion such as truck bodies, marine structures,

railroad tank cars, and pipelines. The alloy is available

1
Table 1. Description of alloys, chemical compositions, and heat treatments.

UNS Number a Description Chemical Composition Usual Heat Treatment

A96061

A97075

G43400

SI 5700

A92024

G10200

G10400

535500

544004

545500

T20811

Wrought aluminum alloy, A1 hal , Cr 0.04-0.35, Cu heat treatable 0.15-0.40, Fe 0.7 max, Ag

0.8-1 .2 , Mn 0.15 max , Si 0.40-0.8, Ti 0.15 max, Zn 0.25 max, Others each 0.05

max, total 0.15 max

Wrought aluminum alloy, A1 bal , Cr 0.18-0.35, Cu heat treatable 1. 2-2.0, Fe 0.50 max, Mg

2.

1-

2. 9, Mn 0.30 max. Si 0.40 max, Ti 0.20 max, Zn

5.

1-

6.1, Others each 0.05

max, total 0.15 max

Wrought titanium alloy, A1 5.5-6.75, C 0.10 max, Fe heat treatable 0.40 max, H 0.015 max, N 0.07 max, 0 0.30 max, V 3.5- 4.5

Alloy steel C 0.38-0.43, Cr 0.70-0.90

Mn 0.60-0.80, Mo 0.20-0.30,

Ml 1.65-2.00, P 0.035 max,

Si 0.20-0.35, S 0.040 max

18Ni 300 maraging steel A1 0.10, B 0.003, Ca 0.05,

C 0.03 max, Co 9.0, Mn 0.10

Mo 4.80, Ni 18.50, P 0.01 max. Si 0.10 max, S 0.01 max, Ti 0.60, Zr 0.02

Precipitation hardenable Cr-Ni-Mo-Al stainless steel

A1 0.75-1 .50, C 0.09 max,

Cr 14.00-16.00, Mn 1.00 max,

Mo 2.00-3.00, Ni 6.50-7.75,

P 0.04 max. Si 1.00 max, S 0.03 max

Wrought aluminum alloy, .41 ba 1

, Cr 0.10 max, Cu 3.8-

heat treatable 4.9, Fe 0.50 max, Mg 1.2-1. 8, Mn 0.30-0.9, Si 0.50 max, Zn 0.25 max, Other each 0.05

max, total 0.15 max

Carbon steel C 0.18-0.23, Mn 0.30-0.60,

P 0.040 max, S 0.050 max. Other sheets and plates, C 0.17-0.23

Carbon steel C 0.37-0.44, Mn 0.60-0.90,

P 0.040 max, S 0.050 max, Other sheets, C 0.36-0.44

Cr-Ni-Mo stainless

steel, precipitation hardenable (AM 355)

Stainless steel

,

hardenable (440 C)

C 0.10-0.15, Cr 15.00-16.00,

Mn 0.50-1 .25, Mo 2.50-3.25,

N 0.07-0.13, Ni 4.00-5.00,

P 0.040 max, S 0.030 max,

Si 0.50 max

C 0.95-1.20, Cr 16.00-18.00,

Mn 1.00 max, Mo 0.75 max, P 0.040 max, S 0.030 max, Si

1 .00 max

Stainless steel, wrought C 0.05 max, Cb 0.10-0.50, Cr precipitation hardenable (custom 455) 11.00-12.50, Cu 1.50-2.50,

Mn 0.50 max. Mo 0.50 max, Ni 7.50-9.50, P 0.040 max, S 0.030 max. Si 0.50 max, Ti 0.80-1.40

Tool steel , hot-work

(H— 1

1

)

C 0.33-0.43, Cr 4.75-5.50,

Mn 0.20-0.50, Mo 1.10-1 .60,

P 0.030 max, S 0.030 max.

Si 0.80-1.20, V 0.30-0.60

Solution treat at 529°C

(985°F) and artificially age

at 1 60°C (320°F) for 18h (T6 plate)

Solution heat treat at 482°C

(900°F) and artificially age

at 1 21 °C (250°F) for 24h (T6 plate)

Solution treat at 816-941 °C

(1 500-1 750°F) 15-30 min, water quench, artificially age

at 482-538°C (900-1000°F) for 4-8 h, air cool

Austenitized at 829-899°C

( 1 525-1 650°F) , oil quench,

temper at 399-632°C (750- 1170°F)

Solution anneal at 816°C

(1500°F) for Ih/in, air cool,

age at 482°C (900°F) for 3h

Austenitize at 760-954°C

( 1 700-1 750°F) , cool rapidly

Solution treat at 493°C (920°F)

and artificially age at 191°C

(375°F) for 8-16 h depending

on product; cold deformation

after solution treatment de- pending on product

Hot rolled: 899°C (1650°F)

for 1 h, air cool; annealed: 899°C ( 1 650°F) for 1 h, fur- nace cool ; quenched and tem- pered: 899°C (1650°F), water

quench, temper at 204°C (400°F)

to 427°C (800°F) for 1 h, air

cool

Hot rolled: 843°C (1550°F)

for 1 h, air cool; annealed: 843°C ( 1 550°F) for 1 h, fur- nace cool

Double aged: solution anneal,

age at 732°C ( 1 350°F) 1-2 h, air cool, age at 454°C (850°F)

1-2 h

Solution anneal at 917°C

(1700°F) 1 h, oil quench, tem- per 2 h at 316°C (600°F) , 538°C

( 1000°F) or 760°C (1400°F),

and air cool

Solution treat at 816°C (1500°F

for 30 min, age at 482°C (900°F 510°C ( 950°F) , 538°C (1000°F),

or 566°C ( 1 050°F) for 4 h, air

cool

Solution treat at 1010°C (1850°

F), for 1 h, temper twice at 510°C (950°F) , 538°C (1000°F),

593°C ( 1 1 00°F) , 621 °C (1150°F).

or 704°C ( 1 300°F) for 1 to 2 h each, air cool

2
Tabl el.- Conti nued

UNS NUMBER

a Description Chemical Composition Usual Heat Treatment

G 1 1410

S31 600

K66286

Wrought titanium alloy, A1 5. 0-6.0, C 0.05 max, (1) Solution treat at 816 to 949°C

heat treatable (Ti-6A1-6V) Cu 0.35-1.0, Fe 0.35- (1500 to 1740°F) 1/2 - 4h, 1.0, H 0.015 max, N 0.04 water quench or air cool, age max, 0 0.2 max, Sn 1.5- at 482 to 871°C (900 to 1600°F)

2.5, Ti bal. V 5. 0-6.0 1 - 8 h, air cool

(2) Anneal at 704 to 982°C

(1300 to 1800°F) 1 - 8 h, air or furnace cool

.

(1) Solution treat at 774 to 816°C

(1425 to 1 500°F ) 1/6 - 1 h, air cool or water quench, at 427 to 649°C (800 to 1200°F)

1 - 24 h, air cool

(2) Cold roll 9 to 50% (usually

25%), solution treat at 760 to

81 6°C (1400 to 1 500°F ) for

1/6 - 1/4 h, air cool, age at 427 to 649°C (800 to 1200°F)

8 - 24 h, air cool

Wrought titanium alloy,

heat treatable (Ti-8Mo-8V)

Resulfurized carbon steel

(Cl 1 41

)

A1 2 . 5-3 . 5 , C 0.05 max

,

Fe 1 .75-2.25, H 0.015 max , Mo 7 . 5-8 . 5 , 0 0.10-

0.18, V 7. 5-8.

5

C 0.37-0.45, Mn 1.35-1.65,

P 0.040 max, S 0,08-0.13

Heat to 816 to 843°C (1500 to 1550°F), oil quench, temper at 204 to 704°C (400 to 1300°F)

Austenitic Cr-Ni stainless steel

Iron-base superalloy

(A286)

C 0.08 max, Cr 16.0-18.0,

Mn 2.0 max, Mo 2. 0-3.0,

Ni 10.0-14.0 max, P 0.045

max, S 0.030 max. Si 1-0 max

A1 0.35 max, B 0.001-0.01 , C 0.08 max, Cr 13.5-16.0,

Mn 2.0 max, Mo 1 .0-1 .5,

Ni 24.0-27.0, P 0.04 max,

S 0.03 max, Ti 1 .9-2.35,

V 0.1-0.

5

Anneal at 1038 to 1177°C

(1900 to 2150°F), Cool rapidly

Solution treat at 899 to 982°C

(1650 to 1 800°F) 1/2 -1 h, oil quench, age at 704 to 760°C

(1300 to 1 400°F ) 16 h, air cool

1 8N i -400 maraging steel b A1 0.12, B 0.003, Ca 0.05, (1) Solution treat at 760 to 816°C

C 0.01, Co 11.50, Fe (1400 to 1500°F) 1/4 - 1 h, bal. M0 4.69, Ni 18.0 air cool, age at 510°C (950°F)

Mn 0.01, P 0.004, S 0.005, 3 - 10 h, air cool

Si 0.003, Ti 1.33, Zr 0.008 (2) Cold deform 25-60%, solution

treat at 760 to 816°C (1400

to 1 500° F) , 1/4 - 1 h, air

cool , age at 454 to 593 °C (850-1 1 00°F) 3 - 8 h (3) Solution treat 816°C (1500°F)

1 h, air cool, age at 454 to 482°C (850 to 900°F) 3 h, air cool

Iron-base superalloy (V 57) A1Cr

Mo

Ti

0.25, B 0.008, C 0.06,

15.0, Fe bal . Mn 0.25

1 .25, Ni 25.50, Si 0.55,

3.0, V 0.25

Solution treat at 982°C

(1800°F) 2 - 4 h, oil quench,

age at 732°C (1350°F) 16 h, air cool

Iron-base superalloy

(unitemp 212)

B 0.01, C 0.05-0.15, Cb 0.6,

Cr 15.0-17.0, Ni 23.0-27.0,

Si 0.15, Ti 4.0, Zr 0.07,

A1 0.15

Solution treat at 1010°C

(1850°F) 2 h, water quench, double age at 774°C (1425°F)

2 h, air cool, 677°C (1250°F)

16 h, air cool

a Unified Numbering System for Metals and Alloys (Society of Automotive Engineers, Warrendale,

Penn., Second Ed . ,

1 977 )

.

b Properties quoted are actually for 350-grade.

3
in all commercial forms and in various sizes. Sheet and

plate are available clad with 7072.

Aluminum alloy 7075-T6. This heat-treatable

aluminum alloy contains zinc, magnesium, and copper

for hardness and has very high strength under static conditions in the T6 temper. It is available in a large range

of forms and sizes. In the annealed-and-solution-treated

condition it has good formability at ambient temperatures, and in the T6 condition it has good formability at elevated temperatures. The T6 temper has low fracture

toughness at room and cryogenic temperatures. A

recently introduced T73 temper has a lower tensile and

yield strength but improved fracture toughness

combined with better stress-corrosion resistance. The

unusually high static strength at ambient temperature is not reflected, however, in corresponding high fatigue re- sistance. Fatigue strengths are comparable to those of

2024 and 2014, which have lower static strength. The

loss of fatigue strength is thought to be due to the

progressive breakdown of the hardening particles, which

lie in the slip regions, progressively reducing their size

until they become unstable and dissolve into the matrix,

thus losing their hardening function. At high temperatures the alloy loses its strength advantage over 2024

even under static conditions.

Titanium-6aluminum-4oanadium. This alloy is the

most widely used of all the alpha-beta titanium compositions. It may be heat treated to a range of strength

levels. In its fully aged conditions it is successfully used

in highly stressed welded structures. However, in the

maximum strength conditions careful attention must be

given to the fracture toughness in design of highly

stressed parts. Hardenability is limited and sections

exceeding 2.5 cm (1 in) may not develop full properties.

The alloy has good strength and high stability up to 672

K (750 °F). Very high strength is obtained at cryogenic

temperatures. However, the fracture toughness below

116 K (-250 °F) is extremely poor for the fully heat- treated conditions and in the annealed condition inferior

to that of 5Al-2.5Sn. Low-temperature applications

should use the extra-low-interstitial grades. Welding

techniques for sheet have been highly developed and

procedures for heavy plate are under development.

Forming requires special methods and elevated temperatures. Alloy steel 4340. 4340, including its variety 4337,

which has a slightly lower carbon content, is the

preferred common low-alloy steel for air weapons where

good strength, high hardenability, and uniformity are

desired. It can be heat treated to strength values within

a wide range. For low-strength to intermediate-strength

applications, other low-alloy steels that have sufficient

hardenability possess nearly the same mechanical and

other properties as 4340. For high-strength applications,

this steel has been found to be superior to other

common low-alloy steels and also to some of the recently

developed more complex low-alloy steels. 4340 is available in all wrought forms, and castings in this steel are under development. It possesses a fair formability

when properly annealed and can be welded by various

methods. Forgings in this alloy, heat treated to high

strengths, require special measures in design and

fabricating.

Managing steel 18Ni-300. This steel is one of a class of maraging types that develops yield strengths up to 2400 MPa (350 ksi) primarily as a result of complex precipitation reactions in a very low-carbon Fe-Ni

martensite. The maraging steels were designed to have

superior resistance to crack propagation at high strength

levels. In the 18Ni maraging steels, transformation from

austenite to martensite occurs above room temperature.

Three composition ranges have been specified corresponding to typical yield-strength grades of 1400, 1700, and

1900 MPa (200, 250, and 280 ksi); the latter grade,

considered here, being more frequently designated as 2000 MPa (300 ksi). The various yield-strength grades

differ principally in the amounts of titanium,

molybdenum, and cobalt in the composition. (Material

with yield strength up to 2400 MPa (350 ksi) may be

obtained from some producers through further

adjustments in composition.) The actual strength and

toughness will vary considerably within the composition

limits and can also depend strongly on the processing

history. High fracture toughness, compared with other

types of quenehed-and-tempered steels, characterizes a properly processed sheet product. The toughness and

impact properties of heavy sections are superior to those

of conventional medium-carbon, low-alloy, ultrahighstrength steels heat treated to tensile strength levels exceeding 1700 MPa (250 ksi). However, the fracture

properties of heavy sections can be directional and are lowest in the short-transverse direction. This directionability is influenced by the melting and processing conditions.Corrosion and oxidation resistance are somewhat

better than 4340 steel. Resistance to environmentassisted crack propagation is better than 4340 steel at an equivalent level of tensile strength. Hydrogen

embrittles the maraging steels, but they exhibit a greater

tolerance for hydrogen than conventional low-alloy

steels. Formability is excellent in the annealed condition.

The steel is readily machined in the annealed condition

and can be machined in the fully aged condition. A high

degree of dimensional stability is maintained throughout

4
heat treatment. Welding requires special precautions,

and the toughness of the weld deposit is generally below

that of the parent metal.

Precipitation-hardened stainless steel 15-7. This alloy

is a semi-austenite precipitation-hardening stainless

steel. It is a modified 17-7PH alloy in which 2 to 3

percent molybdenum is substituted for an equivalent

percentage of chromium. Thus, higher strengths can be

obtained both at room and elevated temperatures in the

various heat treated conditions. The alloy can be

considered for use at temperatures up to 811 K

(1000 °F). PH 15-7Mo is essentially austenitic at room

temperature in either the annealed or solution-treated

condition, but can be transformed to martensite by a series of thermal treatments or by cold working. The

alloy can then be hardened further by thermal treatment

to strengths exceeding 1400 MPa (200 ksi) at room temperature. The alloy is available in sheet, strip, plate, bar,

and wire. It can be formed readily in the annealed condition and is welded easily by various methods. Its heat treatment is identical with that of 17-7PH, and much of

the information available for the latter alloy applies also

to PH 15-7Mo.

Aluminum alloy 2024. This heat-treatable wrought

aluminum alloy is the final development of the dural

type, which contains copper, magnesium, and manganese

as hardeners. Its strength properties in various tempers

are among the highest obtainable in aluminum alloys.

Including clad 2024, it is still the most used highstrength alloy and it is available in all wrought forms,

except forgings. The room-temperature aged conditions

of this alloy should not be used where the temperature

exceeds 339 K (150 °F) and corrosive conditions exist. The more recently developed artificially aged conditions

maintain their strength and corrosion resistance up to a temperature of 422 K (300 °F). The corrosion resistance

of the alloy is inferior to that of alloys free from or low

in copper. Therefore, where higher corrosion resistance

is required, clad 2024 sheet and strip is preferred over

the bare material. The alloy is readily formable in either

the annealed or solution-treated condition. Limited

forming can also be performed in the T4 condition. The

maehinability of the heat-treated conditions is very good.

The alloy may be resistance welded, but fusion welding

is not recommended.

Carbon steel 1020. This low-carbon, nonalloyed steel finds extensive use in large-scale construction. It machines easily and forges readily. In general, such a

steel combines fair strength with high ductility and excellent fabrication properties such as rolling, drawing, and

welding. It is used mainly as hot-rolled, normalized, or annealed.

Carbon steel 1040. This medium-carbon, nonalloyed

steel can be quenched and tempered to produce high

toughness and good strength properties useful in engineering applications such as shafts, gears, connecting

rods, rails, rail axles, and drop-forging dies. Precipitation-hardenable stainless steel AM355. This

alloy is one of a series of age hardenable steels that combine high strength, at temperatures up to 700 K

(800 °F) and higher, with the corrosion resistance of

stainless steels. In the annealed condition, the alloy is austenitic. Upon forming at room temperature the alloy

work hardens very rapidly because of martensite

formation during working. Formation of martensite can be avoided by working at temperatures of about 422 K

(300 °F) or higher, in which case the alloy forms in much the same manner as conventional austenitic

stainless steels. AM355 is a companion alloy to AM350

differing from it by a slightly lower chromium content and a higher carbon. Although designed primarily to meet the demand for heavier sections including plate,

bar, and forgings, it is also available in sheet form,

which is the principal field for AM350. While the compositions of the two alloys are very similar, the small

differences account for significant changes in structure. For example the AM350 has 5 to 20 percent delta

ferrite; AM355 usually has little or none. Hardenable stainless steel 440C. These 17-percentchromium martensitic stainless steels are produced with

various carbon contents. Type 440A contains about 0.70

percent carbon, type 440B about 0.85 percent carbon,

and type 440C about 1.10 percent carbon. Type 440F is a free machining grade of type 440C and contains

additions of either sulphur or selenium. All these types

are used in the hardened condition where a combination

of high wear and corrosion resistance is required. Their

hardness and wear resistance increase with increasing

carbon content, while their shock resistance and ductility

decrease.

Wrought stainless steel custom 455. Custom 455 is a versatile, low-carbon, martensitic, age-hardening Cr-Ni

stainless steel with good corrosion resistance and

favorable fabrication characteristics. It is intended for service up to 700 K (800 °F). A single aging treatment

in the range of 755 K (900 °F) to 835 K (1050 °F)

develops high tensile and yield strengths. The fracture toughness and ductility in tensile tests decrease with

increasing strength level. The K|S(:( values in salt solution decrease with lower aging temperatures and are

relatively low for the fully-aged condition. It can be

readily cold-formed, welded, and machined in the

annealed condition. Typical applications include highstrength aircraft fasteners and forgings, components for
nuclear reactors, springs, valve stems, gears, shafts, ring

seals, retaining rings, pressure vessels, and various parts

for use at cryogenic temperatures.

Tool steel H-ll. This steel is a modification of the

martensitic hot-worked die steel type H-ll with minor

changes in chemical composition including slightly

higher carbon content. This composition permits heat

treating the steel to high strength. It is used extensively

in the form of sheet, bar, and forgings at various

strengths at room temperature. Also, due to its high

chromium content, this steel is of the secondary

hardening type and requires tempering temperatures

exceeding 755 K (900 °F). Therefore, it is suitable in its full-hardness condition for high strength applications at temperatures up to 811 K (1000 °F) when protected

from corrosion and oxidation by appropriate surface treatments. The steel has good formability in the

annealed condition, is readily welded and exhibits little distortion when heat treated. This tool steel has

relatively good toughness because of low carbon content;

it has good to excellent hardness and fair wear resis- tance and machinability.

Titanium-6aluminum-6vanadium. This is a heat- treatable alpha-beta alloy similar in many respects to Ti- 6A1-4V but containing increased content of beta

stabilizing elements, which provide higher strength

potential at a sacrifice in both toughness and

weldability. In forged sections and plate up to 2.5 cm

thick. solution-treated-and-aged material has a guaranteed minimum /j u =1200 MPa (170 ksi). For

forged sections between 8 and 10 cm the corresponding

Ftu = 1000 MPa (150 ksi). Response to heat treatment may vary from heat to heat and the correct aging temperature is best determined by tests on the heat in question.

As is characteristic of other titanium alloys, exposure to stress at elevated temperature produces changes in the

retained mechanical properties. The stress and temperature limits below which these changes will not occur have not yet been established for this alloy. Structural

applications should be based on a knowledge of the low

toughness characterizing the higher strength conditions

of this alloy and the limited toughness of welds.

Particular attention should be given to the influence of

aggressive environments in the presence of cracks. Such

environments include aqueous solutions of chlorides and

possibly certain organic solvents such as methanol.

Titanium-8molybdenum-8vanadium. Ti-8Mo-8V-2Fe3A1 is an ageable, metastable beta alloy developed under

U.S. Army Contract DA-30-G69-ORD-3743. It was

developed primarily as a high-strength, formable sheet

alloy. But it also possesses hardenability in 10.2 cm (4

in) sections (possibly in 15.2 cm (6 in) sections) and

potential as a fastener alloy. In common with its competitor, Ti- 13V-1 lCr-3Al, the alloy’s body-centeredcubic phase (high temperature allotrope) is retained on

cooling from solution temperatures to ambient temperature at relatively slow rates. The stability of the beta

phase, however, is such that the alloy can be

subsequently strengthened by reheating above 700 K

(800 °F) through the conventional precipitation of alpha

phase (close-packed-hexagonal structure). The alloy is superior in aging kinetics, requiring less aging time to achieve high strength levels. Also, the alloy is claimed to have superior notch fatigue strength, modulus of

elasticity, stability at 589 K (600 °F), and, in the

annealed condition, salt water corrosion resistance. The

major disadvantages of this and other beta alloys

compared to alpha-beta alloys are high density and

relatively poor creep properties at elevated temperatures.

This alloy does not apparently possess smooth fatigue re- sistance commensurate with its higher strength when

compared to Ti-6A1-4V. The alloy is a relatively new

composition which, in some respects, is still in a state of

development. Thus, reported measurements are

tentative. Resulphurized carbon steel Cl 141. This alloy steel contains high manganese content. Manganese, a carbideforming element, increases its hardenability by shifting

the nose of the temperature-time-transformation curve to the right. Compared to the medium-carbon-content steel 1040, Cl 141 has much higher hardenability.

Austenitic Cr-Ni-stainless steel 316. These

molybdenum-bearing grades of austenitic stainless steel, which are normally used in the annealed condition,

cannot be hardened by heat treatment; however, they can be hardened by cold work. The molybdenum content

of 2 to 3 percent in type 316 provides marked

improvements in corrosion resistance, particularly

pitting corrosion, and in elevated-temperature strength over the non-molybdenum-bearing austenitic stainlesses. The higher molybdenum content of 3 to 4 percent in the

less widely used type 317 results in further

improvements in these characteristics. They retain usable strength and oxidation resistance at temperatures

up to 1089 k (1500 °F). They are, however, susceptible

to carbide precipitation and associated intergranular

corrosion as a result of exposure to temperatures in the

range 755 K (900 °F) to 1144 K (1600 °F). Low carbon

modifications, 316L and 317L, are recommended when

exposure in this temperature range is unavoidable,

although the lower carbon results in lower strength. In

cast form, type 316 is generally designated CF3M,

CF8M, and CF12M, corresponding to carbon contents of

0.03, 0.08, and 0.12 percent, respectively. The wrought

6
and cast forms are readily weldable, and the wrought

forms have good formability in the annealed condition.

These alloys are used in various jet-engine parts,

exhaust manifolds, heat exchangers, boat trim, chemicalprocessing equipment, photographic equipment, furnace

parts, and orthopedic implants.

Iron-based superalloy A286. This alloy is one of the

first and most popular age-hardenable, austenitic, nickelchromium steels and has pioneered the successful application of this type of superalloy for high-temperature

use. It is similar to and a development of the German

alloy Tinidur. It is used primarily at temperatures up to 978 K (1300 °F). The alloy is available in sheet, plate,

bar, tubing, wire, extrusions, and forgings. Investment

castings are also produced. It can be formed and welded.

Maraging steel 18Ni-400. This alloy is consumable vacuum melted and relates strongly metallurgically to the 300-series alloy. Containing less than 0.03 C, it combines a yield strength of about 2800 MPa (400 ksi)

with exceptional ductility and toughness for that strength level. An annealing treatment places it in the

best condition for machining and forming. Subsequent

aging increases hardness by a precipitation reaction in the martensite matrix, with corresponding higher

strength properties. Designers and users of this alloy

find among the many desirable characteristics: very high

yield strengths, good ductility and toughness; high

notch-to-smooth tensile strength ratios for a material

with this strength capability; good formability characteristics, both hot and cold, with low work-hardening

tendencies; easy weldability; freedom from

decarburization without use of a protective atmosphere;

ease of heat treatment; minimum distortion during heat

treatment; excellent hardenability; and a low coefficient

of expansion.

Iron-based superalloy V-57. This austenitic stainlesssteel alloy has a good combination of tensile and creep

rupture properties up to 1089 K (1500 °F) at high

stresses. It is a higher titanium and boron modification

of A286 stainless steel and is primarily used for some

parts of aircraft gas turbines.

Unitemp 212. Because of high chromium content,

this alloy is a stainless steel. But it is considered a superalloy because of its superior high-temperature

properties. Designed for service to 1033 K (1400 °F), it resists heat and corrosion. At room temperature and

above, it has a high strength-to-weight ratio. Its high

titanium content causes segregation, which leads to problems in hot working. Its hot-working temperature is relatively low: working above 1339 K (1950 °F) causes

cracking. For room-temperature use only, this alloy does

not offer the best combination of usual mechanical

properties. It has been used for aircraft bolts and for guided-missile components. This alloy was developed

and patented by a U.S. steel company as a promising

high-strength superalloy. But lack of demand has

removed it from production.

3. Properties of Interest

The following properties were covered in this study:

Physical Properties

(1) mass density.

Elastic Properties

(2) Young’s modulus

(3) shear modulus

(4) bulk modulus

(5) Poisson’s ratio. Mechanical Properties

(6) yield strength

(7) ultimate strength

(8) fatigue strength

(9) fracture toughness

(10)

creep strength.

Elastic constants are, of course, physical properties. But

in this report it is useful to consider them as a separate

subclass. Definitions of the various properties together with

their usual SI units are as follows:

Mass density: mass per unit

volume.

Young’s modulus: ratio of uniaxial

stress to strain along the stress

axis, in either tension or compression.

Shear modulus: ratio of stress to corresponding strain when stress

is either pure shear or pure

torsion. Bulk modulus: negative ratio of hydrostatic stress (pressure) to volume change.

Poisson’s ratio: negative ratio of transverse strain to axial strain in a uniaxially stressed body.

Yield strength: stress at which a material deviates significantly

from linear stress-strain behavior;

physically, the onset of plastic

deformation.

Tensile strength: maximum tensile

stress a material can sustain,

based on original cross-section.

g/cm

GPa

GPa

GPa

dimensionless

MPa

MPa

t
MPa

MPa-m 1/2

MPa

Fatigue strength: maximum stress a material can sustain for a specified

number of load cycles, N.

Fracture toughness: resistance of a material to fracture in the

presence of a sharp crack, under

plane-strain, expressed as critical linear-elastic stress-intensity

factor, Kw. Creep strength: stress that causes a given creep strain in a given time.

4. Data Collection INVERSE NORMAL PROBABILITY FUNCTION

Property data were compiled from the following types

of sources:

1. handbooks

2. books

3. reports

4. review papers

5. manufacturers’ literature

6. engineering-science literature

7. unpublished NBS studies.

Many data were obtained from type-1 sources and fron

readily available sources. A chronological bibliograph)

of these is given in appendix 1. Type-6 sources were sought only in cases where very limited data were

available elsewhere. These type-6 sources were located

using:

1. NBS Cryogenic Data Center literature searches

2. Metals Review

3. Metallurgical Abstracts.

From each source, data were recorded on a worksheet

(app. 2), which included chemical composition, thermalmechanical treatment, and other relevant observations.

5. Data Analysis

Two hundred fifty-two data sets (21 materials, 12

properties) were examined statistically for normal distri- bution when the data set contained at least 5 entries. Data-set size ranged from 0 to 111. Examples of normaldistribution probability plots are shown in figures 1-2. When data were distributed nearly normally,

computations were made for: the mean value, the

Fli.l RK 1. Normal-distribution test for yield-strength data for Ti-6A1- 4V. The straight line represents normally distributed data. For

the materials and properties considered in this stud\. these data represent an excellent fit to a normal distribution.

INVERSE NORMAL PROBABILITY FUNCTION

Fk.LHK 2. Normal-distribution test for fracture-toughness data for alloy steel 4340. Normally distributed data would fall along a straight line. Excluding the two highest values, these data

deviate slightly from a normal distribution.

median value, the standard deviation, and a trimmed

mean. Trimming consisted of discarding 7 percent of the

highest values and 7 percent of the lowest values.

Retaining 86 percent of the values amounts to retaining

all values within ±1.5cr, where cr is the standard

deviation. For a large sample size this corresponds ap- proximately to retaining values within a 90-percent

confidence interval. This ±1.5cr cutoff is a judgment

based on the experience of our laboratory in previous ex- perimental and analytical studies. In a few cases, data

8
were distributed non-normally and other methods were

used to ascertain a “best” value. Strong evidence of non- normal behavior in a probability plot was the exception.

Many of these exceptions were for cases where one value was repeated in several references. Such data are best summarized by giving the most prevalent value. Outliers

seldom occurred, thus eliminating the need for the

trimmed mean in many cases. 6.

Results

About 1700 worksheets resulted from the

compilation. These worksheets contain 3900 individual

data, an average of nearly 200 per alloy, ranging from

14 to 574 per alloy. For brevity, these worksheets are omitted here and the results are summarized by alloy in tables 2-22 in both SI and English units.

7.

Discussion

This study suffers from several limitations: reliance

principally on secondary sources, neglect of test-variable

effects, and use of normal-distribution statistics. Perhaps

future related studies will alleviate these limitations. Despite these drawbacks, this study provides many

new insights together with information that may promote

further understanding. For the first time, for 21 technological alloys, physical-property and mechanical-property

results have been collected from a variety of secondary

sources. We see clearly the range of results, the mean

value, and the deviation of the mean. The computed

standard deviations represent perhaps the most

pessimistic statement of uncertainty because the data

contain nearly every imaginable uncertainty source: chemical composition, thermomechanical processing,

sampling method, test method, experimental error, transcription error, and so on. Where data sets are

sufficiently large, we see that practical bounds can be

established for the property value. Knowing such bounds

is enormously useful and is an essential first step toward

determining improved bounds.

That the data may be distributed non-normally seems

irrelevant to present purposes. The “errors” may still be

random. And, calculating mean values and standard

deviations is always valuable for comparing distributions

of data, whatever their actual distribution. We chose to exclude extrema from our summary tables because we

believe that (in most cases) these represent poor

experiments rather than unusual materials.

The veracity of this study can be established partly by

comparing its results with the few existing exhaustive

studies of property variability. For stainless-steel 316,

this is possible because the elastic-property variability was reported recently by Ledbetter (Metal Sci., Dec. 1980, 595-596) and the mechanical-property variability

by Sikka (ORNL Report 5384, 1978). Results from

neither of these two reports were included in the present

study. However, table 23 contains the comparison,

which is good for all properties except yield strength, the property with highest uncertainty.

From the data in the tables the average mass-density

uncertainty is 0.3 percent, the average elastic-constant

uncertainty is 3 percent, and the average mechanicalproperty uncertainty is 19 percent. Mass density is reported infrequently, but it is well known because of

the relative simplicity of measurements and the insensitivity to metallurgical variables such as composition and

heat treatment. None of the four elastic constants—Young’s modulus,

shear modulus, bulk modulus, Poisson’s ratio—is systematically better known than the others. Young’s modulus

is reported more often than the other three constants combined. Direct bulk-modulus measurements are reported seldomly because such measurements are

difficult. Among the four mechanical properties—yield

strength, ultimate strength, fatigue strength, and fracture toughness—the yield and ultimate strength have the

lowest uncertainties. Fracture toughness is about 25

percent uncertain; this reflects both experimental

inaccuracy and material variability. Fatigue-strength data

are relatively scarce because of the long testing times

involved; the large uncertainty in these data, about 25

percent, is due mainly to material variability.

8.

Acknowledgment

R. P. Mikesell was responsible for data collection. M.

W. Austin and G. Maerz for data collation, and J. F. LaBrecque for statistical analysis. J. Dahnke assisted in preparing the report.

9
TABLE 2

(SI).

SUMMARY

OF

PROPERTY

DATA

FOR

ALUMINUM

ALLOY

6061-T6

C/I

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03

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CO ^ H 03

r-C 3 D- c o o

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oj < 0 3 £ o u

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DO f \ • H G G

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03

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Standard

Deviation

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TABLE 6

(SI ).

SUMMARY

OF

PROPERTY

DATA

FOR

MARAGING

STEEL

18Ni-300

CD CO h <d(b 3 3 - bo 3 3 X O S

E— ^OX

CJ

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33

33 3 M 0 3 3 £ 33 0 E 3 CJ • H 3 3 3 M 0 X co X

X

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CJ

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3303X

12

Standard

Deviation
Fatigue

Strength

Young's

Shear

Bulk

Poisson's

Yield

Tensile

10^

10 3

19^

10^

Fracture

Density

Modulus

Modulus

Modulus

Ratio

Strength

Strength

Cycles

Cycles

Cycles

Cycles

Toughness

(g/cm 3)

(GPa)

(GPa)

(GPa)

(MPa)

(MPa)

(MPa)

(MPa M

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cnj CNJ CNJ CNJ rO 3 Cl. 03 03 03

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i— 03 03

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i

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13

Percent

Uncertainty

0.0

1.1-_-

45.5

36.0
TABLE

10(SI).

SUMMARY

OF

PROPERTY

DATA

FOR

CARBON

STEEL

1040

l/l cn

CD c/1 CD cn 3 CD 3 3 Lf CO 3 CD 3 3

+-> _sz

4-> _3 CO *=3” CM

(j cn 03 , i 1 I 1 cj cn 03 LO

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CM

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TABLE 12

(SI ).

SUMMARY

OF

PROPERTY

DATA

FOR

STAINLESS

STEEL

440 C

CD CO

s- a> 3 C I o cj r— >. o

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Percent

Uncertainty
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16
TABLE

16(SI).

SUMMARY

OF

PROPERTY

DATA

FOR

TITANIUM

ALLOY

Ti-8Mo-8V

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(0 CO U 0) 0 d

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TABLE 1

8(

SI ).

SUMMARY

OF

PROPERTY

DATA

FOR

AUSTENITIC

Cr-Ni

STAINLESS

STEEL

316

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18
TABLE 2(0SI).

SUMMARY

OF

PROPERTY

DATA

FOR

MARAGING

STEEL 1

8Ni

-400 2 co h a; 2 2

4-1

X

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19

Standard

Deviation

0.028
TABLE 2(2SI).

SUMMARY

OF

PROPERTY

DATA

FOR

UNITEMP

212 3 3 3 3 u x u CxO 3 3 3 o X H3 O i—

cd PHa

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00

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Standard

Deviation

0.0002

0.3

0.04-

0.005
TABLE

3(E).

SUMMARY

OF

PROPERTY

DATA

FOR

ALUMINUM

ALLOY

7075-T6

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rH P rH 1 1 1 1 rH P 04 rH rH rH o O P T3 43 o P P CD CQ C3 C3 t-H CQ O O o o o o o S rH ,—\ S T-H v—/ CU ' r—-> rt r—n

If) -H CD -H P p CD CU P P CD P rH DU CD O CD 04 ,-1 P rH DU LO

p- X 0 P 43 00 CD 00 o cD CQ 0 P 43 t-H rH T-1 o 04 rC T3 CD < p: oo cd CO O o NO NO NO o O cp o o 43 43 43 o ’ 1 S rH 5* rH W

CO If) -H CD CD -H — p CO rH o 04 CO P CD

too r-H DU P" p- P rH 04 OO r—1

DU o o rH LO P P LO • P P LO P 'P CD o o o o rH p t3 cD rH 43 43 43 o to o o o rH rH rH o o o rH t-H T-1 X S rH X S T-H '—

f N Xoo X O X o Xno rH O rH p4-J P o o 4-> P O O o C3

•rH *rH o O o o •H *H 43 43 43 o LT)

If) *X oo rH o t-H CD

X

X rH t-H

T-* o 04 P P P X 0 rH o O o o o 0 rH O O o o O Q ^ Q w po X4-> P po X4-J P

If) • iH •H CD •rH • pH p 4-> P P +-» P o p 4-> o p 4-J

•rH • rH P •pH •H P

4-> 0 p > 0 +-> 0 p r* 0 P p p 0 CJ P P p 0 CJ > 0 0 o P > 0 rH 0 Q P P P p P> P P P s 33 0 > op 0 > Ip

If)

p op P 4-» CD P T3

p 4-J

Xo > pp 0 P

op P0 Xo > PP 0i p

P3 P0 c •H p 0 P •H e P o p T3 • rH p p P T3 •pH P p

No 0s 0s P

£—

4-> CP 0

CU | No 0s 0S P

E—

4-J CO 0

Cu

21
TABLE

5(E).

SUMMARY

OF

PROPERTY

DATA

FOR

ALLOY

STEEL

4340 P 0 P P -H P (/) U OO pH P 3 P o<^

U.

X

O

X

cj

,P OO P 0

OOtD r-H COO O r-H x ' P CJ P

CO

CD o’ P CO C OO 0 t •H LO r-H v P O O P t-hi X

CL. CJXu

rC -H

4—1 CO 00 pH P

CD oo P O P i-H CO ^P CO T) W) P •“» P

CD 0 ro •H p O X P *-H co ^

co P H CC

CO -H P CO

r-H Qh o o

CO -H P P CO P l-H Ph

CD P ^ X T3 ^

COO

O

O

OJ

PJmX

COw

xi

CQ<

CD CO f P CD P P -H X x CO O 00 pH p p P

CLX o X

cj

x: <o P CD O0<X) .-h COO CD i-H X / P CJ • P

CO

CD o P CO < OO CD 1 •hlo r-t ' POO P ^ XXo c

CD X COp co OO pH p

CD co P O P co

O OO Ph P

<D H P O X p H

CO ^ P o O -H

CO P

CO P

•H O' o

CO -H p co

X -H Ph

•-H P P

CQ

O

O

CO -H P CO -H P- P

TD CD o o oo

to CO -H p CO 00 H Ph §

•§“> o o o X S H

XoX oo

to

X

cnX

cr> o o

to

CO CO -H — p CO OOH Ph P P P ’-p CD O O o X S r->

X

\D

X vD t

l XXXXX X X

Xco p p to to to •H -H OO 00 00

CO

X \D

X CJ

X P X) • (D r-H Q o o o

*Tf oooo

Xco P P

•H *H

CO X. P ,P

CD P Q ^

to o

O') Xo

O') 00Xo o

CT) Xo

LOcoo X

p

p o p

CO • rH •H p P P o P P H •rH fH p 0 P > 0 P p P 0 0 > 0 1—1 0 Q P P p P S P) 0 r-H > X

CO P 'P P P

,P > p 0 P P o P £ X 0 p •H § P O p X •H P P o 0 0 p P 0

2:

X CO Qh

22

Percent

Uncertainty

1.7

7.5--

3.3

12,. 0

10.4

15.6

24.0

25.0

20.9
TABLE

7(E).

SUMMARY

OF

PROPERTY

DATA

FOR

PRECIPITATION-HARDENED

STAINLESS

STEEL

15- 1

CO

CD CO P <D 3 P -H

4->

X CO

CJ bO Ph

03 3 P O

tu

h o

CD to

S- CD 3 C

to

u cn CL

fO 3 p o oo

U- f— o o

CXI

C\J

CJ o

yD

,3 CO

4-> CD bOco r-n p O CD

(D T-H >v, , P U • 4-> CO

(D

a 3 co c bO <D r •H to r-< Y

4->

O CJ 3 rH X

IX

u

O <J ^ XU

cjo

>>

C-J

CD

oo

CD3 LO

cn o O

X> C_J ro

*3-o

to

CJ CJ

LO

*3"

bO Ph P

CD co p o C CD 0O

CD P O

OrLO

CO

OO

C\J CO

4-> CO 3 bO P •“« P

CD 0fO

•H

pO >H O rH

CO ^

ZD—I

<C td cn to

CD CD •r P CO

>- +->

O oo .

oCO

’3" CO P o O -H

CO 4-> co 3

•H DC o

ex

to re

•r- CX o

CO -H 3 CO ^ H Oh H 3 3 T3 cd CO O O 3 TD CO

co o o

CO «H P 3 co 3 f-H Ph

CD 3 3 3 cd CO o o

3-O

to -I— P 3 to (Or- CL

CD 3 H b CD

oo o o

oo

OY

oo

or ooCJY

CO CO -H 3 CO bO '—i Ph P 3 3 3d) o o o ^ S o

cr>

(?) o 3 3 CO o o o

COotooCOo

4-> P P X) >>oo oo ooo o

CD o

23

Standard

Deviation

0.0

0.2

0.11 -

0.006

11.0

12.5
Fatigue

Strength

Young's

Shear

Bulk

Poisson's

Yield

Tensile

10 4

IQ 5

10 6

10 7

Fracture

Density

Modulus

Modulus

Modulus

Ratio

Strength

Strength

Cycles

Cycles

Cycles

Cycles

Toughness

(lb/

in 3)(1

6

psi )(1

6

psi )(1

6

psi )

(10 3

psi) (

10 3

psi )

(10 3

psi)

(10 3

psi/Tn) 1

</> LO LO LO •=d- CD co

CD CM CO CO CO CO =3 C •>- CO CO co 4-5 _C CO O 03 CD- 03 Z3 L O CO

Li_ |—

O"—

CO

CD

O 1 1 1 1 i i— 10 yc o

_CZ CO

4-> CD

O 1 1 1 1 i 03 CO i— C O c_) *

CD -— >> *i— S- O co

4-5 Q- OO

CO CO

CD CD

O

O 1 1 1 1 i =3 LO i— i

03 o O

•r- >“ >>

4-5 C_D 03

Li— CO

CD

O 1 1 1 1 i ^ i— O u O «— >> o O

l— „—

1 CD -O vCO o LO CO o LU i— 4-> tO CM LU •r- 03 Q. 03 03 i

CM co 1— CO

C

CO 03 CO co OO

C CD co

CD S- CD |— -M r— o OO

COcc<C_J -i— CO o CO LO "O 03 CO LO DC r— SZ Q_

CM co co CO LO

O CD CD CO LO CO CM l_L_ •r— S- CO

>- 4->

O

<c OO i—

1—

—- <c

CD

CO CO >- - CO h- c: o

r— CM 1 1 1 1 CC o •«- LU CO 4-5 O Q_ to 03 O •f- CE

QC o

Q_ o_

Li_ O -—>

to •!— >- 3 CO o l 1 1 l 1 C£ — CL C r— Z5 ZE 13 TD CO

z: CO

OO => Z r— C/) ’ -—

to *i— CO LU S_ Z3 co 1

1 1 1 1 ^ -- 03 i— Q- f— O CD 13 <— “ SZ “O CO

OO o o LU z: i—

_l »*

—

CO<C

1— -—

to CO -I— 03 03 03 co , - =3 to CO 03 03 03 o r_* 03 r— Q_ C =5 CM CM CM 13 “O CO O O O >- Z r—' ' „ _ CO CO CO >^CO

CO CO co 4-5

C

CM CM CM CM o o •i— *i

—

to \ c O O o o C _Q

CD r—

CD -

>> c 4-5 o c

CO • 1

.(

c. 4-> 03 o 03 4-> 1

• i

S4-J CD c > CD 03 Z3 03 CD U > CD i

CD CD c

S- Z3 <T3 ZD

CD i

> “O

CO 03 "O S- 4-5 _Q > C CD 03 C O re E ID CD

£Z •f— E C CJ

03

O •i

03 SO CD CD S- 4-5 CD ZI z: 1— OO Q_

Ooo

C\J oooo

_oo oo

CO

Oh

LO

CO

CO

r-^ oco

CDo I I I I I I I I I o co co CM «sj- 03

03 03 r— O LO co

os co

LO CO OO I I I I I I I I

CD

=3c

ro oCD

“O

CD >

CD Q

"O

S-03 "UC

03

4-> OO

24

Percent

Uncertainty -----

41.1

20.4
TABLE

11(E).

SUMMARY

OF

PROPERTY

DATA

FOR

STAINLESS

STEEL

AM355

CO

CD co s.

S- CD 3 C •r— CD 0 CD r^.

-*—> -C CO LO u cn CL CO CO *3- 1

ro 3 CD CD 1

CVJ S- O ro

Lu hOv—

CO

CD

OOO 1

ro 1

0 0 r^ 00 00 «— as as as

CJ

-C CO 4-> CD 0 0 0 CD LO cn co 1

coo / ' CVJ CVJ CVJ *3" CD 1

"I— 0 0 0 s- 0 CO 1— 1

1

4-> CL 00

co ro

CD CDO CVJ LO CVJ

r 3 LO r— 1

OOO 1—•

CO CO 00 CVJ 1

•r- r- >> 1— t— 1—

+->

O 1— 1

1—

ro U_

CO

CD 0 1

OO r— 0 1 1 1 1 «— >0 Cvj O 1 „ x CD -C •1

1— +-> CO LO LO 0 1

•r- cn CL ^t

CO c=

O LO r— CD

c: CD ro 1

O'. O'. as ro 1

CD s- 0 r— 1

1

1— -0 1

00

_c

-0 •r— t3 cn CO CVJ

O CVJ 1— c CL OS

CD CDO 1

00 ro as

•i- S_ ror\ ro 1

>- -t->

O 1

i

1

OO r—

COc 0 0 -f- CO -M

O 1 1 1 1 1 CO ro

•1- ad 0

a_

CO •r— 3 CO LL 1

CL 1— 3 O 1 l * 1 1 3 “O CD

CO

O

O

z: 1

"„ s CO • 1—

O =5 CO

ro 1CL

CD 3 1

1 1 1 1 -C TD CD 1

00 0 O 1

5- 1

CO CO • 1— 3 CO cn.— CL 1

O 1— CO CD

C 3 CD 3 -0 CD as as as 0 CVJ 0 0 0 OJ CVJ CVJ >- z 1—v—' „ -0 C CVJ CVJ CVJ

•r— •r— CO CO co 0 CO "

'=3- CVJ CVJ CVJ 0 LO c JD

CD 1— 0 0 0 0 O Q

>>

c: +-> 0 c

coc •4-> ro 0 ro -M • 1— S-

+-> CD c > CD

rO 3 ro CD CJ > CD 1

CDQ

C

S_ 3 rO z: ZD

CD 1> TD

CO ro TD S- +-> _Q > C CD ro c O ro E TD CD C •1

E C U

rO TD •r— rO

O CD CD -*-> CD

ZZL z: z: 1— OO CL

CD co

S^- CD

=3

C •«- +J r co O cn Gi- ro 3

i- oco

u_ 1— o o cf—

U1oCd

CD CO I c o

C_J

c/s

CD

CO CO

CD

O 3 LO .— .

cn o o 

*•“ r— >>

4-> C_> ro I o >> C CD co

CDL

O

CD CD f— S~ CO

>- -4-J o

co ro

•r- CG o

CD =5

_£= “O CD

(S) o o oc oo

CVJ OS oo cc

CO

oo

CO

CO

I— oo

COI— CO CO •>

- 13 l/l cn r— CL C =3 DT3 CD o o o

CO

LO

OS

oo o

as

oo

LO

asoo

coo

co co

r-^ r^. oo oo oo o o

co

oo o o o

CO

£=O

ro>

a>CO -QO

CD3

CD3C

fO “O

CD ZI

"O

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co

+-> ro>

CD O

"O

s-ro TDa

ro

-t-> OO

25

Percent

Uncertainty

0.7

2.7-

47.3

37,2
Fatigue

Strength

Young's

Shear

Bulk

Poisson's

Yield

Tensile

10 4

10 5

10 6

10 7

Fracture

Density

Modulus

Modulus

Modulus

Ratio

Strength

Strength

Cycles

Cycles

Cycles

Cycles

Toughness

(lb/in 3)

(10 6

psi)

(10 6

psi)

(10 6

psi )

(10 3

psi)

(10 3

psi )

(10 3

psi)

(10 3

psi

/Tn) >

SCD<D _QO

CC

LO

CD

CO

CD

CD

CD

CO

CD

CO

OOOCXJ

CO

CXI

CO

LOCD

CD

CD

COo

CD

CXJ

CO

C\J

'3" LOO

cooo>

CD CD

TD

S-03 TDC

03

+-> UO

COO

CD

CD

CD

Cxi CD

CD

Cd

Ol<C

CO<C

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s- CDO co

I— o i o

CD

CD LO c o

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CD

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+-> 03

>>

CDi o >> CD

CD

CD

C

C CD CO

CD S_O

I— 4-> r—

UO

v

tl CD 1/1 I— C Q_

CD CD

•I— £- CO

>- -D o 00 i

CD 03

•i- Cd O3 “O LO

COOO

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03 i— Q_

CD 3

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OOO CD

CD CD *i— 3 CD CD >— Q_ C 3 3 “O LO O O O

CD Q

CD

CXJ

LO

‘=d

_

00

CO

4-> 03

_QO

O

00OO

r^>

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CD

CXJ

LOLO

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LO

CD

CD

CXI o

CXJ

CO

CO

LOoLO

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CD

00

CXJ >

CD Q

03 "O

C

CDCJ

SCD Q_

26
TABLE 15

(E).

SUMMARY

OF

PROPERTY

DATA

FOR

TITANIUM

ALLOY

Ti- 6A1- 6V

CO

03 CO U 03 P P x X U 00

03 P M O

Pm

H1

CO

03

O

X i—I o

>.

cj I c

03

D-

•h

m

a

4-»

O >.

03

X o

Pm

CO0) O <—I i—I U

Pn

CJx 03 4—1 i—I 00

•H P

co 03 on P H o 03 4-1 t—I H CO w

T3 00 C/ x p c 0) 0) •h j-i cn

>4 4-1 c

CO r- P o O X

CO 4—1 CO 03 •h p^ o

(X

CO

X P CO

x <—i a *—i p D 03 vO

CQO

O E 1—1

H P

03 P CM X X

CO

OX E Oa

C0 COp

00x P P P P vD O O O

>4 E X

O'*m O'*

cnj a> O'* a^

cO

XXX

r>-

xx on

xxx o m O p

CO •H •H p 4-1 03 o 03 X

•H •H >-( 4-» 03 P > 03

03 P 03 03 CJ > 03 *—1

03

Q P P P 03 E X

03X > X

CO 03

X 3-i

X

X > P 03 03p o 03 g X 03 P •H g P CJ

03

X

X 03 3-1 o 03 03 3-4 X 03 2 E £ H CO PM >

ool oe

co

03 CO P 03

C5 p «—

03

3-i

4-1 C/3

03P

00

•H

X

4-»

C

03 r- Pm PX *r 00 C3 P C o

E—4 on o

>>

CJ

>>

CJo

CJ

CJX -H

03

X CO

i-H 00 CM

•H P

co 03 on P 3-J O

03 4-)X

H CO

w

X 00 CO X p P.

03 03 •H 3m on

>4 4-1

O

C/3 .H P o O X

CO

CO 03 •H PS O

PM

CO

X P CO

x *—i a

rH P P X

X

PQ

O

O E X

CO P P t

03 r-H (J 03 P C X X

CO

OX E c

PICO COp

00

X

p

p P X

X o o o

>4 e x

un

x

mm o

oo

X 03 P

03 P 03 > 03 X 03

3-( P 03 E

03X >

CO 03X

X > P 03 O 03 B P •H E

03X •H o 03 03 3-4 2 E E H

27

Standard

Deviation
TABLE

17(E).

SUMMARY

OF

PROPERTY

DATA

FOR

RESULFURIZED

CARBON

STEEL

C1141

CO L-h CO c

CU CO N. cu CO u CU 5-i cu s. G c •H 35 c

4-1 m3 CO r-H CM i i 1 1 4-1 M3 •rH U 00 cl MO u oo CO

03G cd 33

a

5-i o CO 5-i

O

Ph

H o pH

H ro

i-H

O •N^ i-H

CO co

<u CU

O i-H o 1 i i 1 1 O •—

i—

o i-H CJ 30 >1

CJ CJ

CO CO

X <u M3 cu

4-1 M3 1—

4-1 M3 I-1 00 O u N o 1 i i 1 1 00 o u /-s c -h •H G I-H •H

<U cj CO CU CJ CO u D- 5-4 CL

4-» 4-1 C/3 CO CO CO O o

cu CO i—

cu CO i—

G (U

G cu 00 I—

o 1 i i 1 1 M3 00 1—

•H U0 o i-H •H UO CJ

4-»

O CO 4-1O

03 r-H CJ cd i-1 CJ

P-4 i-J pH WwH

CO

CO CO

cu CO cu

O i-H o 1 i i 1 1 CO o rH

r—l

u

w i-H

U

X

CJ z CJ

hH<H s X •H CO M3 •H

<U 4-J CO (U 4-1 CO

r-H 00 CO- •rH 1—OO CL

•H

g z •HG

CO (U CO '<r uO o uO o> l\ 1 CO cu 03 C 1-1 o i-H CN i-H i—

i-H 5-4

G 5-i o

CU 4-1 1—

r-H i—r-H CJ 0) 4-1 r-H

H CO

w

H CO

M

M3 •H

H M3 /-S

4-1 CO

M 4-1 •rH T3 00 CO- Z X) 00 CO

r-H

g

w i-H c CL

<U (U CO uO Mf UO UO 00

H CU cu •H 5-1 o CO 00 00 i—

r—l CO •H S-I CO

>* 4-1 i-H 33 >*

U o

CO 'w' < CO r-H 03

CO o CO pH c o C o O •H <c o •H

CO 4-1

H CO 4-1 CO cd o 1 1 1 1 1 < CO cd •H P3 Q •H cd O O

P-4

>-• Ch H s Cd •H W

N

CO CO P-4 co •H G CL o 35 CO Md 1—

Cd Pd i-H CL 1—

G M0 o 1 1 1 1 1 P-4 r-H G g 03 o G T3 M3

CQ o i-H Ph CQOO

a o a i—

/^N >* •H pc3 CO CO CO

5-( 3 COa 5-i

G •H

cd i—l

a cd r-H CO

cu 3 MO o 1 1 1 1 1 a (U

G CL

X OU o CO M3 T3 c

O i-H CO O M3 £ a

O

r—1 /~s w

•H

CO CO CO OD CO CO •H - 3 CL CO CO co MT CM i—

- G CO 00 ’—

CM 00 i-H CL c 2 MO on ON ON O i-H W G G G 03 O CN CN CM t-3 33 03 M3 o O i-H CQ O O O a < >-• a i-H H W

co CM CM CM o O ro

4-1 c CO CO 00 -U c

•H •H CN CM CM CM o O •H •H

CO • CO G MO o o o c M3

CU r-H cu 1—

Q Q

>n

(3 4-1 O g

CO •rH •rH C 4-1 cd O cd 4-1 •H •H 5-i 4-1 <u c > CU

cd 35 cd <U CJ > cu r-H cu Q c

5-i

G cd

a 33

CU r-H > 03

CO cd XJ S-i 4-1 X > g CU cd c o cd £ 03 cu G •H £ c a

cd

X •rH cd 5-i o cu (U 5-i 4-1 cu z a a H CO P-.

CO

rH I I CO i—I on I I CM

r—I i—I I I CO

rH I | CO 1—I O'* i i CO

\D <—I uO

O lo o» co cr> O CO vO CT' uo <r co co

uO CO O'' O'* CM CM o o

00

UO

CM

M3 M3

CO

O

r-H CO CO

CM CM

00 00 oo co

CM cm o o

coco

4-1 cu

cd

G > <u rH

5h

G cd

cu i-H >

CO cd M3 > G O cd G •H

cd T3

O cu CU z a a IIIII

CM III

M3UO

28

Trimmed

Mean

0.288

28.3

11.6 -

0.294
TABLE

19(E).

SUMMARY

OF

PROPERTY

DATA

FOR

IRON

BASED

SUPERALLOY

A286

CO 1 c z-\

G CO l-H CO 1 c G 0) S. G CO 1-H G G G s.

4-> rG •H CO r-* LO C" Of CO

G

G

a 00

G <r of CO CM 4—* J3 •H CJ\ LO '—1 O

G

G CL i—i

r—1 1—1 a oo

G CM

O

G

O CO 3 cl CM CT\ CO co CO H CO G O <r CO rH o Cu H CO

i-H o s—' i—i s-/

CO

cu CO

O 1—1 G o CM i—l i-H 1—1

Of M3

O i—(

30 vO vO i—i a rH rH 1 i 1 1 CJ Jo rH

CJ i—1

CO

x cu

G

4-1 lo r—1

rGG

60

O

u /—s

4-J M3 rH

g r—1

30 •H r>- 1—1 LO 00 o a —> CM CT\ <r CO

G CJ

G iO M3 LO i—1 CM

C '—I JO •H rH i—i i—i g CL G CJ G i—1 i—i i

i 4-1 G CL CO CO 4-J O CO CO G CO t—1 O G <u G G rH

60 i-H

G

G

•H

m

a 00 rH

4-J o Jo CO i—1 CO

O 00 •H lo CJ CM Mt <r CO

G i—i a 00 r>. CM CM 4-J

O JO Mt mj- rH

PL

G rH CJ

Cu i—1 i—i

rH

CO

cu

O

G o i—i

CM iO LO LO in r"> Mf

G <—i

CJ r^» r- CO Of i O rH CM CT* i—1

rH 1 rH a oCJ

CU00

JO CJ

rH i—l i—i

0) rG

4-J •HG

i—l WW

rG •H

00 CL vO u0 CM <f <f

O

G 4->G

G 00 Of LO <f <r CO rH 00 CL LO On Mf O-

(0 0) CO i—1 1—1

i—i

CO

•h

n a> co Mt CO CM

G

G o G

G CO CO CO CO

CL) 4-J 1—1 O

C

G

O

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29
TABLE

21

(E)

SUMMARY

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IRON

BASED

SUPERALLOY

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30

Standard

Deviation
TABLE 23. FOR STAINLESS STEEL 316, COMPARISON OF PRESENT RESULTS WITH

TWO OTHER VARIABILITY STUDIES.

Here There Ratio

3 Density (g/cm ) 7.971 7.958 1.002

Young's Modulus (GPa) 195.1 194.6 1 .003

Shear Modulus (GPa) 79.9 75.2 1.060

Bulk Modulus (GPa) 177.9 157.5 1.130

Poisson's Ratio 0.294 0.294 1.000

Yield Strength (MPa) 297 227 1.308

Tensile Strength (MPa) 627 583 1.075

Represents a single value.

Appendix 1. Physical and Mechanical Properties of Technological

Alloys: A Data-Source Bibliography

Everhart, J. L, Lindlieff. W. E., Kanegio, J., Weissler. P. G., and

Siegel. F'., Mechanical Properties of Metals anti Alloys. NBS Circular C447 (U.S. Govt. Print. Off., Washington, DC, 1943). Hoyt, S. L., Meta I Data (Reinhold, New York. 1952). Pagonis, G. A., The Light Metals Handbook (Van Nostrand, Toronto,

1954).

Smithells, C. J.. Metals Reference Rook. Volumes 1-2 (lnterscienee. New

York, 1955).

Farr, A. L., and Osborn. J. M., Properties of metallic materials at low

temperatures. Unpublished study. The Engineer Center and Fort Belvoir Engineer Research and Development Laboratories, Corps of Engineers, U.S. Army (1956).

Materials property manual and summary report. North American

Aviation report AE-2604 (Oct. 1957). AGARD Material Properties Handbook. Volumes 1-3 (The Royal

Aeronautical Society, London, 1959). Durham. T. F., MeClintoek. R. M., and Reed, R. P., Cryogenic

Materials Data Handbook. Volumes 1-2 (U.S. Department of Commerce, National Bureau of Standards, Boulder, CO, 1960). MeClintoek, R. M., and Gibbons, H. P., Mechanical Properties of

Structural Materials at Low Temperatures. NBS Monograph 13 (U.S. Govt. Print. Off., Washington, DC, 1960). Lyman, T. (editor). Metals Handbook. Volume 1. Properties and Selection of Metals (Amer. Soc. for Metals, Novelty, OH, 1961). Midgley, P., and Thomas, D. E., The mechanical properties of metals at cryogenic temperatures. Rocket Propulsion Establishment, Westcott, England, Tech. Memo. No. 237 (Oct. 1961). Warren, K. A., and Reed, R. P., Tensile and Impact Properties of

Selected Materials from 20 to 300 °K, NBS Monograph 63 (U.S. Govt. Print. Off., Washington, D.C., 1963). Schwartzberg. F. R., Osgood, S. H., Keys, R. D., and Kiefer, T. F., Cryogenic Materials Data Handbook. Volumes 1-2 (Air Force

Materials Laboratory, Wright-Patterson Air Force Base, OH. 1964). Available from N ITS, order numbers AD713619, AD713620.

Materials Properties Data Book, NERVA Program Report 2275 (Aerojet Nuclear Systems Co., Sacramento, CA, 1970). Wood, R. A., and Favor, R. J., Titanium Alloys Handbook (Battelle Metals and Ceramics Information Center. Columbus, OH, 1972). Available from N ITS, order number AD758335.

Damage Tolerant Design Handbook (Battelle Metals and Ceramics Infor- mation Center, Columbus, OH. 1973). Woldman, N. FT, and Gibbons, R. C., Engineering Alloys (Van

Nostrand Reinhold, New York, 1973). Aluminum Standards and Data 1974-75 (The Aluminum Assoc., New

York, 1974). Matthews, W. T., Typical plane strain fracture toughness of aircraft materials, in Liebowitz, H. (editor), Eracture Mechanics of Aircraft

Structures, AGARDograph No. 176 (North Atlantic Treaty Organization, 1974), [ip. 509-579. Available from NT1S, order number

AD777641

.

Military Standardization Handbook. Metallic Materials and Elements for

Aerospace Vehicle Structures, MIL-HDBK-5B (U.S. Dept, of Defense, Washington, DC, 1975).

Deel, 0. L., Ruff, P. E., and Mindlin, H.. Engineering data on new

aerospace structural materials, Battelle Columbus Laboratories

report AF'ML-TR-75-97 (June 1975), 267 pp. Lynch, C. T. (editor). Handbook of Materials Science. Volume 2: Metals. Composites, and Refractory Materials (CRC Press, Cleveland, OH,

1975). Handbook on Materials for Superconducting Machinery (Battelle Metals and Ceramics Information Center, Columbus, OH, 1977). Moore, T. D. (editor). Structural Alloys Handbook. Volumes 1-2 (Mechanical Properties Data Center. Traverse City, Ml, 1977). Wolf, J. (editor). Aerospace Structural Metals Handbook (Mechanical

Properties Data Center, Traverse City, ML 1977).

31
Material:

Appendix 2.

Composition (Pet.): Min. Avg. Max. Element Wt. At.

Thermal—Mechanical Treatment:

Form:

Mass Density e/cm3 lb/in 3 Comments:

Young’s Modulus GPa 106 psi

Shear Modulus GPa 1

6 psi

Bulk Modulus GPa 1

6 psi

Poisson’s Ratio

Yield Strength MPa ksi

Ultimate Strength MPa ksi

Fatigue Strength MPa ksi cycles

Fracture Toughness MPa\/m ksi\Tn

Creep Strength MPa ksi strain hours

Source:

Compiler: Date:

32
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1. PUBLICATION OR

REPORT NO. NSRDS-NBS 61, Part V

2. Performing Organ. Report No. 3. Publication Date January 1982

4. TITLE AND SUBTITLE

Physical Properties Data Compilations Relevant to Energy Storage. V. Mechanical Properties Data on Alloys for Use in Flywheels

5. AUTHOR(S)

H. M. Ledbetter

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complexity from simple carbon steels to superalloys. Properties include: mass

density, Young's modulus, shear modulus, bulk modulus, Poisson's ratio, yield

strength, ultimate strength, fatigue strength, fracture toughness, and creep strength.

Property values were collected from many types of sources and were analyzed statistically to detect possible outlying values. For each alloy, the report contains typical

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