national Bureau of Standards

Library, N.W. Bldg

JUL 1 1 1963

NBS MONOGRAPH 63

Tensile and Impact Properties of

Selected Materials From 20 to 300

U.S. DEPARTMENT OF COMMERCE

NATIONAL BUREAU OF STANDARDS
THE NATIONAL BUREAU OF STANDARDS

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Documents, Government Printing Office, Washington 25, D.C.
UNITED STATES DEPARTMENT OF COMMERCE • Luther H. Hodges, Secretary

NATIONAL BUREAU OF STANDARDS • A. V. Astin, Director

Tensile and Impact Properties of

Selected Materials From 20 to 300 °K

K. A. Warren and R. P. Reed

National Bureau of Standards Monograph 63

Issued June 28, 1963

For sale by the Superintendent of Documents, U.S. Government Printing Office Washington 25, D.C. - Price 35 cents
Library of Congress Catalog Card Number: 63-60026
Contents

Page

Introduction 1 Equipment 1 Specimens 2

Experimental procedure 2 Reduction of data 3 Results 3

References 3 Data (tables I to VII) 4

Tensile properties (figures 1 to 6) 26

Impact properties (figures 7 to 13) 30

Identification table (table 8) 36

Specimen designs (figures 14 to 30) 37

m

Tensile and Impact Properties of Selected Materials from 20 to 300 °K

K. A. Warren* and R. P. Reed

The tensile and impact properties of structural materials were experimentally de- termined at temperatures from 20 to 300 °K. Tensile properties of a few materials were

also determined at 4 °K. The materials included forty-two commercial alloys of iron, alu- minum, titanium, copper, nickel, and cobalt, and two metal-bonded carbides. The properties experimentally determined were the yield strength, tensile strength, elongation, and

reduction of area, the stress versus strain curve, and the impact energy. The test equipment and procedures are described. The individual data are presented in tables, and the average results are displayed in graphs.

Introduction

There has been a lack of information on the

low-temperature mechanical and physical properties of certain materials that might be used in cryogenic devices. Even where data existed,

they were not always available in convenient

form. Also the designer was sometimes faced

with the necessity of choosing between conflicting

data.

In order to remedy these problems insofar as certain missUe applications were concerned, the

Cryogenic Engineering Laboratory of the Bureau

was requested by the Air Force Ballistic Missile

Division to search the literature published between 1940 and 1960 for pertinent mechanical and

physical properties data on selected materials at low temperatures, to evaluate these data, and to supplement them with experimental measure- ments at room and low temperatures where

deemed advisable. This program was initiated

early in 1959 under Air Force Contract Number

AF 04(647)-59-3. It led to preparation of a Cryogenic Materials Data Handbook which had

a limited distribution to the Air Force and some

of its contractors. This Monograph is presented to provide more

detailed documentation of the experimental portion of the program and to make the results more

generally available. Included are tensile strength,

yield strength, elongation, and reduction of area

values, stress-strain curves, and impact data for

alloys of aluminum, cobalt, copper, iron, nickel,

and titanium, and two metal-bonded carbides.

Only one condition of each material was tested

(except for beryllium copper). The condition

selected was the one thought to be the most useful

for low temperature missile applications. The

materials were tested at four temperatures: 300 °K

(room), 195 °K (dry ice and alcohol), 76 °K

(boiling liquid nitrogen), and 20 °K (boiling

liquid hydrogen). A few results are reported for

tests made at 4 °K (boiling Hquid helium).

•Present address: Granville-Phillips Co., Boulder, Colo.

Equipment

To implement the testing program a tensUe

cryostat, which has been described in the literature

[ly, was designed and built. This cryostat is capable of transmitting tensUe forces up to a max-imum of 5,000 pounds. This load limit influ- enced the specimen design as wUl be subsequently

described. Later in the program another cryostat

[2], of a different design and capable of sustaining

tensUe forces of more than 10,000 pounds, was

designed and built for another project. This

cyrostat was also used, and its use significantly

accelerated the experimental program.

The tensUe tests were performed using two

universal testing machines, one a 60,000 pound

hydraulic machine, the other a 10,000 pound

mechanical machine. Both machines were equipped with 10,000 pound load cells. The load

versus extension curve was plotted automatically on an x-y recorder. The recorders used were equipped with tune plotting devices for the x axis so that load versus crosshead travel (time) could

be recorded after the limit of travel of the

extensometer was reached.

Nearly all of the specimens were equipped during

testing with an extensometer to allow an accurate determination of yield strength and stress versus

strain. Three types of extensometers were available. Initially a commercial clip-on strain gage

extensometer buUt for 1-inch gage length was used.

Because of the desirability of conforming to the

convention that the initial gage length should

equal four times the diameter of the specimen,

two strain-gage type extensometers meeting this

requirement were developed (fig. 1) that fit respectively the two principal types of specimens.

At the same time it proved possible to greatly

extend the strain range, inasmuch as the commercial extensometer had only utilized a small

portion of the elastic region of the strain gages

and beams. By using a difterent method of trans- mitting the strain of the specimen to the strain

1 Figures In brackets indicate the Uterature references on page 3.

1
gage sensing elements of the extensometer, the

full elastic region was utilized. In this method

the knife edges are attached rigidly to the ends

of thin beams on which are mounted the strain gages. As the specimen extends, the knife edges

rotate about the contact points where they grip

the specimen. Wlaereas the commercial exten- someter was Imiited to measuring only slightly over 10 percent elongation, the new extensometers

are linear and reproducible up to about 85 percent

elongation. The strain sensitivities are about

the same. A simple cryostat was built for calibration of

the extensometers at cryogenic temperatures.

It consisted of a commercially available stainless

steel widemouth Dewar with a cover fabricated

mainly from plastic components and provided

with suitable fittings, such as electrical connector,

vent tube, fill tube, and calibration extension

member tube, all with seals to permit use with

liquid hydrogen.

The extensometers were calibrated prior to the

tests by mounting them on a calibration device

incorporating a precision micrometer accurate to 1X10"^ inches over a 2 inch range. The motion

of the micrometer was transmitted into the cali- bration cryostat by stainless steel extension members. For low temperature calibrations the ex- tensometer was immersed in an appropriate

cryogen in the calibration cryostat. The decrease

in sensitivity of the extensometers in going from room temperature to liquid hydrogen temperature was about 8 percent. This figure varied slightly

with changes in, or replacements of, the strain

gage transducing elements of the extensometers.

A measuring microscope was used for determining the initial and final gage lengths needed for calculation of percent elongation values. The

specimen diameters were measured with a precision micrometer.

The impact measurements were conducted

using a standard impact testing machine with a

15 or 30 pound hammer, and a drop in height of

the hammer of 2 or 4 feet. The resulting velocity

at impact is 11.3 or 16.0 feet per second.

Specimens

Because of the limited load capacity of the first tensile cryostat, as mentioned earlier, it was

necessary to use subsize tensUe specimens, since

the tensile strengths of some of the materials were expected to approach 300,000 psi and many

would approach 200,000 psi at low temperatures.

Thus, these two strength values and the 5000

pound load limit were used as a basis for determining two tensile specimen designs which incorporated nominal reduced section diameters of 0.144

inches and 0.177 inches respectively (fig. 2).

Selection of the particular diameter to be used

for each material was based on its expected

maximum tensile strength at low temperatures.

Exceptions to these standard specimen designs were the ElgUoy and 301 XFH specimens.

Initial tests of Elgiloy showed it to be considerably

stronger than anticipated at low temperatures;

thus a reduced section diameter of 0.125 inch was used. Since the 301 XFH stainless steel was available only in sheet form, flat tensile

specimens 0.040 inch thick were used for this ' material (fig. 2). The reduced section of each specimen was

tapered slightly toward the center (by about 0.003 - inch on the diameter or width) in an attempt to : prevent the occurrence of fractures outside the

gage length markings. A tolerance of ±0.1 inch was placed on the axial location of the minimum

diameter. Very short and shallow gage length ; marks were put on each specimen using a carbide

scribe and a guide. Measuring reference points were indicated with short marks applied normal

to and across the gage marks. The tolerance on

coaxiality of thread axis and reduced section axis was set at 0.0002 inch. This close tolerance was , provided to reduce the effects of eccentricity which i would be accentuated by the smallness of the , | specimens. | The impact specimen designs were standard i Charpy U, Charpy V, and subsize (}0 Charpy V j

'

(fig. 2) . Subsize specimens were used for materials '' 1 which exhibited an impact strength greater than , ( 110 foot-pounds or which did not completely r fracture during preliminary tests with standard i t size specimens. The notch contour of the speci- o mens was checked using an optical comparator. j The tolerances of the notch radius, specimen Avidth, |( and specimen thickness from the bottom of the j notch to the opposite side were ±0.001 inch.

It was necessary to heat treat some of the materials (A286, 17-4PH, 17-7PH, 1075, Unimach #1)

before specimen manufacture. The data spread

which occurred in some of these materials can Jj

|" probably be attributed to variations in microj structure that were found to exist. The condition ^ " of each material is recorded in table I. !^

If Hi Experimental Procedure ' *

3 tfi The extensometer was mounted on the specimen, i )[ and the specimen placed in the cryostat. Parts i

if, of the cryostat were then installed in their respec-? d tive locations, all electrical and mechanical con- 1 Ik, nections were made and checked, and the cryostat % was filled with refrigerant if a low temperature run |j jjj was to be made. In using liquid hydrogen, suit-? jo, able safety precautions were observed [3]. WithS ^

solid C02-etliyl alcohol mixtures, the temperature 5 ^^ was checked with a liquid-in-glass thermometer, s Nearly all tensile tests were run with a crossheado

velocity of 0.02 inch per minute. Exceptions to f this are indicated. ! I) After fracture, the broken specimen was as-ii |

sembled in a holder, and the final gage length

| ^

was determined with the measuring microscope.] j An avera.ge was taken of two traverses made ini; opposite directions. Final diameter determina-t ^, tions were made by using another fixture and theit precision hand micrometer. Because neckingj; (||,

i
occurred in most materials, inch diameter wires were placed between the specimen and the

micrometer spindle and anvil to obtain a reliable

reduced-diameter measurement.

The extensometers were calibrated periodically

at all test temperatures to ensure accuracy of strain measurement recording. Also they were

always calibrated after replacing component parts

such as beams and strain gages. For the commercial extensometer it was often necessary to sharpen the knife edges; this change had little effect on the calibration of the extensometer.

The impact tests were conducted with the aid

of a combination specimen aliner and holder

which could be inserted while containing the

specimen into a refrigerant bath and cooled down

to the test temperature. This cool down took

place quite rapidly, but extra time at temperature was allowed before removing the specimen from

j the bath. The transfer from the bath to the

I impact machine was made within 3 seconds. As

the holding fixture was withdrawn it positioned

I the specimen properly in the supports. Immedi-

' ately thereafter the hammer was allowed to drop.

The liquid hydrogen tests on the subsize Charpy

' V specimens were performed in the same manner

except that the tests were conducted outdoors for reasons of safety. Paper boats were glued to

! these specimens prior to the tests for the purpose

t of retaining the liquid hydrogen around the speci-

'i men until fracture. Without the paper boats the

i temperatm-e rise of the specimens prior to fracture

would have been about 30 degrees K.

Reduction of Data

I The tensile strength values were computed by

' dividing the maximum load sustained by the

I specimen by its initial minimum cross-sectional

' area. All yield-strength values were obtained by

'i using the 0.2 percent offset method. In a few

I instances where the initial portion of the stress-

; strain curve was distorted due to back lash in the

I recording system, an accurate value of the modulus

of elasticity, when known for the particular mail terial at the particular temperature, was used in

j conjuction with the extensometer calibration to locate the 0.2 percent offset point on the curve.

;l The yield strength values were computed by

I I dividing the yield load by the initial minimum

I cross-sectional area. The stress-strain curves in

(i figures 3 to 30 were derived from the continuously

!1|

recorded load versus strain and crosshead extenI sion plots and were adjusted to the average values

' of yield strength, tensile strength, and elongation,

j The percent elongation values are based on a 4D gage length. The one exception to this is the

301 XFH stainless steel for which a 1-inch gage

ii| length was used.

]j For high elongation materials it was often

i; necessary to switch to a crosshead movement

- measurement system before fracture occurred, due

nfi! to the limited travel of the extensometers. The

J

|i effective gage length was somewhat indefinite for

I

this portion of the stress-strain curve. For this reason some of the tabulated elongations do not

agree exactly with those that might be calculated

from the stress-strain diagrams. The latter should

be given no weight.

Careful consideration was given to data ac- curacy. Stress data are reported to 4 place ac- curacy and elongation and I'eduction of area data

are reported to 3 places. When experimental

results occurred whicii could be attributed to a

variation in experimental procedure (sucli as fracturing on the gage length marlcing) the results were not reported. The authors conclude that

the reason for the data spread is specimen material

inconsistency, not experimental technique.

The averages of the impact energies in some

cases include both "high drop" and "low drop"

readings. However the results are not indexed

as to heiglit of drop inasmuch as no significant

effect due to this variable was found. In cases where a large spread in the impact data exists, this can again be partially attributed to variations

of microstructure. Where fracture was incomplete the percent fracture reported in the impact

results is an approximate figure based on visual

estimation of the fracture surfaces of the speci- mens which had been tested. The energy absorbed

values are reported to the nearest 0.5 foot-pound

of energy in tables II-VIII. Results

The results of the tests performed on individu al specimens are reported and averaged in tables II-VIII. The material condition and tensile

specimen configuration (with reference to fig. 2) are noted in the "Material" column.

Figures 3 through 30 sliow typical stress-strain curves, the temperature dependences of the aver- age tensile properties, and the average values of

impact energy absorbed for each material. Chemical composition, condition, grain size, and roomtemperature hardness for each material are listed

in table I.

The authors acknowledge the assistance of the

following who contributed to the experimental

program: R. P. Mikesell, R. M. McClintock, T.

F. Durham, C. J. Guntner, R. L. Greeson, G. W.

Pickering, F. M. Reames, H. P. Gibbons, and

many others. Of particular help in preparation

of this Monograph was Mrs. C. J. Dallman, who

did the typing.

References

[1] R. M. McClintock and K. A. Warren, Tensile cryostat

for the temperature range 4 to 300 °K, Materials Research and Standards, ASTM Bulletin, V. 1, $2,

p. 95-98 (1961).

[2] R. P. Reed, A cryostat for tensile tests in the temperature range 300 to 4 °K, Advances in Cryogenic

Engineering, V. 7, paper K-3, p. 448-454, (Plenum

Press, 1961).

[3] D. Chelton, Safety in the use of liquid hydrogen. The

Technology and Use of Liquid Hydrogen, Editors

W. H. Denton, R. B. Scott, and C. M. Nicholls (Pergamon Press, London, to be published).

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TABLE II ALUMINUM ALLOYS

MATERIAL

Test Temp

°K

Room

195 TENS 50

Sand Cast T6

Specimen

Type A

76

20

TENSILE PROPERTIES

Crosshead

Velocity

in/min

Tensile

Strength

psi

Yield Strength

(0.2% offset) psi

Elongation Reduction

of Area % in 4D %

0. 01

0. 01

0. 01

0. 01

0, 01

44, 200

41, 100

40, 400

39, 300

42, 500

42, 400

31, 500

32, 200 32,200

33,200

33, 000

4. 3

3. 3

5. 5

8. 7

9. 8

9. 7

9. 7

avg 41 , 600 32, 400 4. 4

0. 01

0. 01 0.01

43, 000

43, 100

47, 200

35, 400

37, 800

3. 4

3. 9

4. 8

5. 9

10. 8

avg 44, 400 36, 600 4. 0

0. 01

0. 01

0. 01

0. 01

55, 400

52, ,100 46, 300

53, 400

47, 600

45, 000

51, 000

50, 200

51, 300

38, 300

38, 800

39, 400

38, 300

35, 700

6. 2

3. 6

2. 5

1. 4

3. 1 2. 4

2. 4

9. 1 6. 9

7. 1 6. 7 avg 50, 300 38, 100 3. 1 6, 4

0.01

0.01

55, 900

57, 000

43, 600

44, 600

2. 6

3. 0

4. 4

5. 1 avg 56, 400 44, 100 4. 8

IMPACT PROPERTIES

Energy

Absorbed

ft-lb

Charpy FVacture Geometry Area

2.5

2.5

2. 5

2. 5

2. 5 2. 5

2. 5

2. 5

2. 5

2. 0 1.0

1.5

1. 5

1. 5

1 . 5

100

100

0. 02

0. 02

0. 02

40, 500

36, 500

36, 100

28, 700

23, 300

22, 700

10. 7 12. 0

15. 8

11.8

13. 6

18. 4 avg 37, 700 24, 900 12. I 14. 6

195

0. 02

0. 02

0. 02

39, 300

38, 200

38, 300

24, 700

24, 800

12. 3

11.7

12, 5

13. 4

356

Cast T6

Specimen

Type A

avg 38, 600 24, 800 12. 0 13. 0

76

0. 02

0. 02

0. 02

48, 800

48, 600

47, 000

28, 400

25, 800

27, 100

11.1

10. 0

11.6

12. 3

9. 6

avg 48, 100 27, 100 10. 6 11.2

20

0. 02

0. 02 avg

60, 700

60, 400

60, 600

35, 600

33, 200

34, 400

7. 2 10. 9

9. 0

6. 9 U. 2

9. 0

2. 0

2, 0

2. 0

2. 0

2. 0

3. 5

2. 5 2. 0

2. 0

2. 5

2. 5

2. 5

1. 5

2. 5

2. 5

100

100

T
TABLE II ALUMINUM ALLOYS (Continued)

Test Temp

MATERIAL

°K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min , psi psi % in 4D %

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft -lb %

Room

0.02 13,500 7,400 46.8 88.8

0.02 13.400 6,900 44.1 86.8

0.02 13,500 6,500 46.7 89.7

23. 0 22. 5 23. 0 avg 13,500 6,900 45.9 88.4 23. 0 1/2 V 50

195

1100

0. 02 16, 100 7, 300 47. 4 85, 6 0.02 16,900 --- ---

0. 02 16, 500 7, 100 52. 5 85. 7

27. 5 29. 0 28. 0 avg 16, 500 7, 200 50. 0 85. 6 28. 0 1/2 V 50

0 76 Specimen

Type A

0. 02 27, 800 55. 8 81.6

0.02 27,900 9,100 57.0 82.2

0.02 27,300 8,900 --- 79.7

35. 5 36. 5

33. 5 avg 27,700 9,000 56.4 81.2 35. 0 1/2 V 50

20 0.02 47,400 9,600 52.6 57.80. 02 47, 700 9, 300 55. 7 62. I 33.5 31.5

30, 0 avg 47,600 9,400 54.2 60.0 31.5 1/2 V 75

Room

0.02 83,400 74,900 9.9 16.4

0. 02 82, 600 74, 100 9.8 16. 6 0.02 82,000 73,400 10.4 16.8

1.5

1. 5 1.5 avg 82,700 74,100 10.0 16.6 1.5 V 100

195 2020

T6

0. 02 89, 400 78, 100 6. 9 8.8

0. 02 90, 200 79, 600 6. 5 7. 5

1. 5

1. 5

1. 5 avg 89,800 78,800 6.7 8.2 1.5 V 100

Specimen , i 6 Type A

0.02 99,300 86,800 5.3 6.2 0.02 99,400 87,300 5.2 6.6

1. 5

1. 5

1. 5 avg 99,400 87,000 5.2 6.4 1.5 V 100

20 0.02 110,300 93,300 7.3 9.0 0.02 108,600 92,400 7.9 10.2 avg 109, 400 92, 800 7. 6 9. 6

Room

0. 02 74, 300 9.9 25. 7 0.02 73,900 71,600 9.4 26.5

0.02 74,300 71,500 9.5 26.8

0.02 --- --- 9.3 27.3

3. 5

3. 0

3. 5

3. 0 avg 74, 200 71 , 600 9. 5 26. 6 3. 5 V 100

195 2024

0. 02 79, 900 76, 500 9. 6 24. 1 0. 02 80, 100 76, 100 9. 1 22. 3

3. 0

3. 0

3. 0

3. 0 avg 80,000 76,300 9.4 23.2 3.0 V 100 T86

Specimen 76 Type A

0.02 91,100 85,500 10.8 20.8

0.02 92,400 85,700 10.6 21.9

3. 5

3. 5

3. 5 avg 91,800 85,600 10.7 21.4 3. 5 V 100

20 0.02 104,400 93,000 14.6 25.80.02 105,400 93,300 15.6 23.1 avg 104,900 93,200 15.1 24.4

8
TABLE II ALUMINUM ALLOYS (Continued)

TENSILE PROPERTIES IMPACT PROPERTIES

MATERIAL

Test TempCrosshead

Velocity Tensile

Strength

Yield

Strength (0.2% offset)

Elongation Reduction

of Area Lnergy Cnarpy fVacture Absorbed Geometry Area

°K in/min psi psi % in 4D % ft -lb %

0. 02 44, 600 39, 300 18. 5 56 3 1 6. 0 Room 0. 02 44, 200 39, 200 17. 7 55 7 16. 0 avg 44, 400 39, 200 18. 1 56 0 16.0 V 100

0.02 48, 600 42, 100 19. 4 54 2 1 6. 0 195 0. 02 48, 600 42, 100 19. 8 54 0 1 6. 0 6061 16. 0

T6

avg 48, 600 42 1 00 19. b 54. 1 16.0 V 100

0. 02 59, 900 47, 900 24. 7 51

4 1 6. 5 Specimen 0. 02 59, 700 47, 700 24. 2 51. 0 16. 0 Type A 7 A lb. 0

17. 0

16. 5 avg 59, 800 47, 800 24. 4 51. 2 16. 5 V 100

0. 02 75, 400 51, 700 29. 4 45. 8 20 0. 02 76, 000 51, 900 30. 2 43. 4 avg 75, 800 51, 800 29. 8 44. 6

0. 02 80, 600 72, 100 15. 3 35. 8 Room 0. 02 82, 100 73, 900 15. 2 34. 6

0. 02 . 81 , 800 15. 3 34. 3 avg 81, 500 73, 000 15. 3 34. 9

0. 02 87, 200 79, 000 14. 4 27. 7

7075

195 0 02 87, 800 78, 900 13. 9 27. 2 avg 87, 500 79, 000 14. 2 27. 4 T6

0. 02 99, 700 89, 700 14. 2 24. 2 Specimen 76 0. 02 99, 400 89, 300 14. 9 24. 6 Type A avg 99, 600 89, 500 14. 6 24. 4

0. 02 115, 000 97, 900 15. 2 21. 3 20 0. 02 115, 700 101, 400 15. 0 21. 4 avg 115, 400 99, 600 15. 1 21. 4

9
TABLE III COBALT ALLOYS

Test Temp

MATERIAL

°K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min psi psi % in 4D %

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft -lb %

Room

0.02 245,700 209,200 12.0 47.2 0.02 251,000 210,000 10.4 45.7 avg 248,400 209,600 11.2 46.4

195 ELGILOY

0.02 271,400 2 10,800 1 1.7 44.6

0.02 271,700 213,500 13.2 44.1 avg 271,600 212,200 12.4 44.4

Cold reduced 46%

Specimen

0.02 32 1,700 251,500 14.7 32.8

0.02 326,000 255,600 14.5 34.7 avg 323,800 253,600 14.6 33.8 Type C

20 U.U2 362, 3UU Zo4,UUU D.4 32. 3 0.02 361,300 278,900 7.0 30.4

avg 361,800 281,400 6.7 31.4

0, 5 1.0

1 0

0. 5 1.0 avg 1.0 V 100 STELLITE 3

Sand Cast 195

0. 5

0. 5

0. 5 avg 0.5 V 100

76

0. 5

0. 5

0. 5 avg 0.5 V 100

' Room

STELLITE 25

35.0

38.0

37. 0 avg 36. 5 U 100 Cold reduced

2 6%

195

31 5 33. 0 33. 0 avg 32. 5 U 100

76

22. 5 25. 0 23. 0 avg 23. 5 U 100

10
TABLE IV COPPER ALLOYS

Test Temp

MATERIAL

°K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min psi psi % in 4D %

IMPACT PROPERTIES

Energy Charpy FVacture Absorbed Geometry Area

ft -lb %

Room

0.02 69,200 26,900 62.4 79.7 0.02 70,600 27,800 62.9 79.4

102. 0 101. 5 103. 5 avg 69,900 27,400 62.6 79.6 102.5 U 50

195 BERYLCO 25

0.02 74,700 34,500 68.9 77.6 0.02 75,100 34,900 69.0 80.5

90. 5 103. 0 103. 5 97. 5 avg 74,900 34,700 69.0 79.0 98. 5 U 50 Annealed

Specimen 76 Type A

0.02 98,900 49,700 72.8 75.7

0.02 99,200 49,200 66.7 69.9

83. 5 86. 5 90. 0 avg 99,000 49,400 69.8 72.8 8 6.5 U 7 5

20

\J , \J C 1 1 1 , 7 KJ \J DO , DKjyj O7.7 il.v 0.02 116,600 57,800 68.1 68.5 avg 117.200 58,200 69.0 69.8

Room

BERYLCO 25

0. 02 101, 800 96, 100 19. 6 68. 0 0.02 101,700 97,200 18.8 68.0

37. 5 36.5

39. 0 avg 101,800 96,700 19.2 68.0 37.5 U 75 Hard

Specimen

Type A

0.02 107,700 99,200 23.7 69.6

0.02 109,200 101,000 22.1 70.1

39.5

42. 0 38. 0 avg 108,400 100,100 22.9 69.8 40.0 U 7 5

76 0.02 131,000 120,300 31.5 66.1 0.02 132,800 117,200 30.5 65.8

34. 0 35. 0

35. 0 avg 131,900 118,800 31.0 66.0 34. 5 u 100

20 0.02 153,700 1 17,900 31.4 60.0 0.02 153,800 120,200 31.4 60.0 avg 153,800 1 19,000 31.4 60.0

11
TABLE IV COPPER ALLOYS (Continued)

TENSILE PROPERTIES IMPACT PROPERTIES

Test Crosshead Tensile Yield Elongation Reduction Energy Charpy R-acture Temp Velocity Strength Strength of Area Absorbed Geometry Area MATERIAL (0.2% offset) "K in/min psi psi % in 4D % ft -lb 0770

0. 02 96, 100 66, 400 14. 2 58 3 14. 0

0. 02 95, 100 57, 300 14. 2 58. 2 14. 0 Room 0.02 0.05

94, 900

94, 600

58, 900 14. Z 58 4 15. 5 18. 0 avg 95, 200 60, 900 1 4. 2 58 3 1 5. 5 V 100

0. 02 100, 700 60, 400 1 6. 6 62 8 1 5. 5

0. 02 100, 800 68, 500 16. 8 61 6 15.5 195 0. 02 100, 700 63, 500 18. 2 63. 3 16. 0 0.02 100, 500 64, 100 17. 9 61 2 101 , 400 65, 100 17. 2 62 4 70/30 BRASS

avg 100, 800 64, 300 1 7. 3 62 3 15. 5 V 100 3/4 Hard

0. 02 1 18, 500 70, 400 27. 6 63 0 1 5. 0 Specimen

Type A

0. 02 115,400 66, 800 29. 1 63 8 14.5

18.5

15.5

14.0 avg 1 17, 000 68, 600 28. 4 63 4 15.5 V 100

0. 02 133, 200 74, 200 32. 4 58 5 20 0. 02 131, 800 72 , 600 32 . 1 58 0 avg 132, 500 73, 400 32. 2 58, 2

0. 02 31, 800 10, 700 54. 2 85. 1 52. 5 0. 02 31, 900 10, 800 53. 4 87. 7 52. 0 B oom 0. 2 32, 500 10, 500 53. 0

0 . 2 32, 500 10, 600 85. 4

0 . 2 32, 500 12, 000 86. 5 avg 32, 200 10, 900 53. 8 86. 2 52. 5 1/2 V 25

0. 02 38, 500 10, 300 53. 1 83. 8 57. 0

0. 02 39, 200 9, 200 53. 3 84. 0 56. 5 195 0. 2 39, 800 14, 600 84. 3 57. 5 0 . 2 39. 400 11, 100 OFHC

0 . 2 38, 800 12, 700 85. 7 avg - 39, 100 11, 600 53. 2 84. 5 57. 0 1/2 V 25

Soft

0. 02 51, 500 13, 100 59. 8 82. 6 67.0 Specimen

Type A

0. 02 51 , 100 10, 100 60. 8 85. 4 62. 0

0. 02

0. 2 0 , 2 0 . 2

52, 300

52, 500

52, 700

53, 100

15, 600

12, 300

12, 800

59. 7 85. 84.

82.

6

3

8

66. 5

avg 52, 200 12 800 60. 1 84. 1 65. 5 1/2 V 25

0. 02 59, 400 1 4, 900 70. 7 83. 4 64. 0

0. 02 59, 900 10, 200 67. 8 83. 8 62. 5 20 0. 02 61, 300 10, 800 68. 1 64. 5

0. 2 61, 800 13, 500 82. 6

0. 2 61, 000 15, 900 82. 3 avg 60, 700 13, 100 68. 9 83. 0 63. 5 1/2 V 25

12
TABLE V IRON ALLOYS

Test Temp

MATERIAL

Room

195

INVAR 36

12-15% Cold drawn

Specimen

Type A

76

20

TENSILE PROPERTIES

Crosshead Tensile Yield Velocity Strength Strength (0.2% offset) in/min psi psi

Elongation Reduction

of Area % in 4D %

0. 01

0. 01

0. 01

0. 01

0. 05

93, 600

94, 400

93, 900

93, 200

95, 400

90, 100

91, 500

91, 900

89, 900

92, 100

21.5

19. 5 21.5

61. 6 62. 4

62. 1 61. 1

avg 94, 100 91, 100 20. 8 61. 8

0. 01 0.01

0. 01

0. 01

0. 01

0. 02

0. 02

111, 900

115, 100

115, 400

113, 600

114, 500 115,200

116, 300

104, 400

106, 200 105,000

106, 800

105, 000

104, 500

106, 600

27, 6 27. 9 28. 4

27. 9 32. 0

61, 2 60. 4

58. 3 59. 7 60. 0

114, 600 105, 400 28. 8 59. 9

0. 01

0. 01

0. 01

0. 01

157, 800

156, 300

155, 700

155, 700

133, 600

134, 100

132, 700

25. 5

27. 6

59. 9 61. 8 62. 3 61. 7

avg 156, 400 133, 500 26. 6 61. 4

0. 02 0.01

0. 01 0.05

0. 02

171, 300

170, 300

172, 500

174, 300

163, 900

1 56, BOO

161, 300

164, 500

27. 0 25. 0

17. 6 22. 9

57. 1 59. 9 59. 7 53. 6 57. 8 avg 172, 100 161, 600 23. 1 57. 6

0. 05 177,800 160,900 19. 8 51. avg 177, 800 160, 900 19. 8 51 . 8

IMPACT PROPERTIES

Energy

Absorbed

ft-ib

Charpy FVacture Geometry Area

27. 5 28. 5 25. 5

n. 0

26. 0 21.0

24. 5

23. 0

24. 0

21. 5 23. 5 23. 0

24. 0

23. 5

23. 0

95

100

Room

0. 02

0. 02

0. 02

174, 500

174, 100

174, 400

112, 200

112, 100

24. 2

23. 9

51. 0

48. 9 avg 174, 300 112, 200 24. 0 50. 0

NiSpan "C"

Age hardened

at 1200°F, AC

Specimen

Type B

195

0. 02

0. 02

0. 02

196, 700

188, 600

189, 500

121, 300

119, 200

120, 200

24. 7 29. 7 26. 8

47, 6 49. 7 48. 1 avg 191, 600 120, 200 27. 1 48. 5

76

0. 02

0. 02

0. 02

222, 300

225, 000

226, 800

132, 500

132, 300

128, 700

30. 9 29. 8 34. 1

47. 6 45. 1 48. 4 avg 224, 700 131, 200 31. 6 47. 0

20

0. 02

0. 02 avg

243, 400

245, 600

244, 500

145, 700

144, 000

144, 900

31. 6 29. 0

30. 3

43. 1 43. 5

43, 3

18. 0 18. 0

18, 0

18, 0

17, 0

1 7, 5 18, 0

1

17. 0

17. 0

17, 0

17. 0

100

676435 O—63 3 13
TABLE V IRON ALLOYS (Continued)

TENSILE PROPERTIES IMPACT PROPERTIES

Test Crosshead Tensile Yield Elongation Reduction Energy Charpy Fracture Temp Velocity Strength Strength of Area Absorbed Geometry Area MATERIAL (0.2% offset) °K in/min psi psi % in 4D % ft -lb %

0. 02 299, 000 236, 100 10. 3 38. 1 8.0 Room 0. 02 300, 900 239, 500 10.0 37. 2 8. 0

8. 0 avg 300, 000 237, 800 10. 2 37. 6 8.0 V 100

n r\7 U . U -510, DKJyJ to, o UU 7. 4 7 . 0

0. 02 317, 400 6. 7 22. 3 6. 5 UNIMACH #1 (Vascojet

195 0. 02 318, 000 257, 400 8. 8 29. 1 5. 5

0. 02 312, 100 262, 400 7. 0 19. 7 5. 5

4. 5 1000)

Heat treated avg 316, 500 265, 000 7. 5 23. 3 6. 0 V 100

at 1850°F, 0. 02 365, 400 324, 000 1. 4 1 . 1 1. 5 lOZST double 0. 02 350, 900 302, 000 0. 5 0 3. 0 temper 76 0. 02 340, 600 300, 700 0. 3 0 3. 0

Specimen

Type B

2. 5 avg 352, 300 308, 900 0. 7 0. 4 2. 5 V 100

0. 02 350, 800 350, 800

20 0. 02 353, 200 350, 100 0. 3 0 avg 352, 000 350, 500 0. 3 0

0. 02 187, 800 179, 500 1 5. 4 56. 3 64. 0

0. 02 183, 700 176, 600 15. 8 59. 4 47, 0 Room 50. 5 61. 0 46. 5 avg 185, 800 178, 100 15. 6 57. 8 54. 0 V 100

0. 02 213, 300 206, 600 15. 0 55. 6 14. 5

0. 02 213, 300 206, 200 14. 6 54. 9 16. 5 17-4 PH 195 1 5. 0 H 1100

14. 0 avg 213, 300 206, 400 14. 8 55. 2 15. 0 V 100 Specimen

Type B

76

0. 02

0. 02

233, 400

246, 600

230, 300

241, 300

12. 9 10. 444. 7 30. 22. 5 3. 0

0. 02 257, 900 251, 100 2. 7 5. 0 3. 0 avg 246, 000 240, 900 8. 7 26. 6 3. 0 V 100

0. 02 293, 100 Z93, 100 0. 7 3. 7 20 0. 02 1.0 5. 0

0. 02 289, 900 287, 100 0. 8 5. 1 avg 291, 500 290, 100 0. 8 4. 6

14
TABLE V IRON ALLOYS (Continued)

TENSILE PROPERTIES IMPACT PROPERTIES

Test Cros shead Tensile Yield Elongation Reduction Energy Charpy FVacture Temp Velocity St IT 6ngth T" *i n frtVi i. Cii^ Ll 1 of Area Ab 6 or be d Geometry Area MATERIAL (0.2% offset) °K in/min psi psi % in 4D % ft -lb %

0. 02 97, 900 62, 800 55. 7 80. 4 48, 5 Room 0. 02 97, 200 61, 600 54. 5 78. 4 46. 5

avg 97, 600 62 200 55. 1 79. 4 49 0 } /? ^r I fifi 1 / C \ 1 u u

0.02 1 51 , 300 53, 800 44. 6 72. 9 42. 5 195 0. 02 1 53, 000 54, 900 46. 4 73. 3 42. 5

3 2 1

0. 02 154, 100 59, 100 46. 1 71. 8 avg 152, 800 55, 900 45. 7 72. 7 42. 5 1/2 V 100 Anns ^Is d

0. 02 229, 400 ... 37. 8 62. 9 30. 0 Specimen

Type B

0. 02 220, 700 64, 600 38. 2 58. 0 34. 0 76 0. 02 219, 800 66, 200 37. 1 53. 3 34. 5

0. 02 2 Z 1, 700 46, 400 38. 6 65. 6 avg 222, 900 59, 100 37. 9 60. 0 33. 0 1/2 V 100

0. 02 267, 400 58, 300 27. 0 20 0.02 271, 700 58, 600 34. 7 43. 6 35. 5 30. 5 avg 269, 600 58, 500 34. 7 43. 6 31. 0 1/2 V 100

0. 02 103, 300 64, 000 55. 3 76. 8 52. 0

0. 02 104, 200 62, 800 55. 4 75. 5 59. 5 Room 49. 0 51. 0 avg 103, 800 63, 400 55. 4 76. 2 53. 0 1/2 V 100

0. 02 148, 400 67, 200 50. 2 70. 6 56. 0 195 0.02 143, 900 69, 500 50. 5 70. 4 57. 5

347

0. 02 149, 100 69, 700 49. 9 69. 3 61. 5 avg 147, 100 68, 800 50. 2 70. 1 58. 5 1/2 V 100 Annealed

0. 02 60, 100 53. 0 Specimen

Type B

0. 02 217, 400 62, 500 41. 7 60. 0 56. 0 76 0. 02 216, 400 60, 500 41. 7 57. 3 54. 5

0. 02 218, 600 65, 500 41. 1 56. 3 avg 217, 500 62, 200 41. 5 57. 9 54. 5 1/2 V 75

0. 02 266, 400 72, 100 38. 3 42. 3 44. 5 20 0. 02 268, 600 74, 900 38. 2 48. 0 44. 5

0. 02 269, 200 82, 200 37. 6 45. 5 avg 268, 100 76, 400 38. 0 45. 3 44. 5 1/2 V 75

15
TABLE V IRON ALLOYS (Continued)

Test Temp

MATERIAL

"K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min psi psi % in 4D %

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft -lb %

Room

3. 5

3. 0

3. 0 avg 3.0 V 100

195 440 C

1. 0

2. 0

2. 0

2. 0 avg 2.0 V 100 Heat treated

at 1875°F; 1000°F, 1050°F

double temper 76 -

1. 0 1.0

1,0

1. 0 1.0 avg 1.0 V 100

Room

0.02 151,100 106,200 0.02 142,800 93,400 17.3 57.2 0.02 152,000 103,000 17.8 59.2

12.5

18. 0

1 5. 5 16.0

17. 5 avg 148,600 100,900 17.6 58.2 16.0 V 100

1 0 7 5

Heat treated 195

at 1450°F, 720°F temper

0.02 164,700 112,100 18.7 51.8 0.02 162,400 109,300 17.9 51.8 0.02 173,600 127,000 --- 57.5

7. 0

7. 0

avg 166,900 1 16,100 18.3 53.7 7.0 V 100 Specimen

Type B

76

0.02 224,400 14.5 40.9

0.02 218,900 189,300 15.3 38.3 0.02 228,500 201,000 8.3 11.7 0.02 214,600 187,000 --- 33.8

1. 5

1. 5

avg 221,600 192,400 12.7 31.2 1.5 V 100

20

0. 02 268, 300 1.5 5. 5 0.02 271,200 262,900 1.4 5.7 avg 269,800 262,900 1.4 5.6

16
TABLE V IRON ALLOYS (Continued)

MATERIAL

Test Temp

°K

TENSILE PROPERTIES

Crosshead

Velocity

in/min

Tensile

Strength

psi

Yield Strength (0.2% offset) psi

Elongation Reduction

of Area % in 4D %

IMPACT PROPERTIES

Energy Charpy FVacture Absorbed Geometry Area

ft -lb %

0. 02

0. 02

219, 200

219, 500

204, 700

207, 200

11.3

10. 4

35. 8 31. 2 Room

avg 219, 400 206, 000 10. 8 33. 5

195

0. 02

0. 02

246, 600

244, 000

228, 100

229, 100

10. 4

8. 0

24. 0

17. 3 17-7 PH

TH 1050

Specimen

Type B

avg 245,300 228,600 9. 2 20. 6

76

0. 02

0. 02

271, 800

273, 000

265, 700

267, 600

0. 4

0. 4

avg 272, 400 266, 600 0. 4

20

0. 02

0. 02

0. 02

239, 100

258, 500

237, 400

0. 3 0. 2

0 avg 245, 000 0. 2

2. 5

3. 5

5. 5

5. 5 6.0

5. 0

4. 5

2. 5

2. 5

2. 5

1. 5

1. 5

1. 5

1. 5

100

100

100

Room

0. 02

0. 02

160, 600

159, 500 111,400 no, 800

25. 4 49. 9 48. 7

avg 160,000 111, 100 25. 4 49. 3

195

0. 02

0. 02 176,000

175, 600

120, 200

120, 400

29. 0 29. 1

51. 6

52. 0 A - 286

Solution treated at 1800°F,

Aged at 1350°F

Specimen

Type B

avg 175, 800 120, 300 29. 0 51. 8

76

0. 02

0. 02

209, 100

209, 700

135, 300

135, 500

36. 2 35. 348. 3 50. 0

avg 209, 400 135, 400 35. 8 49. 2

20

0. 02

0. 02

235, 100

235, 500

150, 600

149, 800

36. 8

35. 5

43. 9

41. 8 avg 235, 300 1 50, 200 36. 2 42. 8

57, 0 55. 0 55. 0

55. 5

55. 0

57. 0 58. 0

56. 5

52. 0 52. 5 52. 0

52. 0

100

100

Room

0. 02

0. 02

0. 02

240, 300

241, 800

241, 200

218, 900

221, 200

14. 1 13. 5 18. 3

25. 2 26. 4 avg 241, 100 220, 000 15. 3 25. 8

195

0. 02

0. 02

267, 300

268, 000

222, 100

218, 800

16. 8 17. 1

25. 9 26. 3 30 1

Extra full hard

Specimen

Type D

avg 267,600 220,500 17. 0 26. 1

76

0. 02

.0. 02

329, 100

327, 500

280, 000

264, 500

19. 1 18. 7

24. 7 24. 8 avg 328,300 272,200 18. 9 24. 8

20

0. 02

0. 02

352, 700

352, 600

314, 700 2. 7

2. 7

13. 2 11.6 avg 352,600 314,700 12. 4

17
TABLE V IRON ALLOYS (Continued)

Test Temp

MATERIAL

°K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min psi psi % in 4D %

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft -lb %

Room

2800 (9% Nickel 195

Steel)

Doable normal0.02 126,800 119,600 24.6 70.3 0.02 124,000 117,200 23.8 70.4

avg 125,400 118,400 24.2 70.4

0.02 145,900 131,400 25.1 67.3 0.02 147,000 127,700 25.6 67.7

52. 0 53. 0 51. 0

52. 0 U 75

50. 5 50, 0 47.0 avg 145, 3UU 1^7, OUU o/.D A Q fl T T "7 C

izeu 1D-)U r ana

1450°F; 1050''F

/ b temper

Specimen

0.02 180,600 159, 200 27.1 59.6 0.02 180,100^^ 159,900^^ ^''•^y, 0.02 176,800'' 160,100'' 25.7'' 62. o"

25. 0 25. 0 26, 0 avg 179,200 159, 700 26.7 60.6 25.5 U 100 Type A

(except (*) type B) 20 0.02 218,600* --- 13-5* 36.9^

0.02 220, lOOj^ 206, 400^ 23.1'" 58.6' 0.02 217,700* 210,100*

avg 218,800* 208,300°" 18.3* 47.8*

Room

11.0 11.5

11. 5 10.5 avg 11.0 V 100

4340

Annealed

3. 5

3. 0 3.0

3. 0 avg 3.0 V 100

76

1.5

1. 5 2, 0 1.0 avg 1.5 V 100

18
TABLE V IRON ALLOYS (Continued)

TENSILE PROPERTIES IMPACT PROPERTIES

Test Crosshead Tensile Yield Elongation Reduction Energy Charpy JVacture Temp Velocity Strength of Area Absorbed Geometry Area MATERIAL (0. 2% offset) °K in/min psi psi % in 4D % ft -lb %

0. 02 129, 700 97, 200 62. 9 75. 1 54. 0 Room 0. 02 1 33, 000 97, 600 57. 2 76 9 52. 0 53 5 avg 131, 400 97, 400 60. 0 76 0 53. 0 U 100

0. 02 187, 200 95, 700 44. 7 67 7 57. 0 195 0. 02 189, 000 97, 300 45. 0 69. 5 56. 0

30 2

55. 5 avg 188, 100 96, 500 44. 8 68. 6 56. 0 U 100 Cold Drswn

0. 02 258, 200 101, 300 37. 4 56. 1 46. 0 Specimen

Type B

76

0. 02 260, 600 102, 700 37. 8 56. 0 47, 0 51. 0 48 5 avg 259, 400 102, 000 37. 6 56. 0 48. 0 U 100

0. 02 114, 400

20 0. 02

0. 02

312, 300

315, 000

117, 300 33. 3 31.135.

37.

28 avg 313. 600 115, 800 32. 2 36. 5

0. 02 109, 000 60, 600 71. 6 71. 1 34. 5

0. 02 109, 800 62, 100 70. 4 71. 6 33. 0 Room 34. 5 36. 5 avg 109, 400 61, 400 71.0 71. 4 34. 5 U 100

0. 02 177, 600 62, 200 43. 5 61. 6 60. 0

0. 02 176, 400 64, 300 42. 8 61. 0 60. 0 51. 0 195 48. 0 303 71.0

53, 0 Annealed avg 177, 000 63, 200 43. 2 61. 3 57. 0 U 25

Specimen 0. 02 245, 300 69, 000 37. I 56. 9 87. 0 Type B

76

0. 02 240, 600 65, 500 37. 0 55. 2 93. 5 83. 0 91. 0 avg 243, 000 67, 200 37, 0 56. 0 88. 5 U 2 5

0. 02 297, 400 32. 9 36. 8 20 0. 02

0. 02

298, 400

296, 600

82, 700

82, 500

33. 0 38. 0

avg 297, 500 82, 600 33. 0 37. 4
TABLE V IRON ALLOYS (Continued)

Test Temp

MATERIAL

°K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min psi psi % in 4D %

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft -lb %

Room

0.02 98,300 56,700 79.2 83.7

0.02 98,400 57,000 78.6 83.0

65. 0 65. 5 66. 0 avg 98,400 56,900 78.9 83.4 65. 5 1/2 V 75

195

3 0 4 LC

Annealed

0.0^: lD3,bUU 61,100 71.8 76.8 0.02 152,500 62,100 67.6 76.7

102. 0

82. 0 71. 5 90. 5 77. 0 avg 153,000 61,600 69.7 76.8 84. 5 1/2 V 75

Spec imen Type B

0.02 222,300 66,900 42.3 69.6

0.02 221,400 65,700 43.6 68.9 0.02 221,000 --- 42.9 69.1

80. 5 74. 5 70. 5 76. 0 avg 221,600 66,300 42.9 69.2 75. 5 1/2 V 75

20 0.02 272,900 75,400 47.8 38.60.02 273,300 75,800 36.7 42.1

63. 0 63. 0 62. 0 avg 273,100 75,600 42.2 40.4 62, 5 1/2 V 100

4 0.20 241,800 77,900 33.6 58.6 0.20 242,600 77,900 --- 55.8 avg 242,200 77,900 33.6 57.2

Room

0.02 84,900 31,800 62.1 70.2 0.02 84,200 31,700 56.3 72.2

0.02 84,400 31,500 58.4 71.0

70. 0 71. 0 70. 0 avg 84, 500 31,700 58.9 71.1 70. 5 1/2 V 100

195

3 1 0

0.02 106,700 43,500 69.8 67.7 0.02 107, 300 44, 300 73.3 68.4

66. 0 71. 0 67. 0 avg 107,000 43,900 71.6 68,0 68, 0 1/2 V 100 Annealed

Specimen

Type B 76

0.02 157,700 76, 500 68.8 46.2 0.02 156,600 75,600 66.6 53.0

51. 0 55. 0

46. 0 55. 5 avg 157,200 76,000 67.7 49.6 52. 0 1/2 V 100

20

0.005 181,100 99,300 41.9 34.8 0.02 185,000 100.200 46.8 38.5 0.02 185,800 99,400 49.3 34.1

1.0 164,500 103, 900 --- 50.3

48. 5 44. 5 44. 0

avg 179,100 100,700 46.0 39.4 45. 5 1/2 V 100

4 0.02 186,700 102,100 49.8 41.0 avg 186,700 102,100 49.8 41.0

20
TABLE V IRON ALLOYS (Continued)

TENSILE PROPERTIES IMPACT PROPERTIES

Temp

MATERIAL

Orossneacl

Velocity Tensile

Strength

Yield Strength (0.2% offset)

Elongation Reduction

of Area

jLitiG r gy Absorbed Charpy Fracture Geometry Area

°K in/min psi psi % in 4D % ft -lb %

0. 02 201, 400 201, 400 14. 5 67. 1 20. 5

0. 02 1 94, 700 1 94, 700 13. 9 68. 2 26. 0 Room 0. 02 205, 700 205, 700 14. 6 66. 2 16. 5 34. 0 21.0

17. 0 avg 200, 600 200, 600 14. 3 67. 2 22. 5 V 100

0. 02 216, 400 216, 400 15. 6 63. 7 6. 0

0. 02 205, 800 205, 800 15. 8 66. 3 8.0

0. 02 214, 300 214, 300 13. 8 63. 2 12. 0

6. 5 195 13. 0

9. 5 11 0 4 10 9. 0

Heat treated

at 1800°F,

12. 0 avg 212, 200 212, 200 1 5. 1 64. 4 9. 5 V 100 700 °F temper

0. 02 258, 900 258, 900 6. 2 20. 6 3. 0 Specimen

Type B

0. 02 269, 300 269, 300 5. 4 20. 7 2. 0

2 0

3. 0

2. 0 avg 264, 100 264, 100 5. 8 ZO , 6 2. 5 V 100

0. 02 327. 600 0. 7 6. 0 20 0. 02 315, 900 0. 8 5. 2 avg 321, 800 0. 8 5. 6

0. 02 205, 600 165, 600 15. 6 53. 9 33. 5 Room 0. 02 201, 300 179, 100 14. 9 53. 8 33. 5 0. 02 202, 500 177, 500 14. 9 52. 2 34. 0 avg 203, 100 174, 100 15. 1 53. 3 33. 5 V 100

0. 02 217, 300 182, 300 15. 5 51. 6 10. 0 195 0. 02 218, 900 182, 900 1 5. 3 52. 5 9. 5

4 1 6

10. 0 avg 218, 100 182, 600 1 5. 4 52. 0 10. 0 V 100 Heat treated

at 1800°F, 0. 02 258, 300 230, 200 8. 4 18. 8 2. 0 700"^ temper 0. 02 262, 300^ 233, 400 11. 1 29. 8 27. 1

2. 5 76 0. 02 260, 700* 3. 0 Specimen 0. 02 263, 000 8. 2 18. 2 2. 5 Type B 2. 5 (except (*) type A) avg 261, 100 231, 800 9. 2 23. 5 2. 5 V 100

0. 02 290, 100 290, 100 0. 4 2. 1 20 0. 02 295, 100 295, 100 2. 5 avg 292, 600 292, 600 0. 4 2. 3

676435 0—63 4 21
TABLE VI NICKEL ALLOYS

Test Temp

MATERIAL

"K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min psi psi % in 4D %

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft -lb %

Room

0.02 131,900 124,200 17.2 58.8 0.02 130,600 122,700 16.8 56.9

62. 0

80. 5 72. 5 84. 0 86. 5 avg 131,200 123,400 17.0 57.9 77. 0 V 75

INCONEL 195

Cold drawn

20%

0.02 143,700 133,600 19.7 57.8 0.02 142,800 130,400 20.5 58.9

88. 5 91. 0 89. 0 avg 143,300 132,000 20.1 58.4 89. 5 V 100

specimen

Type A

0.02 167,700 150,500 26.2 62.1 0.02 168,900 --- 26.6 61.7

77 0 86. 0 85. 0 avg 168,300 150,500 26.4 61.9 82. 5 V 100

20 0.02 180,400 160,000 30.4 55,5 0.02 181,700 160,700 30.6 55.9 avg 181,100 160,400 30.5 55.7

Room

0.02 191,600 136,300 24.1 47.5 0.02 191,900 136,300 26.5 46.6

0.02 188,600 136,900 25.6 44.6

0.02 191,600 136,900 27.2 47.6

40.5

40.0 40.0

avg 190,900 136,600 25.9 46.6 40. 0 V 100

INCONEL "X" 195

Direct aged

0.02 204,900 143,500 30.1 49.1 0.02 203,100 143,700 30.0 47.4

avg 204,000 143,600 30.0 48.3

1300°F, AC,

tempe red

opecimen

Type B

0.02 227,500 151,300 31.7 45.6

0.02 226,500 --- 32.4 45.7

0.02 226,500 150,200 32.9 45.4

0.02 228,100 150,200 33.5 44.6

35. 0

34. 5 35. 0

avg 227,200 150,600 32.6 45.3 35.0 V 100

20

0.02 248,500 156,100 33.3 43.6

0.02 247,200 155,300 34.0 40.0 0.02 241,000 155,400 34.7 43.3 0.02 243,600 153,800 35.6 42.2 avg 245,100 155,200 34.4 42.3

22
TABLE VI NICKEL ALLOYS (Continued)

Test Temp

MATERIAL

°K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min psi psi % in 4D %

Energy Charpy fVacture Absorbed Geometry Area

ft -lb %

Room

KJ . KJ c, UL. f 1 w

0.02 64,000 21,400 49.1 66.2

0.02 64,300 20,400 47.8 66.2

89.5

94. 5 94. 5 avg 63,700 20,900 48,4 66.2 93. 0 1/2 V 50

195 "A" NICKEL

Annealed

0.02 71,100 21,100 51.4 69.2

0 02 69 900 22 200 48 8 64 1 0.02 71,300 22,800 50.6 63.5

79. 0 92 5 88. 0 84. 5 avg 70,800 22,000 50.3 65.6 86. 0 1/2 V 50

Specimen

Type A

u. v y-^i ^uu L.O , luu Oil. 1 (D. ii 0.02 92,200 28,000 60.8 75.1 0.02 93,600 29,000 60.7 74.3

o 0 . D 90. 0 87. 0 81.0

avg 93,000 28,500 61.2 75.2 86. 0 1/2 V 75

20 0.02 112 400 37 300 59.2 68.20. 02 111, 400 39, 600 59. 1 67. 5

99. 5 93. 5 100. 5 avg 1 11,900 38,400 59.2 67.8 98. 0 1/2 V 75

Room 0. 02 191, 900 --- 24. 6 33. 0 0.02 191,000 140,300 25.2 33.2

15 0

15. 5 14. 5 avg 191,700 1 39,200 26.2 32.8 15. 0 1/2 V 100

195 RENE 41 (R41)

0.02 207,600 --- --- nn? iQ7inn i An nnn '^n^ ^4R

0.02 202,400 143,800 28.9 33.1

13.0

12 0

13. 5 12. 5 avg 202,400 141,900 29.6 34.0 12. 5 1/2 V 100 Solution treated

at 1975°F, WQ

76 Specimen

Type B

U.Uii c, JO , yyJyJ i Oc. , CVKJ c. i . ( . O 0.02 240,500 164,400 29.3 26.6

11 5 10. 5 10. 5 10. 5 avg 239,700 163,300 28.5 25.6 10. 5 1/2 V 100

20 0.02 254,000 --- 27.4 26.6

0.02 254,200 172,900 24.9 24.3 11.5

10.0

11.5 avg 254,100 172,900 26.2 25.4 11.0 1 '2 V 100
TABLE VI NICKEL ALLOYS (Continued)

Test Temp

MATERIAL

TENSILE PROPERTIES

Crosshead Tensile

Velocity Strength

in/

r

psi

Yield Elongation Reduction

Strength of Area

(0.2% offset) psi % in 4D %

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft -lb %

0. 02 0.02

169, 100

170, 900

118, 700

119, 700

26. 6 27. 651. 6 53. 7 Room

avg 170, 000 119, 200 27. 1 52. 6

"K" MONEL

Age hardened

at 1100°F and

lOOO-F, AC

Specimen

Type B

195

0. 02 1 78, 100 128, 700 0.02 179,000 130,900

0. 02 176, 100 129, 000

30. 3 28. 3 27. 354. 2 54. 5 54. 3

avg 177, 700 129. 500 28. 6 54. 3

0. 02

0. 02

199, 500

196, 100

142, 900

142, 700

33. 4 33. 2

54. 3 54. 3 76

avg 197, 800 142, 800 33.3 54. 3

20

0. 02

0. 02

212, 300

214, 400

152, 900

152, 000

34. 3 33.8

52. 6 52. 1 avg 213, 400 152,400 34.0 52. 4

35. 0 41. 5 32. 0 41. 5 34. 0

37. 0

37. 5 37. 5 30. 5 28. 0

36. 5

34. 0

30. 5

36. 5 28. 5 28. 5 31.0

100

100

100

Room

0. 02

0. 02

0. 02

115, 100

102, 800

111, 600

78, 600

74, 100 4. 5

9. 0

36. 0 28. 0 27. 4

avg 109, 800 76, 400 6. 8 30. 5

"S" MONEL

Cast, annealed

1600 °F, 1300°F,

"'OQ .

Specimen

Type A

195

0. 02

0. 02

0. 02

1 1 7, 100

126, 700

126, 800

83, 700

86, 200

12. 5

9. 3 17.0

26. 0 21.6

32. 0

avg 123, 500 85, 000 12.9 26. 5

76 0.02 127,800 97,100

0.02 137,200 97,200

0.02 135,700

18. 5

12. 7

32. 8 17. 4

18. 0 avg 133, 600 97, 200 15. 6 22. 7

20

0. 02

0. 02

0. 02 avg

135, 400

145, 100

168, 500

1 49, 700

106, 500

106, 500

17. 4

12. 4

14. 9

28. 1 23.4

20. 8

24. 1

26. 0 54. 5 39. 5 46. 5 39. 5

41. 0

43. 5 37.0

53. 0 41. 5

43. 5

30. 0 43. 0 43. 5

39. 0

100

100

100

24
Test Temp

MATERIAL

°K

TABLE VII TITANIUM ALLOYS

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/min psi psi % in 4D %

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft-lb %

Room

0.02 135,200 127,800 17.4 42.4

0.02 133,000 126,000 20.5 44.7

1 7. 5

1 7. 5 18.0 avg 134,100 126.900 19.0 43.6 17.5 V 100

195 5Al-2.5Sn,

(A-1 lOAT)

0.02 1 59,700 150,400 13.2 37.5 0.02 160,500 1 50,600 14.0 39.5

14. 5 15. 0

13. 5 avg 160,100 1 50,500 13.6 38.5 14.5 V 100 Annealed

Specimen 76 Type B

0.02 208,100 200,000 13.5 29.2

0.02 208,800 200,300 14.2 29.8

11.5 11.5

10. 5 avg 208,400 200,200 13.8 29.5 11.0 V 100

20 0.02 250,900 242,900 10.7 17.2 0.02 250,800 242,200 12.3 19.4

Room

0.02 136,900 136,900 27.4 56.2 0.02 1 37,400 1 37,600 26.6 55.6

20. 0

18. 5 20. 5 avg 137,200 1 37, 200 26.5 55.9 19. 5 V 100 13V-llCr-3Al

(B-120 VCA)

Solution treated

0.02 182,800 181,900 17.3 48.0 0.02 183,900 183,900 16.1 46.011.5

9. 5

9. 5 avg 183,400 182,900 16.7 47.0 10.0 V 100

Specimen

Type B

76

0.02 279,400 273,200 6.1 20.5

0.02 279,600 273,500 7.3 21.4

4. 0

5. 0

2. 5

5. 0

4. 5 avg 279,500 273,400 6.7 21.0 4. 0 V 100

20 0.02 327,100 --- 0.3 2.5

0.02 338,900 --- 0.6 4.4

avg 333,000 0.4 3.4

Room

0.02 147,900 138,000 17.0 48.4

0.02 149,100 138,000 16.1 46.3

28. 5 28. 0 26. 0 avg 148,500 1 38,000 16,6 47.4 2 7. 5 V 100

6A1-4V 195 (C-120 AV)

Annealed

0.02 173,500 163,900 12.5 41.5

0.02 1 74,300 164,400 13.3 41.6

22. 5 22. 0 22. 5 avg 173,900 164,200 12.9 41.6 22.5 V 100

Specimen

Type B

0.02 236,800 227,200 10.0 40.7 0.02 239,500 230,000 10.4 40.5

14. 5 16. 0 16. 5 14. 5 avg 238,200 228,600 10.2 40.6 I 5. 5 \' 100

20 0.02 285,900 277,200 6.7 32.3 0.02 286,400 278,400 6.7 29.8 avg 286,200 277,800 6.7 31.0

25
FIGURE I HIGH-ELONGATION EXTENSOMETER
FIGURE 3. TENSILE PROPERTIES OF THE ALUMINUM ALLOYS.

TEMPERATURE, °F

-300 -200 -100

C 80

in CO

100 150 200 TEMPERATURE, °K

75 « 10'

0.01 0.02 0 03 0.04 005 STRAIN, inches per inch TENS 50, SAND CAST T 6

- 460 - 400

ISOxlO'r

TEMPERATURE, "F

-300 -200 -100

"C. BOto

CO y

UJ w

^ 60- —

to

40

RA

~ UJ

X lU- 1

^20

,76 °K

-/195 "1 ; \OOM TEM >

100 150 200 TEMPERATURE, "K

0.03 0.06 0 09 0.12 STRAIN, inches per inch

356, CHILL CAST T6
FIGURE 4. TENSILE PROPERTIES OF THE ALUMINUM ALLOYS.

2020 , T6
FIGURE 5. TENSILE PROPERTIES OF THE ALUMINUM ALLOYS.

-460 - 400

150x10^

TEMPERATURE, "F

-300 - 200 - 100

76 'K —-—

OS")'

Roo^h TEM

100 150 200 TEMPERATURE °K

a03 0.06 009 0.12 STRAIN, inches per inch

2024 , T86

TEMPERATURE, °F

-300 - 200 -100

100 150 200 TEMPERATURE, "K aoe 016 024 a32 STRAIN, inches per inch

6061 , T6
FIGURE 6. TENSILE PROPERTIES OF THE ALUMINUM ALLOYS.

-460 -400

I50«10-

TEMPERATURE , °F

- 300 -200

OO 150 200 TEMPERATURE, °K

0

,20° Kr

<

C

0.04 008 012 0.16 STRAIN, inches per inch 7075 , T6

FIGURE 7 IMPACT PROPERTIES OF THE ALUMINUM ALLOYS.

CDa 10 o

TEMPERATURE ,°F -300 -200 -100

6 2024-T6

CHARPY V

100 150 200 TEMPERATURE , "K

-460 -400 TEMPERATURE, °F

- 300 - 200 - IOC

CHARPY V

( 1/2 SIZE)

• PARTIALLY FRACTURED

SAMPLES

100 150 200 TEMPERATURE , °K

30
FIGURE 8. TENSILE PROPERTIES OF THE COBALT ALLOYS.

ELGILOY , COLD REDUCED 45 7o

FIGURE 9. IMPACT PROPERTIES OF THE COBALT ALLOYS.

-460 -400 TEMPERATURE, °F

-300 -200 -IOC

CHARPY V

STELLITE 3 (SAND CAST)

100 150 200 TEMPERATURE , °K

250 300

- 460 - 400

<^ 30

TEMPERATURE, °F

- 300 200 -100

CHARPY U

STELLITE 25 (COLD REDUCED 26%)

100 150 200 TEMPERATURE, "K

250 300
FIGURE 10. TENSILE PROPERTIES OF THE COPPER ALLOYS.

BERYLCO 25 , ANNEALED

BERYLCO 25 , HARD
FIGURE II. TENSILE PROPERTIES OF THE COPPER ALLOYS.

-460 -400 TEMPERATURE, °F

-300 -200 -100

_] O

— _]

in iij

-

1 1 1 1 1

-

- ,^_^T -

- -

-<

-

RA

E

1 1

1 1

1

10

i,

K

^76 •K

^195°K

ROON1 TE^ p.

100 150 200 TEMPERATURE, °K

0.08 0.16 0.24 0.32 STRAIN, inches per inch

70/30 BRASS , 3/4 HARD

-460 -400

isoxio'r

TEMPERATURE,

-300 -200

in <n

I- F

, 80

in

UJ 60 J3

Z -

LJ >

40

1

1 1 11

RA ~.

E

< Y

1

1 1

1 1 100 150 200 TEMPERATURE, °K

0 -

» i

K

^76°K

^195 'K

^OOM TEMP\/\

Q20 0.40 0.60 080 1.00 STRAIN, inches per inch

OFHC , SOFT
FIGURE 12. IMPACT PROPERTIES OF THE COPPER ALLOYS.

TEMPERATURE. "F

-300 -200 -100

CHARPY V

70/30 BRASS ( 3/4 HARD )

TEMPERATURE, °h -300 -200 -100

100 150 200 TEMPERATURE . °K

OFHC (SOFT)

CHARPY V

(1/2 SIZE)

• PARTIALLY FRACTURED

SAr^PLES

100 150 200 TEMPERATURE , °K

Q: 60

TEMPERATURE , °F

-300 - 200 -100

BERYLCO 25 (ANNEALED)

BERYLCO 25 (HARD)

CHARPY U

• PARTIALLY FRACTURED SAMPLES

100 150 200 TEMPERATURE , °K

34
FIGURE 13. TENSILE PROPERTIES OF THE IRON ALLOYS.

TEMPERATURE, °F

-300 -200 -100 T

100 150 200 TEMPERATURE, °K

20° K

^ROOM TEMP.

0.06 0.12 0.18 024 STRAIN, inches per inch

INVAR 36 , 12-15% COLD DRAWN

TEMPERATURE,

-300 - 200

.2C °K

76°K

195°^

OM T EM P.

100 150 200 TEMPERATURE, °K

0.08 0.16 0.24 032 STRAIN, inches per inch

NiSPAN "C" , AGE HARDENED I200°F-5HR , AC , TEMPERED
TABLE VUI CARBIDES

Test Temp

MATERIAL

°K

TENSILE PROPERTIES

Crosshead Tensile Yield Elongation Reduction

Velocity Strength Strength of Area

(0.2% offset) in/ Tn in nci y^ci 0/- in A. 07 111/ 111111 jjoj. ^oi /o in, rrU /o

IMPACT PROPERTIES

Energy Charpy Fracture Absorbed Geometry Area

ft -lb %

Room . 25

.25 avg .25 V 100 TITANIUM

CARBIDE 195

Sintered (32% Ni)

, 20

. 20

. 20 avg .20 V 100

76

. 20

. 20 avg .20 V 100

i

Room

1.0 i 1.0

1.0 i avg 1.0 V 100

195 TUNGSTEN

CARBIDE

1 . 0 1.0

1.0 avg 1.0 V 100

(CA-10)

76 Sintered (13% Co)

1,0 1.0 ! 1.0 avg 1.0 V 100

36
FIGURE 14. TENSILE PROPERTIES OF THE IRON ALLOYS.

TEMPERATURE, "F

ROOM TEMP.

0 50 100 150 200 250 300 0 0.04 a08 0.12 ai6 0,20 TEMPERATURE, °K STRAIN, inches per inch

UNIMACH *l(VASCOJET 1000), HEAT TREATED 1850 °F- I HR , AC, DOUBLE TEMPERED I025°F-%HR

37
FIGURE 15. TENSILE PROPERTIES OF THE IRON ALLOYS.

-460 -400 TEMPERATURE, °F

-300 - 200 -100

if -i

K ^20°K

DOM TEMP

100 150 200 TEMPERATURE, °K

0.04 0.08 012 0.16 0.20 STRAIN, inches per inch

I7-7PH, TH 1050

TEMPERATURE, °F

-460 - 400 -300 -200 -100 0 80 J

0.40 TEMPERATURE, °K STRAIN, inches per inch A-286 .SOLUTION TREATED I800°F-I Vz HR, AC, AGED AT 1350 °F - I6HR, AC
FIGURE 16. TENSILE PROPERTIES OF THE IRON ALLOYS.

TEMPERATURE °F

20°K

r ^ROOM TE HP.

iOO 150 200 TEMPERATURE, °K

250 300 0.06 0.12 018 024 STRAIN , inches per inch

301 , EXTRA FULL HARD

-460 -400

450 «I0^

TEMPERATURE, °F

-300 -200 -100 0

K

Y-76 i

EMP sOM T

100 150 200 TEMPERATURE, °K

0.12 0.24 036 048 STRAIN, inches per inch

302, COLD DRAWN
FIGURE 17 TENSILE PROPERTIES OF THE IRON ALLOYS.

-460 -400

300«I0'

TEMPERATURE, °F

-300 - 200 -100

10 /1 —

0°K

6°K /

195° <

RO 3M T EM P.

100 ISO 200 TEMPERATURE. °K

250 300 020 040 O60 080 1.00 STRAIN , inches per inch

303 , ANNEALED

TEMPERATURE, "F

-300 - 200 -100

100 150 200 TEMPERATURE, "K

250 300 0.15 032 0.48 064 STRAIN, inches per inch

304 L, ANNEALED

40
FIGURE 18. TENSILE PROPERTIES OF THE IRON ALLOYS.

-460 -400

300«I0'

TEMPERATURE, °F

-300 - 200 -100 u

4° < fa

20°K| 76 "K

20°K, 1 IN. PER MIN. CROSSHEAD VELOCITY

^195 K

)M TE MP. A

100 150 200 TEMPERATURE, °K0.15 0.30 0.45 0.60 STRAIN .inches per inch

310 , ANNEALED

-460 -400

300«I0'

TEMPERATURE, °F

-300 - 200 -100 0' —

0°K

\ ^ 6''K

yROOM TEM A

100 150 200 TEMPERATURE, "K

ai2 0.24 036 048 STRAIN, inches per inch

321 , ANNEALED
FIGURE 19. TENSILE PROPERTIES OF THE IRON ALLOYS.

TEMPERATURE, °F

TEMPERATURE, °K STRAIN, inches per inch

347 , ANNEALED

-460 -400

450x10^

TEMPERATURE, "F

-300 -200 -100

100 150 200 TEMPERATURE, °K

0

10° K

1 <

<

5°K

ROC M T EMP.''

004 0.08 0.12 016 STRAIN, inches per inch 410 , HEAT TREATED 1800 °F - I HR , 00 , TEMPERED 700 °F - 4HR , AC
FIGURE 20. TENSILE PROPERTIES OF THE IRON ALLOYS.

TEMPERATURE , °F

0 50 100 150 200 250 300 0 0O4 008 0.12 0.16 0.20 TEMPERATURE, °K STRAIN, inches per inch

416 , HEAT TREATED 1800 "F - IHR , 00, TEMPERED 700 °F - 4HR , AC

TEMPERATURE, "F

020 TEMPERATURE, °K STRAIN, inches per inch

1075, HEAT TREATED 1450 °F - I MR , 00 , TEMPERED 720 °F - IHR, AC
FIGURE 21. TENSILE PROPERTIES OF THE IRON ALLOYS.
FIGURE 22. IMPACT PROPERTIES OF THE IRON ALLOYS.

TEMPERATURE, °F

300 - 200 - 100 r

TEMPERATURE,

300 -200

A-zee (SOLUTION TREATED AND AGED)

CHARPY V

-

1 1

1 1 1 1 CHARPY V

17-4 PH / — (H 1 100)/

-

416 (HARDENED)

-

1075 (HARDENED).

^ ^^^340

^^ANNEALED)

1 \ 'l 440C(AI>jNEALED)

100 150 200 TEMPERATURE , °K

100 150 200 TEMPERATURE , °K

TEMPERATURE, °F

•300 -200 -100

302 (ANNEALED)

_2800 (9% NICKEL STEEL) (DOUBLE NORMALIZED)

CHARPY U

• PARTIALLY FRACTURED

SAMPLES

NISPAN "C" (AGE HARDENED)

100 150 200 TEMPERATURE, °K

-400 1

TEMPERATURE , °F

-300 -200 -100 T

100 150 200 TEMPERATURE , °K
FIGURE 23. TENSILE PROPERTIES OF THE NICKEL ALLOYS.

-460 -400

300x10'

r

TEMPERATURE, °F

-300 -200 -100

tlJ

1/1 w IC/1 UJ z —

llJ >

-

1 1

1

1

1

—

— ' -

-

—

RA —

]

_

-

' -—

-

1

1 1

1

1

u

K

,76° /

K

-'^

,195 °K

^ROO yl TE

100 150 200 TEMPERATURE, "K

0.08 0.16 0.24 0.32 STRAIN, inches per inch

INCONEL , 20% COLD DRAWN

-460 -400

300«IO'r

TEMPERATURE, °F

-300 - 200 -100

100 150 200 TEMPERATURE, °K

0 —

^20° K

V

35° K

1 OOM TEMP

016 0.24 0.32 STRAIN, inches per inch

INCONEL "X", HOT ROLLED , DIRECT AGED 1300 °F - 20 HR . AC TEMPERED
FIGURE 24. TENSILE PROPERTIES OF THE NICKEL ALLOYS.

"S" MONEL , CAST, ANNEALED 1600 °F- IHR, 1300 °F - l/2 HR, OQ
FIGURE 25. TENSILE PROPERTIES OF THE NICKEL ALLOYS.

RENE 41, SOLUTION TREATED I975 °F-4HR , WQ
FIGURE 26. IMPACT PROPERTIES OF THE NICKEL ALLOYS.

TEMPERATURE, °F

-300 - 200 -100

INCONEL

(COLD DRAWN 20%)

-INCONEL X" (DIRECT AGED)

CHARPY V

• PARTIALLY FRACTURED SAMPLES

S MONEL

(CAST ANNEALED)

K MONEL

{AGZ HARDENED)

100 150 200 TEMPERATURE , °K

-460

120 I

TEMPERATURE, °F

• 300 - 200 - 100

60 o

Ul 40

CHARPY V

(1/2 SIZE)

• PARTIALLY FRACTURED SAMPLES

"A" NICKEL (ANNEALED)

RENE 41 (R4I) (SOLUTION TREATED)

100 150 200 TEMPERATURE , °K
FIGURE 27 TENSILE PROPERTIES OF THE TITANIUM ALLOYS.

-460 -400

300«10=

TEMPERATURE "F

-300 - 200 -100 IT

10=

-f

'76°K —

^195° K

\-

ROOM T lMP.

150 200 TEMPERATURE, "K

0.04 0.08 QI2 0.16 020 STRAIN, inches per inch

5AI - 2.5 Sn, ANNEALED

-460 -400

450.10'r

TEMPERATURE, "F

-300 -200 -100

CO liJ 2 —

1 r

50 100 150 200 TEMPERATURE, "K

0 —

— 20' K

<

(

^ROOM T EMP.

250 300 0.06 0.12 0.18 0.24 STRAIN, inches per inch

13V - IICr-3AI, SOLUTION TREATED
FIGURE 28. TENSILE PROPERTIES OF THE TITANIUM ALLOYS.

-460 -too TEMPERATURE, "F

-300 - 200 -100 IT

300x|o'

280

—1

r

76 °K

195° K

RC)0M T EMP.

150 200 TEMPERATURE, °K

0 0.04 0.08 0.12 0J6 0.20 STRAIN, inches per inch 6AI-4V, ANNEALED

FIGURE 29. IMPACT PROPERTIES

OF THE TITANIUM ALLOYS.

FIGURE 30. IMPACT PROPERTIES

OF THE CARBIDES.

TEMPERATURE , °F

- 300 • 200 - 100

CHARPY

6AI-4V (C-120 av) (ANNEALED),

5AI-2.5Sn(A-IIO AT) (ANNEALED)

l3V-IICr-3AI

(B-120 VCA)

(SOLUTION TREATED)

-460 -400 TEMPERATURE, °F

-300 - 200 -100

100 150 200 TEMPERATURE, "K

250 300

CHARPY V

TITANIUM CARBIDE

/(SINTERED, 32% Ni)

TUNGSTEN CARBI DE (CA- 10) / (SINTERED, l37oCo )

100 ISO 200 TEMPERATURE, °K

250 300

U.S. GOVERNMENT PRINTING OFFICE: 1963 O—676435
s£
U.S. DEPARTMENT OF COMMERCE

Luther H. Hodges, Secretary

NATIONAL BUREAU OF STANDARDS

A. V. Astin, Director

THE NATIONAL BUREAU OF STANDARDS

The scope of activities of the National Bureau of Standards at its major laboratories in Washington, D.C., and Boulder,

j Colorado, is suggested in the following listing of the divisions and sections engaged in technical work. In general, eacl'i

I section carries out specialized research, development, and engineering in the field indicated by its title. A brief description

of the activities, and of the resultant publications, appears on the inside of the front cover. WASHINGTON, D.C.

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I Basic Instrumentation.

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Processes. Mass Spectrometry. Photochemistry and Radiation Chemistry.

Office of Weights and Measures.

I BOULDER, COLO.

i Cryogenic Engineering Laboratory. Cryogenic Equipment. Cryogenic Processes. Properties of Materials. Cryogenic

i Technical Services. CENTRAL RADIO PROPAGATION LABORATORY

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J

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