Download - XI. MECHANICAL PROPERTIES - a passion for discovery. MECHANICAL PROPERTIES CONTENTS A. Aluminum 1. ... the Mechanical Properties, ... in Metals Handbook, Am. SOC. Metals, 1948, p 204.

X I . MECHANICAL PROPERTIES

CONTENTS

A . A l u m i n u m 1. 1 1 0 0 2 . 6 0 6 1

B. S t a i n l e s s Steel 1. 3 0 2 2. 303 3. 3 0 4 4 . 3 1 0

5. 3 2 1 6. 347

C. S u p e r All.oys 1. I n c o n e l 2 . Inconel X 3. K M o n e l

D. Al loy S t e e l s 1. 2 8 0 0 ( 9 % N i )

E . C o p p e r a n d M i s c e l l a n e o u s A l l o y s

1. C o p p e r 2 . B e r y l l i u m C o p p e r

3. 70/30 Brass 4 . I n v a r

F. P o l y m e r i c Materials 1. Nylon 2. Mylar 3. T e f l o n

4. Kel-F

XI- INDEX- 1

G. Fiber-Reinforced Plastics, 1. Epoxy 2. Phenolic 3. Polyester

4. High-Temperature Polyester 5. Silicone

H. Titanium

XI-INDEX-2

UTS

PSI

KSI

O F

HR

MIN

IN.

MM

DIA

FT-LB

BTU

WQ

OQ

AC

FC

R

Kt

LONG.

TRANS

DPH

NOL

ABBREVIATIONS AND T E R M S 111 t imate tensile strength

pounds per square inch

1000 pounds per square inch

degrees Fahrenheit

hour, hours

minute, minutes

inch, inches

mi I1 ime t er , mi 1 1 ime t e rs

diameter

foot-pounds

British Thermal Units

water quench

oil quench

air cool

furnace cool

stress ratio (minimum stress/maximum stress in fatigue tests)

theoretical stress concentration factor, according to Peterson's data

longitudinal grain direction

transverse grain direction

Diamond Pyramidal Hardness

Naval Ordnance Laboratory

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XI- i

~ A l l of t h e mechanical p r o p e r t i e s d a t a i n t h i s s e c t i o n

are presented g raph ica l ly . For t h e m a t e r i a l s l i s t e d t h e follow-

ing proper t ies a r e included w h e r e ava i lab le :

a . Yield S t rength (0 .2% o f f s e t ) b . Tens i le Strength c . Elongation d . Weld Tens i le Strength e . S t r e s s - s t r a i n Diagram f . Modulus of E l a s t i c i t y g . Impact Strength m. Compressive Strength 0. Fatigue Strength

The da t a sheets marked " * * I ' have been reproduced from:

"Cryogenic Materials Handbook" AD 609 562 F.R. Swartzberg, e t a l . The Martin Company Denver, Colorado August 1964

The a t tached l i s t of re ferences are given as t h e o r i g i n a l sources of t h e m a t e r i a l presented i n t h e above document.

X I - i i

by Mar t in 1. Data o b t a i n e d f o r Company, Denver, C ~ L o ~ a d o , under A i r Force c o n t r a c t AF33(657)- 9 1 u .

2. K. A. Warren and R. P. Reed: T e n s i l e and Impact P r o p e r t i e s of S e l e c t e d Materials f r o m 20 t o 300'%. Monograph 63. Na t iona l Bureau of S tandards , June 1963.

3 . K. E . Mowers: Program of T e s t i n g Nonmetal l ic Materials a t Cryogenic Temperatures , F i n a l Report . RTD-TDR-63-11. Rocketdyne, December 1962.

4. R. J. Favor et a l a : I n v e s t i g a t i o n of F a t i g u e Behavior of C e r t a i n ' Al loys i n t h e Temperature Range of Room Temperature to -423'F. WADD TR 60-123. Bat te l le Plemarial I n s t i t u t e , June 1961.

5. D . N . Gideon e t a l . : I n v e s t i g a t i o n of Notch F a t i g u e Behavior of C e r t a i n Alloys i n t h e Temperature Range of Room Temperature t o -423OF. ADS-TDR-62-351. Bat te l le Memorial I n s t i t u t e , A p r i l 1962.

6 . Data ob ta ined f o r Cryogenic M a t e r i a l s Data Handbook by Cryo- gen ic Engineer ing L a b o r a t o r i e s , Na t iona l Bureau of S tanda rds , under A i r Force c o n t r a c t AFO4(647)-59-3.

9 . J. F. Watson and J.. L. C h r i s t i a n : Low Temperature P r o p e r t i e s of Cold Ro l l ed AIS1 Types 301, 302, 304L, and 301 S t a i n l e s s S t e e l Shee t . Spec. Tech. Pub. 257. ASTM, 1960, p 170 t h r u 193.

LO. J. L. C h r i s t i a n : P h y s i c a l and Mechanical P r o p e r t i e s of P r e s - s u r e Vessel M a t e r i a l s f o r App l i ca t ion i n a Cryogenic. Environ- - ment. ASD-TDR-62-258. General D ~ a m i c s ~ A s t r o n a u t i c s ~ March 1962.

11. J. F. Watson e t a l . : S e l e c t i o n of M a t e r i a l s f o r Cryogenic App l i ca t ions i n Missiles and Aerospace Vehic les . MRG-132. Conva i r /As t ronau t i c s , February 1960.

12. J. W . Spre tnak e t a l . : "Notched and Unnotched T e n s i l e and F a t i g u e P r o p e r t i e s of Ten Engineer ing Alloys a t 25OC and 196°F.' ' T rans , Am. Soc. Metals , Vol 43, 1951, p 547 .

,

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XI-iii

13.

14.

15.

16.

1 7 .

18.

19.

20.

21.

22.

23.

R. L. McGee e t a l . : The Mechanical P r o p e r t i e s of C e r t a i n A i r c r a f t S t r u c t u r a l Metals a t Very LQW Temperatures. WADC TR 58-336. Ba t t e l l e Memorial I n s t i t u t e , November 1958.

J. L. C h r i s t i a n : Mechanical P r o p e r t i e s of Titanium and Titaniums Alloys a t Cryogenic Temperatures. MRG-189. Con- v a i r f A s t r o n a u t i c s , October 1960.

F. R. Schwartzberg e t a l . : Determination of Low Temperature Fa t igue P r o p e r t i e s of Aluminum and Titanium Al loys , Annual Summary Report. Mart in Company, Denver, Colorado, J u l y 1963. Prepared under NASA c o n t r a c t NAS8-2631.

R. P. Mikesel l and R. P. Reed: The R e s u l t s of t h e I m p a c t Tes t ing of Copper Alloys. Memo AT(29-1)-1500. Report t o US Atomic Energy Commission. Cryogenic Engineering Labora- t o r i e s , Na t iona l Bureau of Standards, 1958.

V . N . Krivobok and A . M . Ta lbo t : "Ef fec t of Temperature on t h e Mechanical P r o p e r t i e s , C h a r a c t e r i s t i c s , and Processing of Aus ten i t i c S t a i n l e s s S t e e l s . " Proc. Am. SOC. Test ing Mate-

-9 r i a l s V o l 50, 1950, p 895.

R . H . Kropschot e t al.: Low Temperature T e n s i l e T e s t i n g Equipment and R e s u l t s (300-20°K). Report 2708. Cryogenic Engineering Labora to r i e s , Nat ional Bureau of Standards, J u l y 1953.

E . T. Wessel: "Some Exploratory Observations of the T e n s i l e P r o p e r t i e s of Metals a t Very Low Ter-peratures .I1 Trans. Am. SOC. Metals, Vol 49, 1957, p 149..

V . N . Krivobok and R. D. Thomas, Jr: A u s t e n i t i c S t a i n l e s s S t e e l s . " Welding J. Research Supple- @, September 1950.

V . A r p e t a l . : "Thermal Expansion of Some Engineering Mate- r i a l s from 20 t o 293°K." Cryogenics, Vol 2 , No. 4 , June 1962.

R. A. Baughman: Gas Atmosphere E f f e c t s on M a t e r i a l s . WADC TR 59-511.

"Impact T e s t s of Welded

General E l e c t r i c Go, May 1960.

J. Dyment and H. Ziebland: The T e n s i l e P r o p e r t i e s of Some P l a s t i c s a t Low Temperatures. Report 24fRf55. Explosives Research and Development Establ ishment , Essex, England, November 1955.

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XI- i v

24.. 3 . Dyment and H. Z ieb land : "The T e n s i l e P r o p e r t i e s of Some P l a s t i c s a t Low Temperatures ." (London), Vol 8 , 1958, p 203.

J o u r n a l of Appl ied Chemis t ry

25. H. L. Laquer ,and E. L. Head: Low Temperature Thermal Expan- s i o n of P l a s t i c s . AECU-2161. Los Alamos S c i e n t i f i c Labora- t o r y , September 1952.

26. F. Nix and D . MacNair: "The Thermal Expansion of P u r e Metals: Copper, Gold, Aluminum, Nicke l , and I ron . " 1941, p 597.

Phys. Rev., Vol 60,

I 27. F. M . Howell: "Low-Temperature P r o p e r t i e s and A p p l i c a t i o n s

Engineer Research and Development of Aluminum Al loys Low-Temperature Service. L a b o r a t o r i e s , E o r t Bebvoi r , V i r g i n i a , May 1952, p 253. A l s o , see Alcoa Research L a b o r a t o r i e s Report 9-M-214, November 1953.

Conference on M a t e r i a l s and Desipn f o r

28. Data from Armco S t e e l Corp, Middletown, Ohio, as quoted i n Defense Materials In fo rma t ion Center Report 112, B a t t e l l e Memorial I n s t i t u t e , Columbus, Ohio, 1959.

29. I n v e s t i g a t i o n of t h e I n f l u e n c e of Chemistry on Low-Temperature Behavior of Ti tan ium Al loys . Data B u l l e t i n EFE. Ti tan ium Metals Corp of America, May 1962.

30. M. G . Fontana: I n v e s t i g a t i o n of Mechanical P r o p e r t i e s and P h y s i c a l Me ta l lu rgy of A i r c r a f t Al loys a t Very Low Tempera- - t u r e s . Foundat ion , October 1948.

WADC TR 5662 P a r t 11. Ohio S t a t e U n i v e r s i t y Research

31. J . L. Zambrow and M . G . Fontana: 'Nechan ica l P r o p e r t i e s , I n c l u d i n g F a t i g u e , of A i r c r a f t A l loys a t Very Low Temperatures . ' I

Trans . Am. Soc. Metals, Vol 41, 1949, p 480.

32. J. L. Zambrow and M. G . Fontana: "Impact S t r e n g t h and Hard- n e s s o f A i r c r a f t A l loys Down t o -423QF. '' Metal P r o g r e s s , V o l 53, L948, p 97.

33. M. P. Hanson and M. T. Richards : Smooth and Sharp-Notch P r o p e r t y V a r i a t i o n s f o r S e v e r a l Heats of Ti-6Al-4V Sheet a t Room and Cryogenic Temperatures . NASA TN D-1282. L e w i s Research Center , May 1962.

34. Some P r o p e r t i e s of I n c o Nicke l Alloys a t Low Temperatures . The I n t e r n a t i o n a l N i c k e l Co, New York, 1956.

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XI-v

35.

36.

37.

38.

39.

40.

41.

42.

43.

44.

45.

46.

S t a i n l e s s S t e e l Handbook. Allegheny Ludlum S t e e l Corp, P i t t s b u r g h , Pa . , 1951, p 67.

H. L. Johnston and H. E . Brooks: Impact S t r e n g t h of Various Metals a t Temperaturks Down t o 20" Absolu te . Tech. Rep . 264-17. Ohio S t a t e U n i v e r s i t y Research Foundat ion, May 1952.

M. P . Hanson e t a l . : Sharp-Notch Behavior of Some High S t r e n g t h Shee t Aluminum Al loys and Welded J o i n t s a t 75, -320, and -423°F. Spec. Tech. Pub. 287. ASTM, 1960.

Union Carb ide and Carbon Research Labora tory d a t a , a s quoted i n Metals Handbook, Am. SOC. Metals, 1948, p 204.

C . A . Swenson: "The Mechanical P r o p e r t i e s of Some Techn ica l Metals i n Compression between 4 .2 and 300°K.'' Advance's i n Cryogenic Engineer ing , Plenum P r e s s , N e w York, Vol 1, 1954, p 251.

G . B . Espey e t a l . : Sharp-Edge-Notch T e n s i l e C h a r a c t e r i s t i c s of S e v e r a l High-St rength Ti tan ium Sheet Al loys a t Room and Cryogenic Temperatures . Spec. Tech. Pub. 287. ASTM, 1960.

J . L. C h r i s t i a n : Mechanical P r o p e r t i e s of High-Strength Shee t Materials a t Cryogenic Temperatures . ERR-AN-255. Genera l Dynamics/As t r o n a u t i c s , November 1962 ,

H. E . Brooks and H. L. Johns ton: Hardness of Var ious Metals a t Temperatures Down t o 20°K. Tech. Rep. 264-20. Ohio S t a t e U n i v e r s i t y Research Foundat ion, May 1952.

J. L. C h r i s t i a n : Mechanical P r o p e r t i e s of Aluminum Al loys a t Cryogenic Temperatures . MRG-190. ConvairIAs t r o n a u t i c s , December 1962.

R . P . Mikese l l and R . P . Reed: "The Impact T e s t i n g of Vari- ous Al loys a t Low Temperatures .If Advances i n Cryogenic Engi- n e e r i n g , Plenum P r e s s , N e w York, Vol 3 , 1957, p 316.

R. M. McClintock: Copper and Four Bronzes." ASTM B u l l e t i n , Vol 240, 1959, p 47.

J . L. C h r i s t i a n and A. H u r l i c h : P h y s i c a l and Mechanical P r o p e r t i e s of P r e s s u r e Vessel M a t e r i a l s f o r App l i ca t ion i n Cryogenic Environment. ASD-TDR-62-258, P a r t 11. Genera l D y n a m i s s / A s t r o n a u t i c s , A p r i l 1963.

"Low Temperature T e n s i l e P r o p e r t i e s of

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XI-Vi

47. D. E. Furman: "Thermal Expansion C h a r a c t e r i s t i c s of S t a i n - less S t e e l s between -300°F amd 1000°F.'' J. Metals, Vol 188, 1950, p 688.

48. Technical d a t a on Allegheny Ludlum a l l o y A-286. Allegheny- Ludlum S t e e l Corp, P i t t s b u r g h , Pa . , 1952.

49. Haynes Al loy No. 25. Haynes S t e l l i t e CQ, Kokomo, Ind., 1957.

50. L. P. Rice e t a l . : The Evaluation of t h e E f f e c t s of Very Low Temperatures an the P r o p e r t i e s of A i r c r a f t and Miss i l e Metals . WADD TR 60-254. BatteEle Memorial I n s t i t u t e , February 1960.

51. F. R. Schwartsberg and R. D. Keys: Mechanical P r o p e r t i e s of 2000 S e r i e s Aluminum Alloys a t Cryogenic Tempera tures . R-61-32 Martin Company, Demver, Colorado, October 1961.

52. E. W . Colbeck and W . E . MacGill ivray: "The Mechanical Proper- t ies of Metals a t Low Temperatures, P a r t 11." Trans. I n s t . of Chem. Engrs. (London), Vol 11, 1933, p 107.

53. R. Markovish and F. E%. Sshwartzberg: Tes t ing Techniques and Evaluation of Materials f o r Use a t L i q u i d 3 d r o g e n Temperature. Spec. Tech. Pub. 302. AS"SPI, 1961, p 113.

54. W. D. Jenkins and 'E. G . Digges: "Effect of Temperature on t h e Tens i l e P r o p e r t i e s of High-Purity Nickel." J. Research - NBS, Vol 48, 1952, p 313.

J. H. Hoke e t a l . : a t Subzero Temperatures." Metal Progress , Vol 55, 1949, p 643.

55. "MechznisaE P r o p e r t i e s of S t a i n l e s s S t e e l s

56. J. F. Watson and J. L. C h r i s t i a n : The E f t e c t of Cryogenic Temperatures on t h e Mechamical P r o p e r t i e s of High S t r enk th Sheet Alloys (Cold Worked A u s t e n i t i c S t a i n l e s s S t e e l s ) . ERR-AN-003. General Dynamics/Astronautics, May 1960.

57. P. L. Teed: The P r o p e r t i e s ~f Metallic Materials a t Low T e m p e r a t u E . John Wiley and Sons, New York, 1950.

58. R. H. Henke: "Low Temperature P r o p e r t i e s of t he A u s t e n i t i c S t a i n l e s s Skeels." Prod. Eng., Vol 2 0 , 1949, p 104.

59. J. F. Watson and 9. L. C h r i s t i a n : Low-Temperature P r o p e r t i e s of K-Monel, Inconel-X, Rene 41, Haynes 25, and H a s t e l l o y B Sheet Alloys. Paper 61-WA-12. A%E, 1962..

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XI-vii

60.

61.

62.

6 3 .

64.

65 .

66.

67.

69.

70.

71.

H . W. Altman e t a l . , Ohio S t a t e U n i v e r s i t y unpubl ished d a t a , as quoted by H . L. Laquer i n Document 3706, O f f i c e of Tech- n i c a l S e r v i c e s , US Department of Commerce, 1952.

T. S . DeSis to : Automatic I m p a c t T e s t i n g t o 8°K. Tech. Rep. 112/93. Watertown Arsena l L a b o r a t o r i e s , J u l y 1958.

T . Rubin e t a l . : " C o e f f i c i e n t s of Thermal Expansion of S o l i d s a t Low Temperatures , I. The Thermal Expansion of Copper from 15 t o 300°K." J . Am. Chem. SOC., Vol 76, 1954, p 5289.

I . Estermann and J . E . Z imerman: "Heat Conduction i n Al loys a t Low Temperatures . ' ' J . A p p l . Phys. , Vol 23, 1952, p 578.

J . C. Campbell and L. P. R i c e : P r o p e r t i e s of t h e P r e c i p i t a t i o n - Hardening S t a i n l e s s S t e e l s and Low-Alloy High-St rength S t e e l s a t Very Low Temperatures . Spec. Tech. Pub. 287. ASTM, 1960, p. 158.

T . N . Armstrong e t a l . . : " P r o p e r t i e s A f f e c t i n g S u i t a b i l i t y of 9 P e r c e n t N icke l S t e e l f o r Low-Temperature Serv ice ." Welding J . Research Supplement, February 1959.

J . C . Hamaker J r . , and E . J. Vater: Carbon: S t r e n g t h R e - l a t i o n s h i p s i n 5 P e r c e n t Chrominum Ultra-High S t r e n g t h S t e e l s . P r e p r i n t 80. ASTM, 1960.

G . Sachs and J. G . S e s s l e r : E f f e c t of S t r e s s Concen t r a t ion on T e n s i l e S t r e n g t h of Ti tanium and S t e e l A l loy Shee t a t Var ious Temperatures . Spec. .Tech. Pub. 287. ASTM, 1960, p 122.

C . F. Lucks and H. W. D e e m : Thermal P r o p e r t i e s of T h i r t e e n Metals. Spec. Tech. Pub. 227. ASTM, 1958, p 1.

H. W . Altman e t a l . : C o e f f i c i e n t s of Thermal Expansion of S o l i d s a t Low Temperatures , P a r t 11. Tech. Rep. 264-19. Ohio S t a t e U n i v e r s i t y Research Foundat ion. A s quoted by R . J. C o r r u c c i n i and J . J . Gniewek i n NBS Monograph 29, 1961.

R. W . Powers e t a l . : The Thermal Conduc t iv i ty of Meta ls and Al loys a t Low Temperatures , P a r t 11. Tech. Rep. 264-6. Ohio S t a t e U n i v e r s i t y Research Foundat ion, 1951. A s quoted by R. L. Powell and W . A. Blaqpied i n NBS C i r c u l a r 556, 1954.

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X I - v i i i

72. R . L. Powel l e t al.: "Low Tempera ture T r a n s p o r t P r o p e r t i e s of Commercial Metals and A l l o y s , 11." 3 1 , 1960, p 496.

J. App. Phys . , Vol

73 . H. W . ALtman e t a l . : C o e f f i c i e n t of Thermal Expans ion o f S o l i d s , P a r t 111. Tech. Rep, 264-27. Ohio S t a t e U n i v e r s i t y R e s e a r c h F o u n d a t i o n , 1954. As q u o t e d by R . J . C o r r u c c i n i a n d J . J. Gniewek i n NBS Monograph 29, 1961.

74. R. W . Powers e t a l . : The Thermal C o n d u c t i v i t y of M e t a l s and A l l o y s a t Low T e m p e r a t u r e s , P a r t 111. Tech. Rep. 264-8. Ohio S t a t e U n i v g r s i t y R e s e a r c h F o u n d a t i o n , 1951. As q u o t e d by R . L. P o w e l l a n d W. A . B l a n p i e d i n NBS C i r c u l a r 556, 1954.

75. E . H. Schmidt : "Low Tempera ture Impact of Annealed and S e n s i t i z e d 18-8. I' Metal P r o g r e s s , November 1948, p 698.

76. C . F . Hickey, Jr.: Mechanica l P r o p e r t i e s o f T i t a n i u m and Aluminum A l l o y s a t C r y o g e n i c T e m p e r a t u r e s . a t Annual ASTM M e e t i n g , N e w York, J u n e 1962.

P a p e r p r e s e n t e d

77. C. H. C u r l 1 and G . M. O r n e r : C o r r e l a t i o n of S e l e c t e d S u b s i z e Charpy Bars vs t h e S t a n d a r d Charpy Bar. Tech. R e p . 112/91 . Watertown A r s e n a l L a b o r a t o r i e s , 1958.

78. H . J. F r e n c h : "Some A s p e c t s of H a r d e n a b l e A l l o y S t e e l s . " T r a n s a c t i o n s of t h e American I n s t i ' u t e of Metal E n g i n e e r s , Vol 206, 1956, p 770.

79. C. J . Guntner and R. P. Reed: "Mechanical P r o p e r t i e s of Four A u s t e n i t i c S t a i n l e s s S t e e l s a t Tempera tures Down t o 20°K. It Advances i n Cryogenic E n g i n e e r i n g , Plenum P r e s s , N e w York, V o l 6 , 1961.

80 . R . K. K i r b y : "Thermal Expansion of P o l y t e t r a f l u o m e t h y l e n e ( T e f l o n ) f rom -190" t o 3 O O 0 C . " J. R e s e a r c h NBS, Vol 57; 1956, p 91.

81. J. H . B e l t o n e t a l . : M a t e r i a l s f o r Use a t L i q u i d Hydrogen Tempera ture . Spec . Tech. Pub. 287. ASTM, 1960, p 108.

82 . H . W . Altman e t a l . : C o e f f i c i e n t s o f Thermal Expansion of S o l i d s a t Low T e m p e r a t u r e s , P a r t I V . Tech. Rep. 264-28. Ohio S t a t e U n i v e r s i t y Research F o u n d a t i o n . A s q u o t e d by R. J. C o r r u c c i n i and J. J . Gniewek i n NBS Monograph 29, 1961.

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XI- ix

83.

84.

85.

86.

87.

88.

.89.

90.

91.

92.

93.

F. R. Schwartzberg and R. D. Keys: "Mechanical P r o p e r t i e s of an Alpha Ti tanium A l l o y a t Cryogenic Temperatures." Proceedings of ASTM, Uol 62, 1963, Q 816.

J. L. C h r i s t i a n and J. F. Watson: Mechanical P r o p e r t i e s of S e v e r a l 2000 and 6000 S e r i e s Aluminum Alloys a t Cryogeni.c Temperatures . Gene ra l Dynamics/Astronaut ics . Paper pre- s e n t e d a t Cryogenic Engineer ing Conference, Los Angeles, C a l i f o r n i a , 1962.

J. L. C h r i s t i a n and J. F. Watson: "P rope r t i e s of 7000 S e r i e s Aluminum Al loys a t Cryogenic Temperatures .It Advances i n Cryogenic Engineer ing , Vol 6, 1960, p 604.

C. A. Swenson: "Mechanical P r o p e r t i e s of Te f lon a t Low Temperatures ." Rev. S c i . I n s t r . , Vol 25, 1959, p 134.

B. B. B e t t y and W. A. Mudge: "Some Engineer ing P r o p e r t i e s of Nicke l and High-Nickel Al loys ." Mech. Eng. , VoL 67, 19rt5, p 123.

T. Broom: "The E f f e c t of Temperature of Deformation on t h e E l e c t r i c a l R e s i s t i v i t y of Cold-Worked Metals and Al loys ." Proc. Phys. SOC. (London), V o l 65, 1952, p 871.

C. J . S m i t h e l l s : Metals Reference Book. I n t e r s c i e n c e Pub- l i s h e r s , N e w York, 1949.

P. L. Teed: " A i r c r a f t Metallic Materials under Low Tempera- t u r e Condi t ions ." J. Roy. Aeronaut . SOC., Vol 55, February 1951, p 61.

D. J . McAdam, J r . e t a l . : "Ef fec t s of Combined S t r e s s e s and Low Temperatures on t h e Mechanical P r o p e r t i e s of Some Non- f e r r o u s Meta ls . " Am. S O C . Meta l s , Vol 37 , 1946, p 497.

R . W . Powers e t a l . : The Thermal Conduc t iv i ty of F!etaIs and Al loys a t Low Temperatures , P a r t I. Tech. R e p . 264-5. Ohio S t a t e U n i v e r s i t y Research Foundat ion, 1951. A s quoted by R. L. Powell and N . A. Blanpied i n NBS C i r c u l a r 556, 1954.

G . L. Richards and R . M . B r i ck : "Technical P r o p e r t i e s of Bery l l ium Copper a t Subzero Temperatures ." 6, 1954, p 571c.

J. Metals, Vol

**

XI-x

94.

95.

96.

97.

98.

99.

102.

105.

106.

107.

108.

**

C. H. Lees : "The E f f e c t s of Temperature and P r e s s u r e on t h e Thermal C o n d u c t i v i t i e s of S o l i d s , P a r t 2." P h i l . Trans . Royal S o c i e t y (London), S e r i e s A208, 1908. A s quoted i n NBS C i r c u l a r 556, 1954.

E . W . Colbeck e t a l . : "The Mechanical P r o p e r t i e s of Some A u s t e n i t i c S t a i n l e s s S t e e l s a t Low Temperatuses . ' I Trans . I n s t . Chem. Engrs . (London), Vol 11, 1933, p 89.

D. J. McAdam and R. W . Mebs : and Other Mechanical P r o p e r t i e s of Metals a t Low Temperatures .I1 Proc . ASTM, Vol $3, 1943, p 661.

"The Technica l Cohesive S t r e n g t h

G. W . G e i l and N . L. C a r w i l e : T e n s i l e P r o p e r t i e s of Copper, NickeL, and Some Copper-Nickel Al loys a t Low Tempera tures . C i r c u l a r 520. N a t i o n a l Bureau of S tandards , 1952, p 67.

M a t e r i a l s P r o p e r t y Manual and Summary Report , Con t rac t No. AF33(600)-28469. AL2604. North American A v i a t i o n , Missile Development D i v i s i o n , Downey, C a l i f . , 1957.

Eng inee r ing P r o p e r t i e s . of "S" Monel. N e w York, 1957.

I n t e r n a t i o n a l N icke l Co,

G . E. Espey e t aL.: Some F a c t o r s I n f l u e n c i n g t h e F r a c t u r e Toughness of Shee t Alloys f o r Use i n Lightweight Cryogenic Tankage. Spec. Tech. Pub. 302. AS'IM, 1961, p 140 t h r u 165.

P. J. S o l t i s : Eva lua t ion of C r u c i b l e S t e e l Company of A m e r i c a B-120VCA Ti tan ium Alloy: NAMC-AML-Ak 1108. A e r o n a u t i c a l Materials L a b o r a t o r i e s , Naval A i r Material Center , December 1959.

H. W . G i l l e t t : Impac t R e s i s t a n c e and T e n s i l e P r o p e r t i e s of Metals a t Subatmospheric Temperatures . Spec. Tech. Pub. 47. ASTM, 1941.

J. L. C h r i s t i a n e t a l , : Mechanical P r o p e r t i e s of Ti tan ium - 5A1-2.5Sn Al loy a t Room and Cryogenic Temperatures . Paper t o be pub l i shed by ASTM.

J. J. M . Beenaker and C. A. Swenson: "TotaJ Thermal Cont rac- t i o n s of Some Techn ica l Metals t o 4.2"K." Rev. S c i . I n s t r . , Vol 26, 1955, p 1204. A s quoted by R. J. C o r r u c c i n i and J. J. Gniewek i n NBS Monograph 29, 1961.

X I - x i

109. R. D. McCammon and H. M . Rosenberg: "The Fa t igue and U l t i - mate T e n s i l e S t r e n g t h s of Metals between 4.2 and 293OK.l' Proc . Roy. SOC. (London), Vol 242, 1957, p 203.

110. R. K. MacCrone e t a l . : "The F a t i g u e of Metals a t 1.7"K." P h i l . Mag., Vol 4 , 1959, p 267.

111. M . P. Hanson: Smooth and Sharp-Notch T e n s i l e P r o p e r t i e s of Cold-Reduced AIS1 301 and 304L S t a i n l e s s S t e e l Shee t a t 75, -320, and -423OF. NASA TN D-592. L e w i s Research Center , February 1961.

112. J. L. C h r i s t i a n : Mechanical P r o p e r t i e s of High-Strength Shee t Materials a t Cryogenic Temperatures. ERR-AN-255. Genera l Dynamics/Astronaut ics , 28 November 1962.

113. V . N . Krivobok: P r o p e r t i e s of A u s t e n i t i c S t a i n l e s s S t e e l s a t Low Temperatures . C i r c u l a r 520. Na t iona l Bureau of S tandards , 1952, p 112.

114. N . 0. Br ink: Determinat ion of t he Performance of P l a s t i c Laminates under Cryogenic Temperatures. ASD-TDR-62-794. Narmco Research and Development, February 1963.

115. J. F. Watson and J . L. C h r i s t i a n : Mechanical P r o p e r t i e s of High S t r e n g t h 301 S t a i n l e s s S t e e l Shee t a t 70, -320, and -423°F i n t h e Base Metal and Welded J o i n t Conf igura t ion . Spec. Tech. Pub. 287. ASTM, 1960, p 136 t h r u 149.

116. C. V . Lovoy: Low-Temperature Mechanical P r o p e r t i e s of X2020-T6 and 2219-T6 Aluminum Sheet Al loys . IN-PWE-M-62-3. Marsha l l Space F l i g h t Cen te r , May 1962.

117 . W . R . Morgan: Mechanical P r o p e r t i e s of 2219-T87 Al lov P l a r e a t Room and Cryogenic Temperatures. IN-P&VE-M-62-9. Marsha l l Space F l i g h t Cen te r , October 1962.

123. P. C . Miller: Low-Temperature Mechanical P r o p e r t i e s of S e v e r a l Aluminum Al loys and t h e i r Weldments . MTP-S@l-M-61-16. Marsha l l Space F l i g h t Cen te r , October 1961.

**

XI-xii

30

25

20

15

1Q

5 .

0 -

I I I H16. 0.750-IN. L , I A BAR (12, 30. 31) I I

-

-

-

.

I I I

+O. 0.750-IN. DIA BAR (2)

-400 - 300 - 200 - 100 0 100

TEMPERATURE ( O F )

TRENGTH OF 1100 ALUMINUM

**

XI-A-1.1

60

50

40

30

20

10

0 - 400 -

TENSILE STRENGTH OF 1100 ALUMINUM

300 - 200 - 100

TEMPERATURE (OF)

0 100

XI-A-1.2

60

50

n 40 I- z W u IL: W n W

10

0

t- i -400 - 300 - 200 - 100 0 100

TEMPERATURE (OF)

ELONGATION OF 1100 ALUMINUM

**

XI-A-l . 3

**

60

50

40

30

20

a

ALUMINUM

XI-A-1.4

12

1 1

10 -400 -300 - 200 - 108 0 . 100

TEMPERATURE ( O F )

MODULUS

1 20

90

60

36

Q -400 - 308 - 200 - 100

TEMPERATURE ( O F )

IMPACT IF **

XI-A-1.5

%- * 50 -

40

i

0. \- e

NOTE: H l 6 (17.5 KSI UTS), FLEXURE, - R = -1 , 0.750-IN. 01.4 BAR (12, 30, 31)

io" 10' I o4 lo5 FATIGUE LIFE (CYCLES)

FATIGUE STRENGTH OF 1100 ALUMINUM

. 1 o6 I o7

7 5 x Id-

70

FLEXURE; 3/4

TENSILE STR: 19 5 K S I ; R = - I , 2000 GPM; CYGLES NOTED [30]

IN DlA Fi30; C O N D l T i O N NOTED,

- 4 6 0 -400 -300 - 2 0 0 -100 0 100 2 0 0 300 400 500

TE Ll PE RAT URE , O F FATIGUE STRENGTH OF lS00 ALUhlIPdUFif

XI-A-1.7

c ! I

0

XI-A-1.8

20

10 -400 -3QQ - 200 - 100

**

XI-A-2.1

100

90

80

70

60

50

40

3( -400 -300 - 200 - 100

TEMPERATURE (OF)

0 100

TENSILE STRENGTH OF 6061 ALUMINUM

**

XI-A- 2.2

35

30

25

20

15

10

5

0 -400

ELONGATION 1

-300 - 200 - 100

TEMPERATURE (OF)

100

XI-A- 2 . 3

80

70

60

50

40

30

20 -400 -300 - 200 - 100

TEMPERATURE ( O F )

0 100

WELD TENSILE STRENGTH OF 6061 ALUMINUM

**

XI-A-2.4

12-

-

1 1 -

-

10 -

-

9 -

- m + I- LL

W

v

n m

m a

a

8 cn

> 13 Lal z W

20

15

10

4

- 400 - 300 - 200 - 100

TEMPERATURE (OF)

100

MODULUS OF AL

I I . I I I I I NOTE: TG, CHARPY V, EXCEPT AS

'NOTED. - I I I I

V I I I I / I 1 0 .500- IN. P L A T E ( I ) I I I CHARPY K 0 750-IN. D I A BAR (12, 3b,

I 1 I Y

-400 -300 - 2QQ - 106 6 100

IMPACT STRENGT **

XI-A-2.5

I

/ f /

0

In

0

0

8 h

W

7,. D - I

( ISd EOl

SS

3tlLS

XI-A-2.6

28C

200

cn ul W

ul F 120

I I I I I 1 I NOTE: LONGITUDINAL DIRECTION - F O R SHEET M A T E R I A L .

I I /t COLD REDUCED, 0.750-IN. D I A BAR (2) I I I

80

40

0 -400 - 300 - 200 - 100 1 QO

TEMPERATURE (OF)

YIELD STRENGTH %EEL

**

XI-B-1- 1

360

3 20

250

240

20c

16[

1 2(

81

\

TEMPERATURE (OF)

**

XI-B-1.2

120

I I I / 80

I I I I I I 1

0" - 300 - 200 - 100 0 -400

TEMPERATURE ( O F )

**

XI-B-1.3

. 3501=LLLLL 300

250

200

150

100

50

0

e

0

S T R A I N (INCHES P E R INCH)

STRESS-STRAIN DIAGRAM FOR 302 STAINLESS STEEL

**

XI-B-L .4

a 35

30

25

TEMPERATURE ( O F )

MODULUS OF ELASTICITY OF LES

125

100

75

50

I I I I -400 - 300 - 200 - 100 0

TEMPERATURE ( O F /

IMPACT STREN

**

XI-B-1.5

11.0

10.8

10.6 -400 -300 -200 - 100

TEMPERATURE (OF)

12.0

11.8

0

M O D U L U S OF RIGIDITY OF 302 STAINLESS STEEL

**

XI-B-1.6

100

28C

240

200

I60

120

80

40

0 -400 -300 - 200 - 100 160

~

STRENGTH ?E

** a XI-B-2.1

TEMPERATURE ( O F )

ELONGATION OF 303 STAINLESS STEEL

0

TEMPERATURE ( O F )

REDUCTION OF AREA OF 303 STAINLESS STEEL

**

XI-B-2.2

E m E! - m m W I- m a

3 26

280

240

200

160

I20

8Q

40

0 0.200 0.400 0.608 0.800 1. 0 DO

STRAIN (INCHES PER INCH)

STRESS-STRAIN DIAGRAM FOR 303 STAINLESS STEEL **

XI-R-2.3

35

30

25 -400 - 300 - 200 -100

TEMPERATURE (OF)

0 100

MODULUS OF ELASTICITY OF 303 STAINLESS STEEL

160

120

80

40

0

I I I I I I

I I I I I I / I

I I ANNEALED, CHARPY U, 0.750-IN. DIA BAR ( 2 ) q I I

-400 -300 - 200 - 100

TEMPERATURE (OF)

Q 100

IMPACT STRENGTH OF 303 STAINLESS STEEL

**

XI-B-2.4

a 140

120

100

80

60

40

20

0 -400 -300 - 200 - IQO IO8

TEMPERATURE (OF)

**

XI-B-3.1

390

350

310

- I m a 270

m m W E 230 m

190

15C

1 I (

-t-- '-I

t -400 -300 -200 -100

TEMPERATURE (OF) 0 100

YIELD STRENGTH OF 304 STAINLESS STEEL

**

XI-B-3.2

27 f

25c

225

200 - - m Q

m 2

175 m m W IJL c ul

150

125

IO0

75

XI-B-3.3

390

350

,- THREE-QUARTER H A R D (40% COLD R E D U C T ION), - 0.063-IN. S H E E T (115)

-400 -300 -200 -100 0

TEMPERATURE (" F)

TENSILE STRENGTH OF 304 STAINLESS STEEL

180

XI-B-3.4

e 120

100

80

60

4c

2(

TEMPERATURE ( O F )


QO

XI-B-3.5

5(

4c

3c

2a

10

0

I I I I I

NOTE: E X T R A LOW CARBON GRADE, - 0.063-IN. S H E E T (115).

-400

I

-300 -200 -100

TEMPERATURE ( F)

0


J

100

'XI-B-3.6

290

250

210

170

130

90

50

-r

-+ /

LONG.

- 400 - 300

T R A N S

/

- 280 - 108 Q

TEMPERATURE (OF)

W E L D TENSILE STRENGTH OF 304 STAINLESS STEEL

. XI-B-3.7



XI-B-3 * 8

40 c4 I cn a 0 CD c.

20

EXTRA LOW CARBON GRADE FULL HARD (so 0 COLD REDUCTION), 0.012-IN. SHEET (10)

I I I I

-400 -300 -200 -100 TEMPERATURE (OF)

0 100


XI-B-3 .9

2.1 2.1 2r- I

1.53

1.52

t

1.284

0.282

0.280

- 0.278 > 0

0.276 5 !! z 0 v)

0.274 rn 0 a

v

- E

-

0.272

0.27Q

100 200 300 I ." 0

Temperature, K

TEMPERATURE DEPENDENCE OF YOUNG'S MODUL(.6 THE BULK MQDULLJS, AND POISSON'S RATIC~

384 STAINLESS STEEL

XI-13-3.9.1

120

100

80

60

40

20

0

I I I I I I I I I I

NOTE: ANNEALED EXCEPT A S NOTED. I I I I e D (35)) I-

l l LOW CARBON, SUBSIZE CHARPY V, 0.750-IN. D I A BAR (2) I I

i ! I CHARPY K. '0.750-IN, D I A BAR (75) I

- SUB.SIZE CHARPY V (22)

------

I I L 2 0 % COLD REDUCED CHARPY K, 0.562-IN. D I A BAR (76)

\---COLD REDUCED (211 K S I UTS), CHARPY K 0.750-IN. D I A BAR (12 . 30. 32.' 36) ,

-400 -300 - 200 -100

TEMPERATURE (OF)

0 IO0


XI-B-3.10

280

24 0

-g 200 x m u)

.. E c v)

I 6 0

128

I I I I I I l l I I I I I I I I I I I I 1

lo3 lo4 I o5 I os I o7 IO * Fat igue Life (cycles)

FATIGUE STRENGTH OF 304 STAlNLESS STEEL

0

C : 0

d-

U c

a, U

al -J

5: 0

d

0

E

UJ

0

ci, Y

cc Q

-I w w

I- </> CI) </> w -I 2 I- CI) -I t 0

m

m

- a

XI-B-3.12

fu E \ z H c

ln In 2 c v)

Temperature, F

! 4 0

!OO

60

2 0

.40

!OO

60 ' .

2 0

I O

0. i 00 200 3 00 Testing Temperature,K

EFFECT OF TEMPERATURE ON THE STRENGTH OF TYPE 304L STAINLESS STEEL

XI-B-3.13

280

2 40

200

160

2 80 .- v) -Y

v) v)

”

240 E z

200

I60

I20

80

40

0 Test ing Temperature , K

EFFECT OF TEMPERATURE ON THE STRENGTH OF TYPE 3Q4 STAINLESS STEEL

XI-B-3.15

200

175

150

125

100

75

50

25

TENSILE

YIELD _--- I

-400 -300 - 200 - 100 0 IO0

TEMPERATURE (OF)

STRENGTH OF 310 STAINLESS STEEL

’ XI-B-4 1

80

n 70 I- z W u K W a Z 60 0

U

F: 4 s z

50

40 -400 -300 - 200 - 100 0 100 ,

TEMPERATURE' (OF)


**

SI-B-4.2

26C

2 2c

- - E 18C m 0 - - u) m w E 140 I- m

100

60

**

- 400 -300 -200 - 100 0 100 TEMPERATURE ( O F )

WELD TENSILE STRENGTH OF 310 STAINLESS STEEL

XI-B-4.3

210

180

150

120

90

60

30

0 0

NOTE: ANNEALED, 0,750-IN. - D I A BAR ( 2 )

0,150 0.300 0,450 0.600

S T R A I N ( INCHES P E R INCH)

0.750


**

XI-B-4.4

c

35

30

25

20

-

-

-

.

I I I

TEMPERATURE ( O F )

MODULUS OF ELASTICITY OF 31

90

70

50

30 u= -300 - 200 -100 0 1 -400

TEMPERATURE (OF)

b IMPACT STRENGTH OF 310 STAINLES **

XI-B-4.5

00

120c

IOOC

008

600

400

200 E --.. z H - 0 v) In a 5 1200

IO00

800

680

400

200

0

Temperature, F

-400 -300 -200 -100 0 75 200

Type 310, annealed Plate TUS ( L ) Bar + T U S X TYS

Testing Temperature , K

EFFORT OF TEMPERATURE ON THE STRENGTH OF TYPE 31Q STAINLESS STEEL

XI-B-4 a 6

a 280

240

200

160

120

80

40

0

0--

TENS I I E - - - - YIELD

-400 -300 - 200 -100 0 100

TEMPERATURE ( O F )


** ' . !

XI-B-5.1 1 8

,

F: f W c) K w e v

z I- a 2

s W

4

B Iy1 a

80

60

40

20

100

80

60

40

-400 -300 - 200 - 100 0 100

TEMPERATURE (OF)


-400 -300 -200 -100 0 100

TEMPERATURE (OF)


**

XI-B-5.2

280

240

200

160

120

ao

40

0 0

P 0.120 0.240 0.360 0.480


0.600

STRESS-STRAIN DlA FOR 321 STAINLESS

**

XI-B-5.3

35

30

-400 -300 - 200 - 100 0 100 25

TEMPERATURE (OF)


100

80

60

40

20 - 400 - 300 - 200 -100 0 100

TEMPERATURE (OF)


**

XI-B-5.4

Temperature , F -400 -300 -200 -100 0 7

2000 I [ I I' - 280

240

200

.- v)

160 Y c u) v) a3 L c

120 rA

80

4 0

0 0 100 200 300

Testing Temperature K

EFFECT OF TEMPERATURE ON THE STRENGTH OF TYPE 3 2 1 STAINLESS STEEL

XI-B-5.5

TEMPERATURE (OF)


**

XI-B-6.1

F z W u [1: W a

F:

W

0"

s a (3 z

W

F: z W

W k!

3

8 5

a v

U a

F: n 0 3

W U

75

50

25

0 -400 -300 - 200 - 100 0 100

TEMPERATURE (OF)


**

-400 - 300 - 200 -100 0 100

TEMPERATURE (OF)


XI-B-6.2

m m W U I- m



**

XI-B-6.3

A - UJ a

35

30

25 I I I I I I I I -400 -300 - 200 - 100 0 loo

TEMPERATURE (OF)

MODULUS OF ELASflCITY OF 347 STAINLESS STEEL

80

60

40

20

0

I I ANNEALED, SUBSIZE CHARPY V, 0.710-IN. I d - D I A EAR (2)

- 400 -300 - 200 - 100 0

TEMPERATURE (OF)

100


**

XI-B-6.4

I o5 lo6

FATIGUE LIFE (CYCLES)

1 o8

FATIGUE STRENGTH OF 347 STAINLESS STEEL

I80 a 160

140

120 - m R

m 2 -

100 m m W E l- m

80

a

60

40

20

**

I

i

I .

I

-400 -300 - 280 - 100 0 100

TEMPERATURE ( O F )

YIELD STRENGTH OF INCONEL

XI-c-1.1

200

180

160

140

1 20

100

ea

6C

TEMPERATURE (OF)

TENSILE STRENGTH OF I N C O N E L

**

XI-c-1.2

6C

40

20

0

80

60

40

20

I I I I I - 400 -300 - 200 - 100

TEMPERATURE ( O F )

- 400 -300 - 200 -100 0

**

TEMPERATURE (OF)

REDUCTION

XI-C-1.3

**


STRESSTRAIN DIAGRAM FOR iNCONEL

XI-C-1.4

25 -400 -300 -200 -100 0 100

TEMPERATURE (OF)

250

200

I50

100

50

MODULUS OF EL F [

ED, PERCENTAGE UNKNOWN.

-400 -300 - 2QO - 160 IO0

TEMPERATURE (OF)

IMPACT STRENGTH

**

' XI-C-1.5

J

0

m

0

0

c

co 2

(IS$

EO1) SS

3tfl.S

XI-(2-1.6

190

I50

130

90

70

50 - 400 - 300 - 200 - 100

TEMPERATURE ( O F )

**

XI-e-2.1

TENSILE SfRENGTH OF INCONEL-X

**

XI-c-2.2

TEMPERATURE (OF)

ELONGATION OF INCONEL-X

**

XI-(2-2.3

f

TEMPERATURE (OF)

WELD TENSILE STRENGTH OF INCONEL-X

XI-c-2.4

I m n

E! m - m m u E l- ul

28C

240

200

160

120

80

40

0 0

. - 0.080 0.160 0.240. 0.3 20

STRAlN (INCHES PER INCH)

0.4063

STRESS-STRAIN DIAGRAM FOR IN

XI-C-2.5

TEMPERATURE (OF)

MODULUS OF ELA$TlClM OF INCONEL X

TEMPERATURE ( O F )

IMPACT STRENGTH OF INCONEL X

XI-C-2.6

200

160

I 20

80

40

n

"I o3

FATIGUE STRENGTH OF INCONEL X

200

180

160

m ul W

v) 120

100

80

60 -400 -300 - 200 - 100 IO0

TEMPERATURE (OF)

**

XI-C- 3.1

220

200

180

160

140

1 20

100

80

TEMPERATURE (OF)

TENSILE STRENGTH OF K M O N E L

**

XI-C-3.2

F z w u E W a W

i3

s i= a 13 z

w

h I-

40

30

20

10

z I- t) 3 O W E

s?

SOLUTION TREATED AND AGED

-400 -300 - 200 -108 0 1 QO

TEMPERATURE (OF)

ELONGATII k

i n ." - 400 -300 - 280 - 100 0 100

REDUCTION EL

XI-c-3.3

TEMPERATURE (OF)

WELD TENSILE STRENGTH OF K MONEl

XI-c- 3 . 4

280

- I m n

cr) 0

24 0

200

160

120 in

80

40

0

STRES

XI-6- 3 * 5

rc-̂

.I m a W 2

30

25

- 200 - 100 0 100 -400 -300 20

40

30

20

1c

C

TEMPERATURE (OF)

MODULUS OF ELASTICITY OF K MONEL

TEMPERATURE (OF)

IMPACT STRENGTH OF K MONEL

. XI-C-3.6

200

160

120

80

40

0 '_ I. I I I

NOTE: COLD ROLLED HALF-HARD AN0 AGED (112 KS1 UT91 FLEXURE, R - - 1 . 0.011-lN. SHEET (4).

1 o3 1 O4 I I O5 1 o6 FATIGUE LIFE (CYCLES)

I 0' 1 O8

FATIGUE STRENGTH OF K MONEL

- I

# a 0

m c - # # W p: I- #

220

200

180

160

140

12a

1 oc

8(

YIELD STREN

. .

XI-D-1 1

TEMPERATURE (OF)

TENSILE STRENGTH OF 2800 (9% Nil STEEL

XI-D-1.2

n t- z W u Iy: W a,

z I- (3 z

W

W

2 a

3

40 I 30

20

IO

I I I 1 I I I II I I

I- z w c) !Y W e W

3 a 4 LL 0 z t- u 3

w !Y

2

n

*O I 60

40

20

TEMPERATURE (OF)

TEMPERATURE (OF)

REDUCTION OF AREA

200

1 60

1 20

80

40

STRAlN (INCHES P E R INCH)

STRESS-STRAIN DIAGRAM FOR 2800 (9%Ni) STEEL

XI-D- 1.4

35

30

n W

Y (3 tY W z W

25

MODULUS OF ELASTICITY

160

1 20

80

40

(I

TEMPERATURE (OF)

IMPACT STRENGTH

XI-D-1 5

0 a I

0 0 8 cl 0 N 0 Ift -

( ISd c O I ) SS3MIS

Y LL

I .

XI-p-1.6

3 15OxlO -

I4(

I3(

I2C

I IO

I oc

9C .- v) 0.

cn' 8( v, W a: $j 7c

6C

50

4c

3c

2c

10

0

OFHC, 40°/o COLD DRAWN [453]

-460 -400 -300 -200 -100 0 IQQ 200 300 400 500 TEMPERATURE, "F

STRENGTH OF C

XI-E-1.1

1 20

100

80

60

40

20

0 -400 '-300 -200 , l l .O(I . '

T E M P E R A T U R E ('OF)

'0 100

XI-E-1.2

120

100

80

60

40

20

100 0

-400 -300 -200 - 100

TEMPEEATURE ( O F ' )

XI-E-1.3

100

80

60

40

20

0

- 0 F H C . A N N E A L E D , ‘ - I - T W I R E (45)

- O F H C , 4 0 % COLD REDUCTIOIU, 0 . 2 5 - I N . D t A B A R (45)

-400 -300 - 200 - 100

TEMPERATURE (OF)

XI-E-1.4

( 5 7 )

0 too

h

I- Z w c) lx W a v

100

80

6C

4

21

' XI-E-1.5

I O 0

80

Q

* 60 c .C

c c

L 0)

40

a

20

0 -460 -400 -300 -200 -100 0 100 200 300 400 500

TEMPERATURE, O F

ELONGATlOi.1 OF COPPER

100

80

c 60 C Q)

8 40 L o *

20

0

O F H C , 40% COLD 1 1 DRAWN [453]

XI-E-1.6

m -I

I- LL

Q W

I

W

rn

m 8 m U > 13 E W z W

30

20

-300 - 200 - 100 0 100 10 -400

TE b1P E R A 7% R E ( F )

80

60

40

20 -400 -300 -200 1 co

XI-E-1.7

c\ - m a

s m

c,

m m

t- m 2

40 I

30

20

10 ---+------

STRAIN (IPICI-1ES PER INCH)

i

e

XI-E-1.8

0 0

N

I \ I

-- I I

I I I I /!

I

..1 __

. . . . - . . - .

0

0

hl W

- ( lS

il SSI4H

.l.S

0

-3

XI-E

-l . 9

I

:o

I I

I I

I I

I I

I I

LL 0

'XI-E-1.10

XI-E-1.11

100

90

80

70

60

50

40

30

20

10

0

S T R A I N

700

600

500

200

I O 0

S'i'R E S S - S T R A I N C U R v E S 0 F C 0 P PE F:- N I C K E L C U - I O N l 1 , ANi4EALF-D .

XI-E-1.12

Tempera tu re , F

SO( (u

E \ 60(

.2 00

1 90 Cu - IO N i ( 7 0 6 ) bar , annealed - - __ 0 TUS o T Y S

0 0 100

Tes t ing Tempcraturu, K

EFFECT OFTEMPER2;TURE ON THE S T R E N G T H O F 9 0 ClJ-1ONIALLOY

300

4 0

XI-E-1.13

280

260

24C

2 20

200

180 .- m a

v) tn W CE 140 I- cn

I 160

I20

100

80

0 -460

I I I I I

A SOLUTION TREATED, QUENCHED. AT: SOLUTION TREAT ED, OUENCHED, PRECIPITATION HARDENED. 1/2H; SOLUTION TREATED, QUENCHED, COLD DRAWN I / zHT: SOLUTION TREATED, QUENCHED, COLD DRA'tlN,

I

PREClPlTAT ION HARDENED. I I I

' _ _ _ _ L __I L I___( ____L_

-400 -3CO -200 -103 0 1 9 3 200 3x3 400 E TEMPERATURE, " F

60

40

20 _.".. . .. ~ -TENSILE

Y IELD I I. . .i -.

XI-E-2.1

140

120

100

80

60

40

20 -400 -300 -200 , , -100 . , 0 1

XI-E-2.2

IO

240 I 220

200

180

160

140

120

100

.

0

TEMPERATURE (OF)

XI-E-2.3

IO0

160

- L m a

m w 0: I- cn

140

120

1 ot

81

6

40

TEMPERA1'U'iZE ( O F )

XI-E-2.4 e 1 .

24 0

220

200

180 m 0 c

160

140

120

100 - 200 - 100 0 10 -400 -300

T E M P E R A T U R E (OF)

s

XI-E-2.5

100

80

60

40

20

0

-

-400

I I I A, 0.750-IN. D I A BAR ( 2 )

I I

I A , 0.560-IN. D I A BAR (93)

H, 0 . 1 2 5 - I N . SHEET (45)

TEMPERATUfiE ( O F )

XI-E-2.6

. . .

100

25

20

15

10

E c

(

TEMPERATURE (OF)

XI-E-2.7

100

t c Q)

' 0 L Q) a

. .

TREATMENTS S E E PAGE C.1 o b

' THE BEFiYLLiUt.! CORPORATION OF A h i E F i r c ~

. .

XI-E-:!. 8

a 120

1 oa

00

60

20

a 0

I --!

'-

- - -

0.2 0.4 0.6 0.8

__

-

. I_..-

-

1.0

a XI-E-2.9

II) a F7 0 \s II) II) w I- m a

I6O I

140

120

100

80

60

40

20

0

&

7

. --

- 0.080 I-: 0.

7

- -llO°F

-t- C O N D I T I O N H. 0.750--.IN. D I A EAR (2).

0 0.

7

30

I I . I XI-E-2.10

THIS CURVE IS REPRESENTATI>JE OF A L L FORMS AND INCLUDES TREATMErSTS

H, ‘/2 H T [IOS, 453,7491

. T------ .- - .-

- . __ . . ..

30 .

.- v) 20 - Q

120

10

0

80

.

FOR EXPLANATION OF TREATMENTS SEE PAGE C I ob

40

20

0 -460-400 -300 -200 -100 0 100 200 XO 400 500

TEMPERATURE, OF IMPACT ENERGY OF BEI{YLCO* 25

* THE B E R Y L L I U V CORPORATlOv OF A M E R I C A

XI-E-2.11

ZT * z-3-IX

(A,) 3UflLVEl3dL431

0 001 - ooz- OOE- OOP-

(Ao) 3'dmvJH' a=raN31

00 I 0 001 - 001 - OOE- 00P- st

si?

d

0 W

Temperature, F

-400 -300 -200 -100 0 75 1600

200 1400

I200

160 1000

800 I 2 0

1600 up t o 2 . 5 4 0 cm diam

1400

1200 E \ z H

1000 v) v) +

v) E iz

1600

1400

1200

1000

800

600 0 100 200 300

Testing Temperature, K

EFFECT OF TEMPERATURE ON THE STRENGTH OF CU-2 BE ALLOY

XI-E-2.13

0 W m

m a

8 v)

c?

CD !2

120

80

40

0 -400 -300 - 200 - 100 0 100

T E M P E R A T U R E ( O F )

7.5

7.0

6.5

6.0 -300 - 200 - 100 0 100 -400

TEMPERATLJRE ( O F )

7. :

7. I

7.(

6.5

6. E

6.7

6.6 - n 1

6.5

6.4

6.3

6.2

6.1

6 0

5.9

STANDARD DEVIATION BASED ON 4 TESTS AT -423OF. $0.036 x IO6 PSI STANDARD DEVIATION BASED OM 5 TESTSAT -32O0F:+O.051 x IO6 P S I STANDARD DEVIATION BASED ON 8 TESTS A T - 1 0 7 ° F ' + 0 0 1 0 x 1 0 6 P S I ' STANDARD DEVIATION BASED ON I I T E S T S A T 75°F:t0.021 x IO6 PSI

STANDARD DEVIATION BASED ON 8 TESTS AT -423OF. t0.030 x IO6 PSI STANDARD DEVIATION BASED ON 6 TESTSAT -32OOF: 2 0 0 2 2 x IO6 PSI STANDARD DEVIATION BASED ON 5 TESTSAT - 96OF 20033 x IO6 psi

7 5 O F ' t0.021 x IO6 PSI

- - CONDITION A

- - STANDARD DEVIATION BASED ON 5 TESTS AT

STANDARD DEVIATION J-w WHERE , n NO OF T E S T S AND G = MODULUS OF RIGIDITY

100 200 300 4m 500 5.8 -460 -400 -300 -200 -100 0

TEMPERATURE, OF MODULUS OF RIGIDITY OF BERYLCO *25

*THE BERYLLIUM CORPORATION OF A M E R ~ ~ A

XI-E-2.15

XI-E-2.16

0

0

N

CD c

( ISd

EOl) SS3tl.l.S

XI-E-2.17

I o4 I o5 I06

FATIGUE LIFE, cycles FATIGUE BEHAVIOR OF BERYLCON 25

IO'

160 X K13 I

j TENSILE STR: 191,000 PSI; R = - I , le00 CPM

0 8

THE BERYLLIUM CORPORATION OF WERlCA *

100 x

90

80

-- 70 v) a

v3

M [y: I- I

1\3

to 50 0

- 60 XH I LL]

40

3 0

20 IO

FATIGUE LIFE, cycles FATIGUE BEHAVtOR OF BERYLCO'25

THE BERYLLIUM CORPORATION OF AMERICA

EO x

70

60

.- 5c 0 a

0-3 v) 40 W cr i

L

w 7! ' I

N lo '39 30 P

2 0

IO

FATIGUE LIFE, cycles FATIGUE BEHAVIOR OF BERYLCO"25

' THE B E R Y L L I U M CORPORATION OF AMERICA

I

si m

r- 0 u,

.-

.c .... I I

In In

I

J

2

W I

I- %

XI-E-2.22

LL 0

LL 0

z 0

W I

XI-E-2.23

. .._ . .- t---

_-

- I I

. .

.

..

. - . . . -

. .

. __

-

.

. - . . - __ . . -

.

.

. . . . .

(D 0

'LL- -

0

w

LL

0

2

t 0

W

m

..

r

W

I- *

XI-E-2.24 .

..

65 - .- v) Q

v, v) w rx 55 t-- v,

60

50 -

45

40 __

35 __

30

25 - -

2 0 -- -460 -400

I .

- 300 -2ca - . IO0 0 Ion 2CQ 3c;o 403 500

‘THE BER’ILLlUh‘ CORKlF iAT IO ’~ OF A h l E H l C A

XI-E-:!. 25

I

14C

I30

12c

I I C

9c

( - 4

F L E X U R E ; 0 0 7 8 I N SHEET, C O N D I T I O N

I800 8 3450 CPM; CYCLES NOTED [805] HT, T E N S I L E S T R . 191,000 PSI, R = - I ,

-- I

0 100 200 30 0 4 CO X O

TEMPERATURE, * F FATIGUE STRENGTH OF E3: :FNL-CO**' 25

'THE BERYLLlU!d CORPORATION O F AMERICA

XI-E-2.2 6

17C

I61

15C

I4 C

13C

12 c

I I C .- v) n

9 IOC W [r. t- 9' rn

8C

71

6(

5(

4

3

3

.o'

_ _ ....

3 -

3450 CPM, CYCLE Si;'JTE L [ 835 ] . . 7-- 1 I I I

I I . .

201)

TEPdPERATURE, OF

*THE BERYLLIUM CORPCl3ATlON OF Ah!ERICA

XI-E-2.27

150 to3

14(

I3(

I2(

9c .- cn

v) v) W E 7c c- .u)

6C

5c

4c

30

20

IO

0

[335-

5

-460-400 -300 -200 -103 0 loo 2 0 0 300 400 500 TEht PERATURE, O f

STRENGTH OF 70 / 33 Bi':J\SS

XI-E-3.1

120

100

80

60

40

20

0 - I GO 0 . 100

-100 0

XI-E-3.3

TEMPERATURE (OF)

100

. . t

. . . .

, .

I oc

8C 0 Q .- c 6C

+- C Q,

L a Q

40

.2 0

0

100 200 300 4 0 5P.J -460-400 -300 -200 -100 0 . TEMPERATURE, O F

REDUCTION OF AREA OF 70 / 30 BRASS

e XI-E-3.4

, -

/ 2 0 ° / 0 COLD DRAWN

I I -. -460-400 -300 -200 -100 0 100 200 300 400 533

TEMPERATURE, " F ELONGATION OF 70/30 BRASS

20

0 100 200 300 4 0 5P.J -460-400 -300 -200 -100 0

. TEMPERATURE, O F

REDUCTION OF AREA OF 70 / 30 BRASS

XI-E-3.4

14C

12c

100

80

60

40

20

' -I->-

- O F

0.4 20

XI-E-3.5

20

15

1(

XI-E-3.6

- m -I

I t

6

2

W

a W rn

m m c >-

W Z W

100

XI-E-3 7

E T

I

W

co

I 1 I

'F \ i I I

I

I

I !

40 i

i i

I

I

I 1 I I ! 1 1 1 I I L L ! I

I I I I ! 1 1 I I 1 ! ,

I o5 1 o6 10' 1 o8 4 03 1 o4 FATIGUE LIFE (CYCLES)

XI-E-3.9

m

m

Qs

0

rr) \ 0

t+ LL 0

0

> I

W

W

3

c3 I- LL

a

m

a

a

m

- c

a

XI-E-3

10

i .

.

__

v)

cn Q

tx m

0

M

XI-E-3.11

FATIGUE STRENGTH OF 70/30 BRASS X I - E - 3 . 1 2

XI-E-3.12

STANDARD DEVIATION = d v W H E R E

MODULUS O r RIGIDITY OF 70 / 30 BRASS

XI-E- 3 . 1 3

2-

0’-

lJ ll1

J

-1 -

4 u

-- L1

LLI

i= ii I

-4 .. -.

1 .

. I I

--I---

i I

- -i -

t I

_..- I I

__

.-

=-

XI-E-3.14

TEMPERATURE (OF)

ST

XI-E-4.1

-.I W

60

40

20

0 -200 -100 0 100 -400 -300


ELONGATION OF INVAW

90

7.0

50

30


REDUCTION OF AREA OF INVAR

XI-E-4.2

e u) e

0 u) tn W t- u)

vi 0

a

0 0.060 0.1 2Q 0.180 0.240 0.3 00


STRESS-STRAIN DIAGRAM FOR INVAR

XI-E-4.3

25

20

15

40

30

20

10

0

I 1 1

TEMPERATURE (OF)

MODULUS OF ELASTICITY OF INVAR

I

TEMPERATURE (OF)

IMPACT STRENGTH OF INVAR

XI-E-4.4

35

30

25

20

15

10

5

0

TYPE IO

0.25- I N .

TENSILE

- -Y IELD' --

-400 - 300 - 200 - 100 0 too

TEMPERATURE (OF)

STRENGTH OF NYLON

XI-F-1.1

n I- z W u E W

z 0

c3 z 0 W

a

F a

v

200

160

1 20

80

40

0 - 400 - 300 - 200 - 100 0

TEMPERATURE (OF)

ELONGATION OF NYLON

I00

XI-F- 1.2

1.5

1 .o

0.5

-400 I -300 - 200 - 100 0 100

TEMPERATURE (OF)

MODULUS OF ELASTICITY OF NYLON

- 300 - 200 - 100

. TEMPERATURE (OF)

0 100 -400

IMPACT STRENGTH OF NYLON

XI-F-1.3

TEMPERATURE (OF)

COMPRESSIVE STRENGTH

TEMPERATURE (OF)

MODULUS OF RIGIDITY OF NYLON

I 00

XI-F-1.4

T m. a

m' G 0

70

60

50

40

30

20

10

55% CRYSTALLINITY

-

NOTE: CRYSTALL- SPECIFIC T H E R M A L . - GRAVITY HISTORY INITY.

AS RECEIVED

46OF/l HR, SLOW COOL

CROSSHEAD RATE: l - lN./ l MIN-70F. O . l - I N J M IN-LOWER TEMPERATURES

0.002-IN. FILM. (3).

-400 -300 -200 - 100 0 100

TEMPERATURE (OF)

YIELD STRENGTH OF MYLAR*

* T.M. E. 1. DUPONT DE NEMOURS AND CO.

XI-F-2.1

7c

60

50

40

30

20

10

0

1

I I I I I 1

55 1.39 AS RECEIVED f 46OF/l HR. SLOW COOL

CROSSHEAD RATE: l--IN./MIN--70F, 0. I - lN . /MlN- LOW E R TEMPERATURES t 0,002-IN. F I L M (3).

TEMPERATURE (OF)

TENSILE STRENGTH QF MYLAR* * T.M.

E. I. DUPONT DE NEMOCIRS AND CO.

XI-F-2.2

149

1 20

I00

80

60

40

2c

(

b I

NOTE: -

AS RECEIVED -!-

CROSSHEAD RATE: 1-IN /MIN--’IOF 0 I - IN./MIN- LO w E R T E M P E’R A’TU RE s .

TEMPERATURE (OF)

ELONGATION OF MYLAR*

* T.M E. 1: DUPONT DE NEMOURS AND C O .

XI-F-2.3

2.8

2.4

2.0

I .6

1.2

0.8

0.4

C

i!r T H E R M A L HISTORY

CRYSTALL- SPEC IF IC IN ITY, % GRAVITY

15 1.35 AS RECEIVED

I AS RECEIVED+ 480F/1 HR. SLOW COOL I I I 55

IN-

* T . M . E. I . DUPONT DE NEMO'JRS AND CO.

T E M P E R A T U R E (OF)

MODULUS OF ELASTICITY OF MYLAR*

XI-F-2.4

28

24

20

16

12

8

4

0

I I I I 1 1 I I N O T E : - T F E T E F L O N

C R Y S T A L L - S P E C I F I C T H E R M A L I N I T Y , 7, G R A V I T Y T R E A T M E N T

I I

49-50

52.5-56

M O L D E D 7 2 0 F I 3 0 M I N , Q U I C K Q U E N C H E D

I I 2.159-2.171 AS A B O V E + 5 8 5 F / 5 HR I 66.2-71 I 2 ,199-2 .226 1 AS A B O V E + 618F/ZO HR I C R O S S H E A D RATE: l - l N . / M I N - 7 0 F , 0.1 I N . / M I N -

L O W E R T E M P E R A T U R E S

0 . 0 6 2 - I N . S H E E T (3).

I 6 6 . 2 -, C R Y S T A L L I N I T Y d

5 2 . 5 % C R Y S T A L L I N I T Y

-200 - 100 0 IO0 -400 -300

TEMPERATURE (OF)

YIELD STRENGTH OF TEFLON* * T . M .

E . 1. D U P O N T D E N E M O U R S A N D CO.

XI-P-3.1

7

6

5

c

z 4 m 2 - m m w E m I - 3

L

15 % GRAPHITE FILLED

I I

TEMPERATURE ( O F )

YIELD STRENGTH OF TEFLON*

* T.M. E. I . DUPONT D E NEMOURS AND CO.

XI-F- 3.2

24

TEMPERATURE (OF)


100

* T . M . E . I . D U P O N T DE N E M O U R S A N D GO.

XI-F-3.3

120

100

80

40

2c

SHEET (3).

-400 -300 - 200 - 100

TEMPERATURE (OF)


0 100

* T.M E. I : D U P O N T DE N E M O U R S AND co.

XI-F-3.4

28

24

20

m 10 W I- m

12

c

I I I I I I I I I 1 I- NOTE: T F E T E F L O N

~

l- C R Y S T A L L - S P E C I F l C T H E R M A L I N I T Y , % G R A V I T Y T R E A T M E N T

49-50 2.148-2.152 M O L D E D 720Fl30 M IN, -I QUICK QUENCHED

82.5-56 2.159-2.171 AS ABOVE -k 585F/5 HR - - 66.2-71 2.199-2.226 AS ABOVE -I- 618F120 HR

CROSSHEAD RATE-SEE G.3.A. 0.062-IN. S H E E T (3).

100

TENSILE STRENGTH OF TEFLON* *T.M. E. I . UUPONT D E NEMOURS A N D CO.

XI-F-3.5

TEMPERATURE (OF)

TENSILE STRENGTH OF TEFLON* * T.M.

E. I. D U P Q N T DE NEMOURS AND CO.

XI-F-3.6

24

20

16

2

TEMPERATURE ( O F )

TENSILE STRENGTH OF TEFLON*

* T.M. E , I . DUPONT DE NEMOURS AND C O .

XI-F-3.7

120 -

100

ao

60

40

20

0

TENSILE STRENGTH O F TEFLON*

100

XI-F-3.8

TEMPERATURE (OF)

ELONGATION OF TEFLQN” * T . M

E. I : D U P O N T DE N E M O U R S 4 N D Co.

XI-F-3.9

c.\

i "! - 0

z I- Z W L) II: W a z l- a z 0 .-J W

-

v

2 a

50

40

30

20

10

t

TEMPERATURE ( O F )

ELONGATION OF TEFLON*

* r . M . E . I . DUPONT D E N E M O ' J R S AND CO.

XI-F-3.10

TEMPERATURE (OF)

30

1

* T . M E. 1: DUPONT DE NEMOURS AND co.

XI-F-3.11

28

24

20

16

12

8

4

0 j: XI-F-3.12

-400 -300 - 200 - 100

TEMPERATURE (OF)

COMPRESSIVE STRENGTH OF TEFLON* *T M E: I : D U P O N T DE N E M O U R S A N D co.

e

0 100

35

30

25

20

15

10

5

0 -400 -300 - 200 - 100 0 100

TEMPERATURE (OF)

COMPRESSIVE STRENGTH OF TEFLON* * T . M E. I : DUPONT DE N E M O U R S AND Co.

XI-F-3.13

40

35

30

25

20

15

10

5

0

TEMPERATURE (OF)

COMPRESSIVE STRENGTH OF TEFLON* *T .M. E. I . DUPONT DE NEMOURS AND CO.

00

XI-F- 3 . 1 4

120

100

80

60

4c

2(

I

---t---

I

00

TEMPERATURE (OF)

COMPRESSIVE STRENGTH OF TEFLON*

* T . M E . I : D U P O N T D E N E M O i J R S fND CO.

XI-F-3.15

I

m a m 0 c - m m W [r I- m

28

24

20

16

12

8

4

I I NOTE: T F E 52 4 % C R Y S T A L L I N I T Y C R O S S H E A D SPEkD--'O.O2--IN. MIN, 0.lZS-lkl. S H E E T ( 6 ) . I I

0 0.040 0.080 0.120 0.160 0.200 0


STRESS-STRAIN DIAG AM FOR TEFLON*

XI-F-3.16

0

* T . M . E. I . D U P O N T D E N E M O U R S A N D C O .

0.7

0.6

0.5

0.4

0.3

0.2

0.1

0

I I I I I I I

- I N I T Y , % G R A V I T Y T R E A T M E N T - NOTE: T F E T E F L O N - - --

C R Y S T A L L - S P E C I F I C T H E R M A L

49-50 2.148-2.152 M O L D E D 720F/30 M IN, QUICK QUENCHED

-I 52.5-56 2.159-2.171 A S ABOVE t 58SF/S HR

66.2-71 2.199-2.226 A S AEOVE + 618F/20 HR I CROSSHEAD 13’1 RATE-SEE G.3.A. 0.062-1N. S H E E T

-400 -300 - 200 .- 100

TEMPERATURE (OF)

0 100

MODULUS OF ELASTICITY OF TEFLON* * r . M

E. I : DUPONT DE NEMOURS AND co.

XI-F-3.17

1.40

1.20

1 .oo

0.80

0.60

0.40

0.20

0

FEP.

I

- NOTE: @ SAMPLES C U T 11 TO MOLD FORCES.

2 SAMPLES CUT 1 TO MOLD FORCES ' CROSSHEAD RATE- SEE G . 3 . A . 0.06s-IN. SHEET (3).

-400 -330 -200 -100

TEMPERATURE (OF)

0 100

MODULUS TICITY OF TEFLON* * T.M.

E . I . DUPONT DE NEMOIJRS A N D CO.

XI-F-3.18

2.6

2.2

.8

1.4

1 .o

0.6 -400 -300 - 200 - 100 0 100

TEMPERATURE (OF)

MODULUS OF ELASTICITY OF TEFLON*

* T . M . E . I . D U P O N T DE N E M O U R S A N D CO.

XI-F-3. 19

4 -

-

3 -

-

2 -

-

1 -

-

0 -

3

2

1

0

-400 - 300 - 208 - 100 0 100

TEMPERATURE ( O F )

-400 - 300 -200 - 100 0 100

TEMPERATURE (OF)

* IMPACT

* r . M . E. 1. DUPONT DE NEMOVRS AND CO.

XI-F-3.20

3.0

2.0

1.0

0

3.0

2.0

1.0

0

I I I I I

N O T E : T F E T E F L O N S T A N D A R D IZOD. - 0.250- IN. S H d E T (3).

I I I I I I

I

15 % G R A P H I T E F I L L E D

I 65 % B R Q N Z E F I L L E D

I I I I I \-c 25 % A S 5 E S T O S F I L L E D .A& - - 200 - IO0 0 100 -400 -300

TEMPERATURE (OF)

50-IN. S H E E T

-400 -300 - 200 - 100 0 100

TEMPERATURE (OF)

IMPACT STRENGTH * T . M

E . I : D U P Q N T D E N E M O U R S AND co.

XI-F-3.21

T m a

m 0 c J

m tn W 01 I- v)

32

28

24

20

16

1;

I

1

IOTE: - CRYSTALL- SPECIF IC THERMAL HISTORY INITY.qb GRAVITY

I

MOLDED 525F/5 M IN, QUENCHED 40 2.10

55 2.12 AS-RECEIVED +3OOF/4 HR, SLOW COOL

70 2 .14 AS-RECEIVED C395F/24 HR: SLOW COOL

CROSSHEAD RATE: 1-lN./M iN-70F. 0.1--IN./MlN-LOWER TEMPERATURES

100

TEMPERATURE (OF)

YIELD STRENGTH OF KLF* * T M

M ' I N ~ E S O T A MINING AND MFG. CO.

XI-F-4.1

- - m a

m 0 CI .v

3;

2t

2L

21

16

12

8

4

0

TEMPERATURE ( O F )

TENSILE STREN * T.M.

MINNESOTA MINING AND M F G . C O .

XI-F-4.2

160

140

120

100

80

60

NOTE:

M IN, QUENCHED

AS-RECEIVED + 300F/4 HR, S L O W COOL

CROSSHEAD RATE: 1-lN./M IN-70F. 0.1-IN./MIN-LOWER TEMPERATURES

XI-F-4.3

2

24

2(

16

12

8

4

0 0 0.040 0.080 0.120 0.160 0.200

S T R A I N ( I N C H E S P E R INCH)

STRESS-STRAIN DIAGRAM FOR KEL-F* * T.M.

MINNESOTA MINING AND MFG. CO

XI-F-4.4

1.6

1.4

1.2

c

si 1.0 a a 0 c - II) 3 -I =I 0.8

z 8

0.6

0.4

0.2

AS-RECE IVED 4- 500F/4 H R , SLOW COOL

AS-RECE IVED i- 395F1'24 HR, SLOW COOL

CROSSHEAD RATE: I - - IN. /M IN-70F. 0 .1- IN. /MIN-LOWER T E M P E R A T U R E S

0.062-IN, S H E E T (3).

-400 -300 - 200 -100 0 100

TEMPERATURE (OF)

F ELASTICITY OF KEL-F*

*T.M. M I N N E S O T A M I N I N G AND M F G , CO.

XI-F-4.5

n r u I- 4 LL 0

i m L

- \

-I

LL

W

W

a m

m a

a

m

6 w Z W

4.0

3.0

2.0

1.0

3

a M O L D E D 525F/5 M I N , QLJENCHE

I I I S T A N D A R D IZQD. 0 . 2 5 0 - I N . P L A T E (3) I

-400 -300 - 200 -100 0

TEMPERATURE ("F)

IMPACT STRENGTH OF KEL-F*

E 100

* T M M'IWNESQTA M I N I N G A N D M F G , co.

XI-F-4.6

70

60

50

40

30

20

10

0

NOTE:' CRYSTALL-- THERMAL HISTORY IN I TY , A

50 MOLDED SZSF/S M IN, OIUENZHED c t 60 AS-RECEIVED C 300F/4 HR. SLOW COOL

70 AS-RECEIVED 4- 395F/24 HR, SLOW COOL - CROSSHEAD RATE: 0.05-lN./WIIN. 0.5-IN. D I A ROD (3).

-300 - 200 - 100 0 1 -400

TEMPERATURE (OF)

00

*T.M. MINNESOTA M I N I N G AND M F G , COO

XI-F-4.7

140

120

m 2 W

80 m m Lll [r: I- m

60

40

20

I I I EPON 1001 R E S I N , 34.9-38.2% R E S I N CONTENT

TEMPERATURE (OF)

XI-G-1 1

325

300

27 5

250

225

200

175

15C

TEMPERATURE (OF)

TENSILE STRENGT

XI-G-1.2

= u) a

m 0 c v

u) rn w I- rn a

TEMPERATURE (OF)

COMPRESSIVE SP ENGTH OF EPOXY - ERGLASS LAMINATE

0

XI-G-1.3

2

I I

I . I I

FATIGUE STRENGTH OF EPOXY-FIBERGLA3 LAMINATE

J 104 105 FATIGUE LIFE (CYCLES)

1

--320°F

-423OF

/

- 1 l O o F

30000

20000-

25000

I

- ---. GLASSCLOTH t - -

-

Y I P A R A I I FI \

GLASSCLOTH/ 31.6 VQL. EPOXY ---

4.103

I I I 1 I 13.103

v)

3 P 0

3 2

3

TENSILE MOQULU QF ELASTICITY OF UNFILLED, GLASSFIBER- REINFORCED AND FILLED EPOXIES

XI-G-1.5

i4a

12a

100

80

60

40

20 - 400

I I I I NOTE: 181 GLASS CLOTH REINFORCEMENT 0 125- IN. NOMINAL PANEL TH ICKNE'SS I - (i 14)

- 300 - 200 - 100 0 100

TEMPERATURE (OF)

TENSILE STRENGTH OF PHENOLIC - FIBERGLAS L A M I N A T E

XI-G-2. I.

TEMPERATURE (OF)

XI-G-2.2

100

CTL 91 LD RESIN,

C O N T E N T C: 22.a-2aa3% R E S I N .

0

TEMPERATURE (OF)

COMPRESSIVE STRENGTH OF PHENOLIC - FIBERGLASS LAMINATE

XI-G-2.3

XI-G-2.4

140

120

9 00

80

60

40

20 - 400

N O T E : 1 8 1 C L A S S C L O T H R E I N F O R C E M E N T , - - 0 125-IN. N O M I N A L P A N E L T H I C K N E S S c i 14)

- 300 - 200 - 100 0 100

TEMPERATURE (OF)

TRENGTH OF POLYESTER - FIBERGLAS LAMINATE

XI-G-3.1

130,

110

90

TEMPERATURE (OF)

COMPRESSIVE STRENGTH OF POLYESTER - FlBERGLAS LAMINATE

XI-G-3.2

(ISd

EOL) S

S3rJIS

XI-G-3.3

e 100 r

I

NOTE: 181 GLASS CLOTH REINFORCEMENT. - 0 12%- IN. N O M I N A L P A N E L THICKNESS - t i 14)

80

60

40

20

TEMPERATURE (OF)

TENSILE STRENGTH OF HIGH

LAMINATE TEMPERATURE POLYEST

XI-G-4.1

130

110

90

70

5c

3(

1

TEMPERATURE (OF)

COMPRESSIVE STRENGTH OF HIGH

L A M ! N ATE TEMPERATURE POLYESTER - FIBERGLAS

XI-G-4.2

xw f

I 0

I

u

70

60

50 / - - v) a

m 0

--2=

In w E k m

In 40

30

20

1C 1

I I I I

I I

NOTE: V l B R l N 135 RESIN/181 GLASS CLOTH - R E I N F O R C E M E N T . 32.4-34.65 R E S I N

\ I

2 103 I 04 105 FATIGUE LIFE (CYCLES)

E ST F HDGH TEMPERATURE POLYESTE

1 2(

1 oc

m 0 G in # W IY I- #

80

60

40

20

I I N O T E : 181 G L A S S . C L O T H R E I N F O R C E M E N T ,

0 125- IN. N O M I N A L P A N E L T H I C K N E S S I l - ( i 1 4 )

- 400 - 300 - 200 - 100

TEMPERATURE (OF)

0 9 QQ

TENSILE STRENGTH OF SlLlC FIBERGLAS LAMINAPE

TEMPERATURE (OF)

TENSILE STRENGTH OF SILICONE-FIBERGLASS FILAMENT WOUND RINGS

XI-G-5.2

COMPRESSIVE STRENGTH OF SILICONE - FIBERGLASS LAMINATE

XI-G-5.3

60

40

h m n 0 m

3a t l (0 W E l- m

XH r I

ln

-c 20

1c

,--IIO°F

( I 102 103 ' 104 105 106 I 07

I I I I I I I I I I I I ' I I I I I I I

FATIGUE LIFE (CYCLES)

FATIGUE STRENGTH OF SILICONE-FIBERGLAS LAMINATE

300 x

2 6 (

24C

22c

20c

18C

-- E 16C c

v) v) w 140 Ix I- 0

120

I O 0

80

6 0

4 0

2 0

0

-I- -1 .

..

8 I I I I .

I

1 I

. . .___.

. . . _.

.

- - - .I- c /

- l l O ° F I

...... - . . . .

i i -

.

. -. . _

.....

.

. -_

. . .

. .

XI-H-1

6 9

6e

67

6E

6 :

6 l

6: - U J a

6 :

6

6J

5 '

5

5

5

5

I I I

i

1

i

I I

! ! i

I I I

! I

I I I I

1 I

. . -

. - -

. .

. ..

I . -

. _ _ .. . -

- . I _ _ _ _ +

I N D A R D D E V I A T I O N B;

!

.ED

\

\

- i

T i

. .. i I

,L.D ON 21 T E S T S A T 75 F . ? 0 0..'?2 x I O G F S I S T A N D A R D D E V I A T I O N B A S F D ON 3 TESTS A T - 1 0 8 O F 2 0 L i38 x IO6 PSI S T A N D A R D DEVIATION BASED 0t.I 6 T E S T S AT -320 'F : O C 2 7 x IO6 PSI S T A N D A R D DEVIATION BASED 0': 3 T E S T S A T - 4 2 3 " F + 0 0 2 4 x I O E ' i 3 i

- - S T A N D S L P D E V I A T I O N

XI-H- 2

6 25 x :o . ---.I .. - -. ... .

2(

15 .- v) a

IO

5

0

I I

I

I i I

- - _____ i... i ' - I 100 200 3;r 4c.; 5,.:r 0 -463 - 4 G 3 -3GO -200 -100

TEMPERA-! URE, O F '

7

61

5(

4c a t .e

3c

20

I O

0

i I

! I

i i I i

I

! i

! !

I

j _...---'~

I

..

!

I

- . 1

. . - r.-.-.. .

__. I I

I ' I

... - . -. ..

XI-H-3

. .. -..

-.

. ... .

._ __ - . - .. ...

.

. .. -

LL 3

rc) N

2 [o" 0- N

rn -

'1

-

..

1

/ _....

_.

, .

- . .- -

0

? 0

I .. !

- . .

0

c - ..

.

,. ._

.... .

I .

-. I .

.

1

.. . -

. . -.

.. ..

- .. -

..

..

-.

..

_. ... .

-.

._ . ..

0

(u

XI-H-4