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 .
,
**
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.
**
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.
**
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 )
ELONGATION OF 304 STAINLESS STEEL
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
ELONGATION OF 304 STAINLESS STEEL
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
STRAIN (INCHES PER INCH)
STRESS-STRAIN DIAGRAM FOR 304 STAINLESS STEEL
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
MODULUS OF ELASTICITY OF 304 STAINLESS STEEL
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
IMPACT STRENGTH OF 304 STAINLESS STEEL
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)
ELONGATION OF 310 STAINLESS STEEL
**
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
STRESS-STRAIN DIAGRAM FOR 310 STAINLESS STEEL
**
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 )
STRENGTH OF 321 STAINLESS STEEL
** ' . !
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)
ELONGATION OF 321 STAINLESS STEEL
-400 -300 -200 -100 0 100
TEMPERATURE (OF)
REDUCTION OF AREA OF 321 STAINLESS STEEL
**
XI-B-5.2
280
240
200
160
120
ao
40
0 0
P 0.120 0.240 0.360 0.480
STRAIN (INCHES PER INCH)
0.600
STRESS-STRAIN DlA FOR 321 STAINLESS
**
XI-B-5.3
35
30
-400 -300 - 200 - 100 0 100 25
TEMPERATURE (OF)
MODULUS OF ELASTICITY OF 321 STAINLESS STEEL
100
80
60
40
20 - 400 - 300 - 200 -100 0 100
TEMPERATURE (OF)
IMPACT STRENGTH OF 321 STAINLESS STEEL
**
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)
STRENGTH OF 347 STAINLESS STEEL
**
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)
ELONGATION OF 347 STAINLESS STEEL
**
-400 - 300 - 200 -100 0 100
TEMPERATURE (OF)
REDUCTION OF AREA OF 347 STAINLESS STEEL
XI-B-6.2
m m W U I- m
STRAIN (INCHES PER INCH)
STRESS-STRAIN DIAGRAM FOR 347 STAINLESS STEEL
**
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
IMPACT STRENGTH OF 347 STAINLESS STEEL
**
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
**
STRAIN (INCHES PER INCH)
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
T E M P E R A T U R E ( O F )
ELONGATION OF INVAW
90
7.0
50
30
T E M P E R A T U R E ( O F )
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
STRAIN (INCHES PER INCH)
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)
YIELD STRENGTH OF TEFLON*
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)
YIELD STRENGTH OF TEFLON*
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
STRAIN (INCHES PER INCH)
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