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02022nam a2200409Ia 4500 |
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4c6c6e52-b7cd-4852-970d-03e2be964dd7 |
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20230825000000.0 |
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920106s1990 vaua bb f000 0 eng d |
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|a (NjP)4588924-princetondb
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|a ocm25053223
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|z (NjP)Voyager4588924
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|a OKX
|c OKX
|d OCL
|d GPO
|d MvI
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049 |
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|a DOCS
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074 |
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|a 0830-D (MF)
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|a 0830-D (online)
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086 |
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|a NAS 1.15:102590
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1 |
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|a Dawicke, D. S
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1 |
0 |
|a Through-the-thickness fatigue crack closure behavior in an aluminum alloy
|h [microform] /
|c D.S. Dawicke, J.C. Newman, Jr., and A.F. Grandt, Jr
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260 |
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|a Hampton, Va. :
|b National Aeronautics and Space Administration, Langley Research Center ;
|a [Springfield, Va. :
|b For sale by the National Technical Information Service,
|c 1990]
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|a 6 p. :
|b ill
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440 |
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0 |
|a NASA technical memorandum ;
|v 102590
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500 |
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|a Cover title
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500 |
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|a "January 1990."
|
504 |
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|a Includes bibliographical references (p. 5)
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530 |
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|a Also available via Internet from the NASA Technical Report Server web site. Address as of 8/18/05: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19900011111%5F1990011111.pdf ; current access is available via PURL
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533 |
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|a Microfiche
|b [Washington, D.C. :
|c National Aeronautics and Space Administration,
|d 1990].
|e 1 microfiche : negative.
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650 |
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0 |
|a Aluminum alloys
|x Fatigue
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650 |
|
7 |
|a Aluminum alloys
|2 nasat
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650 |
|
7 |
|a Crack closure
|2 nasat
|
650 |
|
7 |
|a Crack propagation
|2 nasat
|
650 |
|
7 |
|a Fatigue (Materials)
|2 nasat
|
650 |
|
7 |
|a Stress intensity factors
|2 nasat
|
650 |
|
7 |
|a Thickness
|2 nasat
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700 |
1 |
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|a Grandt, A. F
|q (Alten F.),
|d 1945-
|
700 |
1 |
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|a Newman, J. C
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710 |
2 |
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|a Langley Research Center
|
999 |
1 |
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|i 4c6c6e52-b7cd-4852-970d-03e2be964dd7
|l 9945889243506421
|s US-NJP
|m through_the_thickness_fatigue_crack_closure_behavior_in_an_aluminum_almicro1990_______natioa________________________________________dawicke__d__s______________________nas_1_15_102590p
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