NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Mode II fatigue crack propagation.Fatigue crack propagation rates were obtained for 2024-T3 bare aluminum plates subjected to in-plane, mode I, extensional loads and transverse, mode II, bending loads. These results were compared to the results of Iida and Kobayashi for in-plane mode I-mode II extensional loads. The engineering significance of mode I-mode II fatigue crack growth is considered in view of the present results. A fatigue crack growth equation for handling mode I-mode II fatigue crack growth rates from existing mode I data is also discussed.
Document ID
19720032127
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Roberts, R.
(Lehigh University Bethlehem, Pa., United States)
Kibler, J. J.
(GE Solid Mechanics Laboratory Schenectady, N.Y., United States)
Date Acquired
August 6, 2013
Publication Date
December 1, 1971
Subject Category
Structural Mechanics
Report/Patent Number
ASME PAPER 71-MET-J
Accession Number
72A15793
Funding Number(s)
CONTRACT_GRANT: NGR-39-007-011
CONTRACT_GRANT: NSF GK-2992
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available