Combined effect of matrix cracking and stress-free edge on delamination
By: S.A. Salpekar and T.K. O'Brien.
Contributors: O'Brien, T. Kevin.; Langley Research Center.; United States. Army Aviation Systems Command.
Series: NASA technical memorandum -- 102591.; AVSCOM technical memorandum -- 90-B-002.
Publisher: National Aeronautics and Space Administration, Langley Research Center; US Army Aviation Systems Command
Published: 1990
Place of publication: Hampton, Va; [ St. Louis, MO]
Language: eng
Format: Microform
Number of pages: 64
Subjects: Composite materials -- Delamination.; Crack initiation.; Delaminating.; Edge loading.; Finite element method.; Laminates.; Strain energy release rate.
Notes: Cover title.

Shipping list no.: 90-0860-M.

"March 1990."

Includes bibliographical references (p. 30-32).

Also available via Internet from the NASA Technical Report Server web site. Address as of 3/1/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19900011810%5F1990011810.pdf; current access available via PURL.

Microfiche. [Washington, D.C.? : National Aeronautics and Space Administration, 1990]. 1 microfiche : negative ; 11 x 15 cm.