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A crack-closure model for predicting fatigue-crack growth under aircraft spectrum loadingThe development and application of an analytical model of cycle crack growth is presented that includes the effects of crack closure. The model was used to correlate crack growth rates under constant amplitude loading and to predict crack growth under aircraft spectrum loading on 2219-T851 aluminum alloy sheet material. The predicted crack growth lives agreed well with experimental data. The ratio of predicted to experimental lives ranged from 0.66 to 1.48. These predictions were made using data from an ASTM E24.06.01 Round Robin.
Document ID
19810009887
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Newman, J. C., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Structural Mechanics
Report/Patent Number
NASA-TM-81941
Accession Number
81N18412
Funding Number(s)
PROJECT: RTOP 505-33-23-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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