SYMPOSIA PAPER Published: 01 January 1971
STP26677S

Initiation and Growth of Fatigue Cracks in and Residual Strength of the F-100 Wing

Source

Full scale fatigue tests were conducted on the F-100 wing. Service connected fatigue failure data were collected and compared with test results. Test lives to initiate fatigue cracks are compared with predicted lives using Miner's rule of linear cumulative damage and by a method accounting for plasticity at the crack origin. Calculated failure stresses using the principles of fracture mechanics are compared with laboratory test failure data. Crack growth data measured during testing are compared with values predicted from the relation dl/dN versus ΔK, the range in the stress intensity factor. Modifications to the wing structure are described, and the resulting fatigue life improvement is presented.

Author Information

Graziano, WD
North American Rockwell/LAD, Los Angeles International Airport, Los Angeles, Calif.
Fitch, GE
North American Rockwell/LAD, Los Angeles International Airport, Los Angeles, Calif.
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Details
Developed by Committee: E08
Pages: 144–163
DOI: 10.1520/STP26677S
ISBN-EB: 978-0-8031-4595-5
ISBN-13: 978-0-8031-0031-2