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Correlation of Fatigue Data for Aluminum Aircraft Wing and Tail Structures
NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO)
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S-N curves are derived for aluminum wing and tail structures by fitting various regression models to 246 full-scale constant-amplitude fatigue test results from twelve types of aircraft structures. The derived curves were tested by comparing the predicted lives with actual test results of various aircraft structures fatigue tested to variable-amplitude loads spectra. More reliable predictions resulted from these derived S-N curves than from existing S-N curves.
APPROVED FOR PUBLIC RELEASE