It is suggested that distribution of reversals to failure obtained from fatigue tests on specimens typical of aircraft wing booms can be represented by log-normal curve; method, based on acceptance of certain fatigue failure rate for wing structures, is given for calculating number of reversals to failure on which "safe" life of wing may be based.
Method for determining "safe" life of aircraft wing from fatigue test results
Roy Aeronautical Soc -- J
Royal Aeronautical Society -- Journal ; 58 , n 521
1954
6 pages
Article (Journal)
English
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