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This paper presents a method for predicting the fatigue life of a full-scale structure for any combination of loading provided that a single datum point representing the life of the structure for 104 or fewer cycles is known. The only additional information required is stress-strain and S–N data for smcoth axially loaded coupons. An illustrative example of the use of this method is the prediction of lives for tail structures yet to be tested at the Navy Aeronautical Structures Laboratory, Philadelphia, Pa.
Smith, Clarence R.
Fatigue Laboratory, San Diego, Calif