It is shown that, even with most careful attention to detailed design of aluminum alloy components, it is not possible to attain minimum acceptable fatigue strength for typical structures, i.e. 2×106 cycles of lg plus or minus 7 1/2% ultimate strength of structure, based on present British Civil Airworthiness Requirements (Reserve Factor 1.0); fatigue test results.
Fatigue life of wing components for civil aircraft
Roy Aeronautical Soc -- J
Royal Aeronautical Society -- Journal ; 56 , n 503
1952
7 pages
Aufsatz (Zeitschrift)
Englisch
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