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.


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    Title :

    Fatigue life of wing components for civil aircraft


    Additional title:

    Roy Aeronautical Soc -- J


    Contributors:

    Published in:

    Publication date :

    1952


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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