Results are presented of a fatigue investigation conducted using 18 outer wing panels of T-29A airplanes. Constant-amplitude tests were performed using the resonant-frequency method at three different alternating load levels superposed on a 1 g, or level-flight mean load. Information is presented concerning crack location, cycles to crack initiation, crack propagation, and residual static strength.


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    Title :

    Fatigue Investigation of Full-Scale Wing Panels of 7075 Aluminum Alloy


    Contributors:

    Publication date :

    1961-04-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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