Results are presented concerning crack location, cycles to crack initiation, crack propagation, and residual static strength of 18 outer panels of T-29A aircraft; constant amplitude tests were performed by using resonant frequency method at 3 different alternating load levels superimposed on 1 g or level flight mean load.


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    Title :

    Fatigue investigation of full-scale wing panels of 7075 aluminum alloy


    Additional title:

    NASA -- Tech Note


    Contributors:
    Castle, C.B. (author) / Ward, J.F. (author)


    Publication date :

    1961


    Size :

    31 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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