STP486: Initiation and Growth of Fatigue Cracks in and Residual Strength of the F-100 Wing

    Graziano, WD
    Supervisor, Structures, and member of technical staff, North American Rockwell/LAD, Los Angeles International Airport, Los Angeles, Calif.

    Fitch, GE
    Supervisor, Structures, and member of technical staff, North American Rockwell/LAD, Los Angeles International Airport, Los Angeles, Calif.

    Pages: 20    Published: Jan 1971


    Abstract

    Full scale fatigue tests were conducted on the F-100 wing. Service connected fatigue failure data were collected and compared with test results. Test lives to initiate fatigue cracks are compared with predicted lives using Miner's rule of linear cumulative damage and by a method accounting for plasticity at the crack origin. Calculated failure stresses using the principles of fracture mechanics are compared with laboratory test failure data. Crack growth data measured during testing are compared with values predicted from the relation dl/dN versus ΔK, the range in the stress intensity factor. Modifications to the wing structure are described, and the resulting fatigue life improvement is presented.

    Keywords:

    military aircraft, airframes, wings, failure, fatigue (materials), cracking (fracturing), crack propagation, cyclic loads, fracture strength, residual strength, aluminum, fatigue tests


    Paper ID: STP26677S

    Committee/Subcommittee: E08.06

    DOI: 10.1520/STP26677S


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