Durability Methods Development. Volume 8. Test and Fractography Data

Abstract

This report contains the test results and raw fractography data for Phase II of the 'Durability Methods Development' program. The fractography data in this report can be used to quantify the initial fatigue quality or equivalent initial flaw size (EIFS) cumulative distribution for clearance-fit fastener holes. These data can be used to implement the probabilistic fracture mechanics approach, described in the Durability Design Handbook (AFFDL-TR-83-3027), for durability analysis. Over 700 specimens were fatigue tested in Phase II. Variables included in the test program were material (7475-T7351 and 2024-T851 aluminum; D6ac steel), spectrum (F-16 400 hour and F-16 500 hour; B-1 bomber); stress level, fastener diameter/fit, % bolt load transfer (0,15, 39, 40%) and specimen geometry. Most of the fatigue data was obtained for: 7475-T7351 aluminum, F-16 400 hour spectrum and countersunk fastener holes. Fractography data are presented for over 800 fatigue cracks (primary and secondary) in fastener holes. A tear-down inspection of the F-16 durability test article (wing) is documented, including fractographic results for the lower wing skins.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1982
Accession Number
ADA141451

Entities

People

  • A. Meder
  • D. E. Gordon
  • R. O. Nay
  • S. M. Speaker
  • W. T. Kaarlela

Organizations

  • General Dynamics

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Force
  • Chemistry
  • Computer Programs
  • Data Sets
  • Materials
  • Measurement
  • Mechanics
  • Photographs
  • Plastic Explosives
  • Recording Systems
  • Spars
  • Spectra
  • Standards
  • Tensile Strength
  • Test Facilities
  • Wing Boxes

Readers

  • Structural Health Monitoring of Composite Structures.