Scatter of Fatigue Crack Rates in 7XXX Aluminum Alloys.

Abstract

Thirty three crack growth curves were analysed in order to estimate the logarithmic variance of fatigue crack growth rate for several 7XXX Aluminum Alloys in various conditions. The estimated Standard Deviation common to all of these is: s = 0.1241 with 18 degrees of freedom. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1980
Accession Number
ADA086543

Entities

People

  • D. G. Ford

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Alloys
  • Aluminum
  • Aluminum Alloys
  • Australia
  • Classification
  • Crack Propagation
  • Cracks
  • Department Of Defense
  • Engineering
  • Equations
  • Experimental Design
  • Heat Treatment
  • Standards
  • Two Dimensional

Readers

  • Regression Analysis.
  • Structural Health Monitoring of Composite Structures.