The Fatigue Behavior of Materials for the Supersonic Transport

Abstract

Tests were conducted on sheet specimens of two materials, Ti-8A1-1Mo-1V and AM350 CRT to determine the fatigue lives, rates of fatigue-crack propagation, and residual static strengths at three temperatures, 550 deg F, -110 deg F, and room temperature. The effects of prior exposure to 550 deg F for up to 10,000 hours on the same properties were also studied. Neither material was significantly degraded by the elevated temperature soak. The fatigue characteristics were found to be comparable to those of contemporary aluminum alloys.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1965
Accession Number
ADA397607

Entities

People

  • C. W. Marschall
  • F. C. Holden
  • M. S. Healy
  • W. S. Hyler

Organizations

  • Battelle Memorial Institute

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Aluminum
  • Aluminum Alloys
  • Amplitude
  • Cracks
  • Cyclic Rate
  • Fatigue Cracking
  • Materials
  • Mechanical Properties
  • Mechanical Working
  • Orientation (Direction)
  • Stainless Steel
  • Tensile Strength
  • Test And Evaluation
  • Titanium
  • Titanium Alloys
  • Yield Strength

Fields of Study

  • Materials science

Readers

  • Materials Science (Mechanical Engineering).
  • Mathematics or Statistics
  • Mechanical Engineering/Mechanics of Materials.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow