FRACTURE TOUGHNESS AND TEAR TESTS

Abstract

Fracture and fatigue crack propagation testing of five sheet alloys being considered for commercial supersonic transport applications has been carried out. The five alloys tested were titanium 8Al-1Mo-1V (duplex annealed), stainless steel AM350 (SCT 850), nickel alloy Inconel 718 (CRA), titanium 6Al-4V (millannealed), and stainless steel PH 14-8Mo (SRH 1050). Both 8 x 24-in. and 24 x 72-in. centrally fatigued cracked panels were used in these evaluations. Crack propagation data were gathered at room temperature during the fatigue cracking of panels. Fracture tests were made over the temperature range of -110 to 650 F for both the longitudinal and transverse grain directions and for material thicknesses up to 0.200 in. for the titanium alloys and 0.125 in. for the other alloys. The variables of crack length, stress rate, and heat variation were also examined.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1964
Accession Number
AD0452827

Entities

Organizations

  • Boeing

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Cameras
  • Chemistry
  • Crystal Structure
  • Materials
  • Materials Laboratories
  • Measurement
  • Mechanical Properties
  • Mechanical Working
  • Mechanics
  • Modulus Of Elasticity
  • Photographs
  • Tensile Strength
  • Test And Evaluation
  • Test Equipment
  • Yield Strength

Fields of Study

  • Materials science

Readers

  • Materials Science (Mechanical Engineering).
  • Metallurgy

Technology Areas

  • Hypersonics