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Engineering Property Comparisons for 2324-T39 and 2024-T351 Aluminum Alloy Plate.


N8626429

Publication Date 1984
Personal Author Schra, L.; Thart, W. G. J.
Page Count 64
Abstract Engineering properties of the plate material of aluminum alloy 2324-T39 and alloy 2024-T351 were compared. Tensile strength, fracture toughness, notched fatigue strength, and the resistance to fatigue crack propagation under constant amplitude and flight simulation loading were considered. Significantly higher strength and fracture toughness properties are found for 2324-T39, but the notched fatigue strengths of both alloys are comparable. Fatigue crack propagation resistance of 2324-T39 is slightly better than 2024-T351 under constant amplitude loading, but less resistant under flight simulation loading. The latter result indicates that replacement of 2024-T351 by 2324-T39 in fatigue critical areas is questionable.
Keywords
  • Airframe materials
  • Aluminum alloys
  • Fatigue tests
  • Flight simulation
  • Fracture strength
  • Crack propagation
  • Heat treatment
  • Notch tests
  • Stress intensity factors
  • Tensile tests
  • Foreign technology
Source Agency
  • NASA Foreign Exchange Program
NTIS Subject Category
  • 71N - Nonferrous Metals & Alloys
Corporate Authors National Aerospace Lab., Amsterdam (Netherlands).; National Aeronautics and Space Administration, Washington, DC.
Document Type Technical Report
NTIS Issue Number 198621
Contract Number
  • NIVR-1906
Engineering Property Comparisons for 2324-T39 and 2024-T351 Aluminum Alloy Plate.
Engineering Property Comparisons for 2324-T39 and 2024-T351 Aluminum Alloy Plate.
N8626429

  • Airframe materials
  • Aluminum alloys
  • Fatigue tests
  • Flight simulation
  • Fracture strength
  • Crack propagation
  • Heat treatment
  • Notch tests
  • Stress intensity factors
  • Tensile tests
  • Foreign technology
  • NASA Foreign Exchange Program
  • 71N - Nonferrous Metals & Alloys
  • NIVR-1906
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