Accession Number:

ADA053743

Title:

Corrosion Fatigue of High Strength Aircraft Structural Materials - Crystallographic Dependence of Fracture Path in A1-Zn-Mg (7075) Alloys.

Descriptive Note:

Final technical rept. 1 Jul 72-30 Sep 74,

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE DIV OF SPONSORED RESEARCH

Personal Author(s):

Report Date:

1977-12-01

Pagination or Media Count:

18.0

Abstract:

Low cycle corrosion fatigue tests were conducted in a variety of environments to quantitatively demonstrate the environmental effects on high strength aluminum 7075-T6 alloys. Environments used included argon, dry air, distilled water, and 3.5 sodium CHLORIDE SOLUTION. Crack growth rates were found to vary by almost two orders of magnitude, from .0001 to .000001 inches per cycle, with argon and dry air the lowest and sodium chloride solution the highest. Scanning electron micrographs clearly showed the transition from ductile to brittle failure going from inert to aggressive environments. Author

Subject Categories:

  • Properties of Metals and Alloys
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE