, Volume 40, Issue 5, pp 16–18 | Cite as

Elevated-Temperature Al Alloys for Aircraft Structure

  • Richard A. Rainen
  • John C. Ekvall
Material Design


Elevated-temperature powder metallurgy (P/M) aluminum alloys are being developed to replace titanium aircraft structure materials for operation in the 300–600°F temperature range. Typical mechanical properties ofP/M Al−Fe−Ce and Al−Fe−V−Si alloys are superior to those of conventional materials, and cost savings of fifty to seventy percent have been projected for these alloys which can be fabricated and processed using methods similar to those used in the production of conventional aluminum.


Aluminum Alloy Fracture Toughness Thermal Exposure Stress Corrosion Test Conventional Aluminum Alloy 


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  1. 1.
    R.E. Sanders and G.J. Hildeman, “Elevated Temperature Aluminum Alloy Development,” AFWAL-TR-81-4076, September 1981.Google Scholar
  2. 2.
    S.L. Langenbeck and R.A. Rainen, et al., “Elevated Temperature Aluminum Alloy Development,” AFWAL-R-86-4027, May 1986.Google Scholar
  3. 3.
    “Elevated Temperature Powdered Aluminum Airframe Structure,” AFWAL Contract F33615-82-C-3200, July 1983–February 1990.Google Scholar
  4. 4.
    “Elevated Temperature Aluminum Program (ETAP),” AFWAL Contract F33615-87-C-3206, September 1987–December 1991.Google Scholar
  5. 5.
    “Standard Recommended Practice for Alternate Immersion Stress Corrosion Testing in 3.5 Percent Chloride Solution,” ASTM G44-75, Annual Book of ASTM Standards (1987).Google Scholar

Copyright information

© TMS 1988

Authors and Affiliations

  • Richard A. Rainen
  • John C. Ekvall

There are no affiliations available

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