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A Note on the Effect of Proof Stress on the Notched Fatigue Strength of the Aluminium Alloy HE 15

Published online by Cambridge University Press:  04 July 2016

P. G. Forrest
P. G. Forrest*
Affiliation:
National Physical Laboratory, Teddington, Middlesex
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Summary

The notched fatigue strength of the aluminium alloy HE 15, under stress conditions similar to those occurring in aircraft structures, is greater when the material is naturally aged than when it is fully heat-treated. This is attributed to the lower proof stress of the naturally aged material, which enables the high stresses in regions of stress concentration to relax more readily. However, no further improvement was obtained by re-solution-treating the alloy to reduce the proof stress further.

Information

Type
Technical Notes
Information
The Aeronautical Journal , Volume 67 , Issue 633 , September 1963 , pp. 596 - 598
Copyright
Copyright © Royal Aeronautical Society 1963

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References

1.Heywood, R. B.Designing Against Fatigue. Chapman & Hall, London, 1962.Google Scholar
2.Gunn, K.Aeronautical Quarterly, Vol. 6, p. 277, 1955.Google Scholar
3. Royal Aeronautical Society Data Sheets on Fatigue.Google Scholar
4.Fisher, W. A. P. RAE Report No. Structures 205, 1956.Google Scholar