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Evaluation of Aeroplane Metals

Published online by Cambridge University Press:  28 July 2016

J. A. Van Den Broek
J. A. Van Den Broek*
Affiliation:
University of Michigan, Ann Arbor, Michigan
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Extract

The material herein presented was gathered as part of a research project for the Bureau of Aeronautics (Structures Branch) of the U.S. Navy on “Evaluation of High Strength Aluminium Alloys.” The Bureau has released this material for independent publication.

In this paper the physical constants determined are limited to elastic limit, yield stress, ultimate stress, modulus of elasticity, weight and ductility. The materials tested are primarily the new aluminium alloys 75 ST, R 301 T, and R 303 T.

To offer an immediate basis of comparison for aluminium alloys, the aluminium alloy at present in common use, namely 24 ST, was also tested. To extend the scope of the project still further, a few tests on magnesium alloy and stainless steel were included.

Type
Research Article
Information
The Aeronautical Journal , Volume 50 , Issue 431 , November 1946 , pp. 811 - 828
Copyright
Copyright © Royal Aeronautical Society 1946

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References

1 “Effects of Gold-Working on Elastic Properties of Steel,” by J. A. Van den Broek, Carnegie Scholarship Memoirs, Vol. IX., 1918; also Engineering, July 16, 1918, and Zeitschrift fur Metalkunde Band XII. Heft 8.

2 “Rational Column Analysis,” by J. A. Van den Broek, The Engineering Journal, December 1941; closing discussion June 1942.

3 See “Strength of Magnesium Alloy Columns,” by F. A. Rappleyea, Journal of Aeronautical Sciences, July 1945.

4 “Theory of Limit Design,” by J. A. Van den Broek, Trans. Am. Soc. Engrs., 1940.

* The latest experimental magnesium alloy, ZK 60, developed by the Dow Chemical Co., has a yield stress of 40,000 lb. p.s.i. and appears to be as ductile as 24 ST aluminium alloy.