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Fatigue Crack Propagation in Clad RR58 Sheet to DTD 5070A: Analysis and Correlation of Test Results

Published online by Cambridge University Press:  04 July 2016

D. P. Rooke ,
N. J. F. Gunn ,
J. T. Ballett  and
F. J. Bradshaw
D. P. Rooke
Affiliation:
RAE, Farnborough
N. J. F. Gunn
Affiliation:
RAE, Farnborough
J. T. Ballett
Affiliation:
RAE, Farnborough
F. J. Bradshaw
Affiliation:
RAE, Farnborough
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Extract

In recent years there has been an increasing need for data on the rates of fatigue crack propagation in alloys of interest to the aircraft industry. In general alloys in which cracks grow slowly, under given stress conditions, have an obvious advantage over those in which cracks grow faster; there is more time to detect a crack before failure. It is possible that, in the future, quantitative crack propagation data may be used to give better estimates of the safe life of a structure. There is, however, a need to rationalise the presentation of such data and to study the effect of such parameters as specimen geometry and stress level. Some experiments to investigate the effect of varying some of these parameters in one clad aluminium alloy, DTD 5070A are described. It is a summary of work contained in two RAE Technical Reports.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 73 , Issue 700 , April 1969 , pp. 335 - 339
Copyright
Copyright © Royal Aeronautical Society 1969 

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References

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