| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 864600 | Procedia Engineering | 2010 | 7 Pages |
Abstract
The paper presents an experimental work of fatigue crack growth for aerospace 2024 T351 aluminum alloy under constant amplitude loading. At 10 Hz frequency, the effect of various amplitudes loading is examined for bending V-Charpy specimen. The results of the fatigue tests conducted at R=0.1, show the effect of the amplitude of loading on the fatigue life and fatigue crack growth rate. The fractography examinations were carried out on scanning electron microscopic SEM and show the presence of fatigue striations in Paris region.
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