Experiments are described in which notched specimens of 2024-T351 aluminum alloy were subjected to a fatigue load distribution typical of that encountered by an aircraft operating continuously at low altitude. While the experiments lack statistical validity, they serve to demonstrate the effects of design stress level on life and suggest that the lives of general-purpose aircraft currently used in these roles may be as low as 2000 to 3000 hours. (Author)
Fatigue Tests on Notched Speciments of 2024-T351 Aluminum Alloy under a Low Altitude Aircraft Load Spectrum
1968
26 pages
Report
No indication
English
Engineering Index Backfile | 1968
|Notch Size Effects in 2024-T351 Aluminum Alloy Under Fatigue Spectrum Loading
British Library Online Contents | 1998
|Notch Size Effects in 2024-T351 Aluminum Alloy Under Fatigue Spectrum Loading
Online Contents | 1998
|