Fatigue Tests on Notched Specimens of 2024-T351 Aluminum Alloy under a Low Altitude Aircraft Load Spectrum.
Abstract
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1968
- Accession Number
- AD0676590
Entities
People
- J. A. Dunsby