Results are presented concerning crack location, cycles to crack initiation, crack propagation, and residual static strength of 18 outer panels of T-29A aircraft; constant amplitude tests were performed by using resonant frequency method at 3 different alternating load levels superimposed on 1 g or level flight mean load.
Fatigue investigation of full-scale wing panels of 7075 aluminum alloy
NASA -- Tech Note
1961
31 pages
Article (Journal)
English
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