Results are presented of a fatigue investigation conducted using 18 outer wing panels of T-29A airplanes. Constant-amplitude tests were performed using the resonant-frequency method at three different alternating load levels superposed on a 1 g, or level-flight mean load. Information is presented concerning crack location, cycles to crack initiation, crack propagation, and residual static strength.
Fatigue Investigation of Full-Scale Wing Panels of 7075 Aluminum Alloy
1961-04-01
Miscellaneous
No indication
English
Fatigue investigation of full-scale wing panels of 7075 aluminum alloy
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