Pages that link to "Item:Q671733"
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The following pages link to Approximate methods for analyzing the growth of large cracks in fatigue damaged aircraft sheet material and lap joints (Q671733):
Displaying 3 items.
- Determination of the fatigue crack-growth rate from the fractographic analysis of a specimen representing the aircraft wing skin (Q1016313) (← links)
- Residual strength of aircraft panels with multiple site damage (Q1315902) (← links)
- The elastic-plastic finite element alternating method (EPFEAM) and the prediction of fracture under WFD conditions in aircraft structures. III: Computational predictions of the NIST multiple site damage experimental results (Q1365780) (← links)