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Overload and underload effects on the fatigue crack growth behavior of the 2024-t3 aluminum alloy
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Dawicke, David S. |
| Copyright Year | 1997 |
| Description | Fatigue crack growth tests were conducted on 0.09 inch thick, 3.0 inch wide middle-crack tension specimens cut from sheets of 2024-T3 aluminum alloy. The tests were conducted using a load sequence that consisted of a single block of 2,500 cycles of constant amplitude loading followed by an overload/underload combination. The largest fatigue crack growth life occurred for the tests with the overload stress equal to 2 times the constant amplitude stress and the underload stress equal to the constant amplitude minimum stress. For the tests with compressive underloads, the fatigue crack growth life decreased with increasing compressive underload stress. |
| File Size | 264738 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19970015461 |
| Archival Resource Key | ark:/13960/t3tt9jp67 |
| Language | English |
| Publisher Date | 1997-03-01 |
| Access Restriction | Open |
| Subject Keyword | Metallic Materials Cutting Cycles Cracks Compressibility Fatigue Materials Compression Loads Aluminum Alloys Crack Propagation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
