The Residual Static Strength of Fatigue Cracked Lug Specimens of Four Aluminum-Copper Alloys.
ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)
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Residual static strength data from cracked fatigue specimens has been obtained for four aluminum-copper alloys DTD5014 RR58, 2L65, 2024-T81, and HID54 Al 6 Cu. It is concluded that all the materials are crack sensitive and an order of merit of the relative crack sensitivities of the materials is established. The reduction in residual static strength during fatigue life is estimated and is shown to depend on the level of alternating stress at low alternating stress cracking appears very early in the life with a consequent early fail in strength. Modified author abstract
- Metallurgy and Metallography