Print Email Facebook Twitter Engineering property comparisons for 2324-T39 and 2024-T351 aluminium alloy plate Title Engineering property comparisons for 2324-T39 and 2024-T351 aluminium alloy plate Author Schra, L. 't Hart, W.G.J. Institution National Aerospace Laboratory NLR Date 1984-03-19 Abstract Engineering property comparisons have been made for plate material of the newly developed aluminium alloy 2324-T39 and the widely used alloy 2024-T351. The properties considered were: tensile strength, fracture toughness, notched fatigue strength, and the resistance to fatigue crack propagation under both constant amplitude and flight simulation loading. Significantly higher strength and fracture toughness properties were found for 2324-T39, but the notched fatigue strengths of both alloys were comparable. With respect to fatigue crack propagation resistance, 2324-T39 was slightly better than 2024-T351 under constant amplitude loading, but less resistant under flight simulation loading. The latter result indicates that replacement of 2024-T351 by 2324-T39 in fatigue critical areas is a questionable proposition. Subject mechanical propertiesaluminium alloysnotch testsfracture resistanceheat treatmentairframe materialsflight simulationtensile testsstress intensityfactorshigh strength materialsfatigue testsfracture toughnessthresholds To reference this document use: http://resolver.tudelft.nl/uuid:c25b1786-b8dd-4def-ac7d-34d415e2adf7 Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR 84021 U Part of collection Aerospace Engineering Reports Document type report Rights (c) 1984 National Aerospace Laboratory NLR Files PDF NLR_TR_84021_U.pdf 22.57 MB Close viewer /islandora/object/uuid:c25b1786-b8dd-4def-ac7d-34d415e2adf7/datastream/OBJ/view