Abstract: An alloy product having improved combinations of strength, density, toughness and corrosion resistance, said alloy product consisting essentially of about 7.6 to 8.4% zinc, about 1.8 to 2.2% magnesium, about 2 to 2.6% copper and at least one element selected from zirconium, vanadium and hafnium present in a total amount not exceeding about 0.5%, preferably about 0.05 to 0.25% zirconium, the balance aluminum and incidential elements and impurities. The alloy product, suitable for aerospace applications, exhibits high yield strength, at least about 10% greater yield strength than its 7X50-T6 counterpart, with good toughness and corrosion resistance properties typically comparable to or better than those of its 7X50-T76 counterpart. Upper wing members made from this alloy typically have a yield strength over 84 ksi, good fracture toughness and an EXCO exfoliation resistance level of "EC" or better, typically "EB".

Abstract: This invention relates to a metal alloy, comprised of two elements, a solute and a solvent, the solute having a maximum equilibrium solid solubility (at one atmosphere pressure) of less than 1 wt. -% in the solvent, the solvent and the solute dissolved therein forming a matrix phase, the matrix phase having a subgrain structure defined by subgrain boundaries and particles at intersections of the boundaries, the subgrains having an average size of less than 5 microns in diameter, and, within the subgrains a dispersion of particles which are finer than the particles at the subgrain boundaries, both types of particles being harder than the matrix phase.