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CHEMICAL COMPOSITION LIMITS (WT. \%)
Si . . . . . . . . . . . 0.40 Zn . . . . . . . . . . . 5.1-6.1
Fe . . . . . . . . . . . 0.50 Ti . . . . . . . . . . . . 0.20
Cu . . . . . . . . . . . 1.2-2.0 Others, each . . . . 0.5
Mn . . . . . . . . . . . 0.30 Others, total . . . . 0.15
Mg . . . . . . . . . . . 2.1-2.9 Balance, Aluminum
Cr . . . . . . . . . . . 0.18-0.28


¯èªÅ¾T7075¼ö³B²z¤Îª«²z©Ê¯à
Introduced by Alcoa in 1943, alloy 7075 has been the standard workhorse 7XXX series alloy within the aerospace industry ever since.
It was the first successful Al-Zn-Mg-Cu high strength alloy using the beneficial effects of the alloying addition of chromium to develop
good stress-corrosion cracking resistance in sheet products. Although other 7XXX alloys have since been developed with improved
specificproperties, alloy 7075 remains the baseline with a good balance of properties required for aerospace applications.
Alloy 7075 is available in bare ~and alclad sheet ~and plate product forms in the annealed state as well as several tempers
of the T6, T73 ~and T76 types.

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