7050 Aluminum Alloy
7050 is a high strength heat treatable alloy with high strength and resistance to spalling corrosion and stress corrosion fracture. It is commonly used in aircraft structural parts for thick plate extrusions, free forging and die forging parts.
The main alloying element of 7050 series aluminum alloy is zinc, adding magnesium to the alloy containing 3%-75% zinc can form MgZn2 with significant strengthening effect, which makes the heat treatment effect of this alloy far better than that of aluminum-zinc binary alloy. By increasing the zinc and magnesium content of the alloy, the tensile hardness will be further increased, and the resistance to stress corrosion and spalling corrosion will rise. Very high strength properties can be achieved by heat treatment. The materials in this series are usually alloyed with small amounts of copper and chromium. The 7050-7451 aluminum alloy is the best in this series, and is regarded as the best of aluminum alloys, with high strength, far better than soft steel. This alloy has good mechanical properties and anodic reaction. Mainly used in aerospace, mold processing, machinery and equipment. It is especially used in aircraft manufacturing structures and other high stress structures that require high strength and corrosion resistance.
Mechanical properties edit
State Tensile Strength Yield Strength Elongation Hardness(a) Shear Strength Fatigue Strength(b)
MPa ksi MPa ksi Sample thickness
1.6mm(1/16in) HB MPa ksi MPa ksi
T73510 496 72- 434 63 -12 135 - - 71 10.4
t7451 524 76 -469 68 1-1 135 303- 44 71 10.4
t7651 552 80 -490 71 11- 135 324 47- 71 10.4
Note: (a) Load 500kg 10mm diameter ball; (b) R.R. Moore type test, 5*108 cycles of full reverse stress.
Density: 2.83g/cm3 (0.102lb/in3) at 20℃ (68℉).
Annealing temperature 415℃（775℉）
Solid solution temperature 475℃（890℉）
Aging temperature 120-175°C (250-350°F)
Chemical composition editor
Aluminum (Al) Balance
Magnesium (Mg) 1.9～2.6
Titanium (Ti) ≤ 0.06
Copper (Cu) 2.0～2.6
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