This reference compares five common wrought aluminum alloys: 1050, 2024, 5052, 6063, and 7075. The tables list magnesium, silicon, manganese, copper, chromium, zinc, and iron content; melting range, density, thermal expansion, thermal conductivity, specific heat, and electrical resistivity; and elongation, hardness, Poisson’s ratio, shear strength, elastic modulus, tensile strength, and yield strength. Notes explain the roles, heat-treatability, corrosion resistance, ductility, and aerospace relevance of the 1000, 2000, 5000, 6000, and 7000 series. The article preserves the source’s reported process conditions, units, material grades, and technical relationships for practical reference.
Aluminum alloys are widely used in space mechanisms because of their low density and high specific strength. Their disadvantages include low stiffness and hardness, a high coefficient of thermal expansion, and susceptibility to adhesive wear and scuffing, so surface treatment is required to improve tribological performance. When an aluminum-alloy self-mated pair slides in contact under vacuum, it exhibits a high and variable coefficient of friction (μ > 0.5). The tables below list the composition and physical and mechanical properties of common aluminum alloys. These alloys contain varying amounts of strengthening elements such as Mg, Cu, Si, and Zn.
| Aluminum Alloy | 1050 | 2024 | 5052 | 6063 | 7075 |
|---|---|---|---|---|---|
| Chemical Composition (wt.%; balance Al) | |||||
| Mg | 0.05 | 1.2-1.8 | 2.2-2.8 | 0.45-0.9 | 2.1-2.9 |
| Si | 0.25 | 0.5 | 0.2-0.6 | ||
| Mn | 0.05 | 0.3-0.9 | |||
| Cu | 0.05 | 3.8-4.9 | 0.1 | 1.2-1.6 | |
| Cr | 0.1 | 0.15-0.35 | 0.1 | 0.18-0.28 | |
| Zn | 0.07 | 0.25 | 0.1 | 5.1-6.1 | |
| Fe | 0.4 | 0.5 | 0.35 | ||
| Physical Properties | |||||
| Melting point (°C) | 650-660 | 500-640 | 593-649 | 600-652 | 477-638 |
| Density (g/cm3) | 2.71 | 2.77 | 2.7 | 2.71 | 2.8 |
| Coefficient of thermal expansion (×10−6/K) | 24 | 24 | 23.5 | 23.4 | 23.6 |
| Thermal conductivity [W/(m·K)] | 237 | 113 | 135-160 | 180-218 | 121 |
| Specific heat [J/(kg·K)] | 920 | 920 | 921 | 880 | 962 |
| Electrical resistivity (μΩ·cm) | 2.67E-08 | 4.6E-08 | 5.1E-08 | 3.3E-08 | 5.7E-08 |
| Mechanical Properties | |||||
| Elongation (%) | 40/4 | 22A/18T | 25A/7T | 15A/12T | 17A/11T |
| Hardness (HB) | 18-44 | 47A/125T | 45A/100T | 115A/73T | 60A/150T |
| Hardness (HV) | 8-22 | 30-50 | |||
| Charpy impact test (ft·lb/in) | |||||
| Poisson’s ratio | −0.35 | −0.35 | −0.35 | −0.35 | −0.35 |
| Shear strength (MPa) | 30-80 | 124A/537T | 125A/175T | 69A/151T | 151A/331T |
| Tensile (Young’s) modulus (GPa) | 70.6 | 73 | 65-75 | 67 | 72 |
| Tensile strength (MPa) | 70/175 | 186A/495T | 193A/290T | 90A/290T | 227A/572T |
| Ultimate flexural strength (MPa) | |||||
| Yield strength σ0.2 (MPa) | 28-150 | 76A/395T | 89A/255T | 48A/270T | 103A/503T |
Note: A indicates annealed and T indicates aged.
All alloys in the table are wrought aluminum alloys. The 1000 series is commercially pure aluminum with low strength and good ductility. The 2000 series contains copper and magnesium, offers high strength, and can be heat treated, although copper reduces corrosion resistance. Magnesium is the principal alloying element in the 5000 series, which has good corrosion resistance and better mechanical properties than the 1000, 3000, and 4000 series. The heat-treatable 6000 series has lower corrosion resistance than the 5000 series but meets general engineering requirements. The 7000 series is used mainly for specialized aerospace applications and can be heat treated; copper lowers corrosion resistance and weldability but provides pronounced strengthening.
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