Jan. 20, 2025
Both alloys are very strong, with 7075 aluminum typically being more widely used in structural applications, while 2618 aluminum is generally used in high-temperature environments.
Both 2618 and 7075 aluminum alloys are high-performance materials used in demanding applications like aerospace and automotive industries. While they share similarities, their unique properties make them suitable for different uses.
Both alloys are invaluable, but the choice between them largely depends on the specific requirements of the application, such as the need for heat resistance, strength, machinability, and overall performance under stress.
| Properties | 2618 Aluminum Alloy | 7075 Aluminum Alloy |
| Tensile Strength | Lower, but suitable for high-strength parts | Higher, suitable for high-strength structural applications |
| Elongation | Higher, with good formability | Lower, suitable for high-strength parts |
| Fatigue Strength | Higher, suitable for fatigue-resistant applications | Broader range, suitable for working under repeated stress conditions |
| Shear Strength | Higher, suitable for applications subjected to shear forces | Higher, suitable for applications with high shear forces |
| Maximum Working Temperature | Higher, suitable for high-temperature environments | Lower, suitable for medium to low-temperature working environments |
| Thermal Conductivity | Higher, suitable for applications requiring heat management | Lower, affecting stability at high temperatures |
| Melting Point | Higher, suitable for high-temperature processing | Higher, suitable for high-temperature processing |
| Electrical Conductivity | Higher, suitable for conductive applications | Lower, suitable for applications with lower conductivity |
| Density | Lower, suitable for lightweight designs | Higher, suitable for applications where weight is not critical |
| Cost | Similar, possibly cheaper | More expensive, due to widespread use and higher strength |
| Main Components | Higher copper and nickel content, suitable for high-temperature performance | Higher zinc content, providing excellent strength and fatigue resistance |
| Main Applications | High-temperature, high-strength parts, engine components, racing, etc. | High-strength structural parts, aerospace, military, etc. |
| Property | 2618 Aluminum | 7075 Aluminum |
| Elastic Modulus (GPa) | 71 | 70 |
| Elongation at Break (%) | 5.8 | 1.8 to 12 |
| Fatigue Strength (MPa) | 110 | 110 to 190 |
| Poisson's Ratio | 0.33 | 0.32 |
| Shear Modulus (GPa) | 27 | 26 |
| Shear Strength (MPa) | 260 | 150 to 340 |
| Tensile Strength: Ultimate (MPa) | 420 | 240 to 590 |
| Tensile Strength: Yield (MPa) | 350 | 120 to 510 |
| Property | 2618 Aluminum | 7075 Aluminum |
| Latent Heat of Fusion (J/g) | 390 | 380 |
| Maximum Temperature: Mechanical (°C) | 210 | 200 |
| Melting Completion (Liquidus) (°C) | 640 | 640 |
| Melting Onset (Solidus) (°C) | 550 | 480 |
| Specific Heat Capacity (J/kg-K) | 880 | 870 |
| Thermal Conductivity (W/m-K) | 160 | 130 |
| Thermal Expansion (µm/m-K) | 22 | 23 |
| Property | 2618 Aluminum | 7075 Aluminum |
| Electrical Conductivity: Equal Volume (% IACS) | 37 | 33 |
| Electrical Conductivity: Equal Weight (% IACS) | 110 | 98 |
| Element | 2618 Aluminum | 7075 Aluminum |
| Aluminum (Al) (%) | 92.4 to 94.9 | 86.9 to 91.4 |
| Chromium (Cr) (%) | 0 | 0.18 to 0.28 |
| Copper (Cu) (%) | 1.9 to 2.7 | 1.2 to 2.0 |
| Iron (Fe) (%) | 0.9 to 1.3 | 0 to 0.5 |
| Magnesium (Mg) (%) | 1.3 to 1.8 | 2.1 to 2.9 |
| Manganese (Mn) (%) | 0 | 0 to 0.3 |
| Nickel (Ni) (%) | 0.9 to 1.2 | 0 |
| Silicon (Si) (%) | 0.1 to 0.25 | 0 to 0.4 |
| Titanium (Ti) (%) | 0.040 to 0.1 | 0 to 0.2 |
| Zinc (Zn) (%) | 0 to 0.1 | 5.1 to 6.1 |
| Zirconium (Zr) (%) | 0 | 0 to 0.25 |
| Residuals (%) | 0 | 0 to 0.15 |
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