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Aluminum Alloy 7075
The 7075 aluminum alloy is primarily composed of zinc, which makes up around 5.6–6.1%, along with 2.1–2.5% magnesium, 1.2–1.6% copper, and trace amounts of other elements such as silicon, iron, manganese, titanium, chromium, and others. It is available in various conditions, including 7075-0, 7075-T6, and 7075-T651. This alloy is notable for its high strength-to-weight ratio, making it ideal for demanding applications.
The 7075 aluminum alloy is well-known for its impressive mechanical properties. It offers excellent ductility, high strength, and toughness, along with great fatigue resistance. While it is more brittle due to microsegregation compared to many other aluminum alloys, it boasts superior corrosion resistance when compared to the 2000 series alloys. As a result, it is extensively utilized in high-stress structural applications, particularly in aircraft structures.
Mechanical Properties of 7075 Plate:
**7075-T6**
In the T6 temper, 7075 aluminum alloy achieves an ultimate tensile strength ranging from 510–540 MPa (approximately 74,000–78,000 psi), with a yield strength of at least 430–480 MPa (63,000–69,000 psi). Its elongation at break is between 5–11%.
To achieve the T6 temper, the alloy undergoes a process involving homogenization at 450 °C for several hours, followed by rapid quenching and aging at 120 °C for 24 hours. This treatment maximizes the alloy's strength by dispersing fine eta and eta' precipitates throughout the grains and grain boundaries.
**7075-T651**
For the T651 temper, the 7075 plate reaches an ultimate tensile strength of 570 MPa (around 83,000 psi) and a yield strength of 500 MPa (73,000 psi), with an elongation at break of 3–9%. These properties can vary slightly depending on the specific form of the material. For instance, thicker plates might have lower strength and elongation values than those listed here.
The T651 temper involves a sequence of steps: solution heat treatment, stress relief, and artificial aging. Stress relief is achieved by stretching the material according to the type of product being manufactured, whether it’s sheet, plate, bar, or forging.
Below is a table summarizing some typical mechanical properties of 7075 sheets:
| Material | Temper | Thickness (in) | Tensile Strength (ksi) | Yield Strength (ksi) | Elongation (%) |
|--------------------------|--------------|----------------|-------------------------|----------------------|----------------|
| Alloy 7075 Sheet | T6 Bare | 0.125 - 0.25 | 78 | 69 | 8 |
| Alloy 7075 Sheet | T651 Bare | 0.25 - 0.50 | 78 | 67 | 9 |
| Alloy 7075 Sheet | T651 Bare | 0.5 - 1.0 | 78 | 68 | 7 |
| Alloy 7075 Sheet | T6 Clad | 0.188 - 0.25 | 75 | 64 | 8 |
| Alloy 7075 Sheet | T651 Clad | 0.25 - 0.50 | 75 | 65 | 9 |
| Alloy 7075 Sheet | T651 Clad | 0.5 - 1.00 | 78 | 68 | 7 |
**Typical Physical Properties**
| Characteristic | English | Metric |
|----------------------------|-------------------------------|-------------------------------|
| Nominal Density | 0.101 lbs./in³ | 2.80 Mg/m³ |
| Melting Range | 990° F - 1175° F | 532°C - 635°C |
| Specific Heat | 0.23 BTU/lb-°F | 960 J/kg-°K |
This alloy remains a favorite choice for aerospace engineering due to its exceptional strength and durability. Engineers continue to explore new ways to optimize its performance in critical applications.