7050 T7651 Aluminum plate
7050-T7651 aluminum plate is a specially treated high-strength aerospace-grade aluminum alloy sheet, offering outstanding advantages in performance and durability.
7050-T7651 aluminum plate is a high-strength aluminum alloy material belonging to the 7050 series. This alloy is primarily used in applications requiring high strength and excellent corrosion resistance, such as aerospace, automotive, and high-performance structural components.
7050-T7651 Aluminum Alloy Information
Property | Description |
Material Name | 7050-T7651 Aluminum Alloy |
UNS | A97050 |
ISO Standard | AlZn6CuMgZr |
AA (Aluminum Association) | AA7050-T7651 |
Main Components | Zinc (Zn), Magnesium (Mg), Copper (Cu), Zirconium (Zr) |
Temper | T7651 |
Strength Grade | High Strength |
Applications | Aerospace, Automotive, High-Performance Structural Components |
Characteristics | Excellent Corrosion Resistance, Good Machinability, Maximum Strength |
Processing Methods | Solution Heat Treatment, Stress Relief, Artificial Overaging |
7050-T7651 Aluminum Plate Features and Properties
High Strength
The T7651 temper significantly enhances the material's strength through solution heat treatment, stress relief (stretching), and artificial overaging.
It is one of the highest-strength variants in the 7050 aluminum alloy series, particularly suitable for high-load aerospace structural components.
Excellent Exfoliation Corrosion Resistance
Artificial overaging treatment optimizes exfoliation corrosion resistance, making it suitable for prolonged exposure to high humidity or salt spray environments.
Complies with corrosion resistance standards for aerospace materials, extending the service life of the material.
Good Toughness and Fatigue Performance
Stress relief processing reduces residual stress, improving toughness and fatigue performance, especially advantageous under complex machining and load conditions.
Machinability and Thermal Stability
While ensuring strength, it maintains good machinability, making it suitable for precision component manufacturing.
Exhibits stable performance and minimal deformation after heat treatment, facilitating subsequent applications.
Density and Weight Advantage
As an aluminum alloy, 7050-T7651 maintains a low density (approximately 2.83 g/cm³) while offering strength comparable to steel, reducing the weight of aerospace equipment.
7050-T7651 Aluminum Plate Applications
Aerospace
Used for aircraft wing spars, fuselage frames, and skins to meet the demands for high strength and lightweight performance.
Applied in landing gear components, offering reliable fatigue and corrosion resistance.
Military Equipment
Utilized in critical components of military aircraft and missiles, offering corrosion resistance and high strength for harsh operating conditions.
High-Performance Industrial Equipment
Used in high-precision mold manufacturing and heavy-duty machinery load-bearing components requiring a combination of strength and fatigue resistance.
7050-T7651 Aluminum Plate Processing
Processing Methods:
Solution Heat Treatment: Strengthens the material by dissolving alloying elements through heating.
Stress Relief: Improves material stability by stretching to remove internal stress.
Artificial Overaging: Optimizes mechanical properties and corrosion resistance by controlling temperature and time.
Tensile Stress Control
The plate typically undergoes a certain proportion of tensile stress relief, ensuring flatness and deformation resistance after machining.
Weldability and Surface Treatment
Compared to some other aluminum alloys, its weldability is relatively weaker but can be improved through anodizing, electroplating, or coatings to enhance surface protection.
Aluminum 7050-T7651 - ASM Material Data Sheet
Physical Properties | Metric | English | Comments |
Density | 2.83 g/cc | 0.102 lb/in³ | AA; Typical |
7050 T7651 Mechanical Properties | |||
Hardness, Brinell | 147 | 147 | 500 kg load with 10 mm ball. Calculated value. |
Hardness, Knoop | 187 | 187 | Converted from Brinell Hardness Value |
Hardness, Rockwell A | 53 | 53 | Converted from Brinell Hardness Value |
Hardness, Rockwell B | 86 | 86 | Converted from Brinell Hardness Value |
Hardness, Vickers | 171 | 171 | Converted from Brinell Hardness Value |
Ultimate Tensile Strength | 552 MPa | 80000 psi | AA; Typical |
Tensile Yield Strength | 490 MPa | 71000 psi | AA; Typical |
Elongation at Break | 11 % | 11 % | AA; Typical; 1/2 in. (12.7 mm) Diameter |
Modulus of Elasticity | 71.7 GPa | 10400 ksi | AA; Typical; Average of tension and compression. Compression modulus is about 2% greater than tensile modulus. |
Poisson's Ratio | 0.33 | 0.33 | |
Fracture Toughness | 26 MPa-m½ | 23.7 ksi-in½ | K(IC) in S-L Direction |
Fracture Toughness | 31 MPa-m½ | 28.2 ksi-in½ | K(IC) in T-L Direction |
Fracture Toughness | 34 MPa-m½ | 30.9 ksi-in½ | K(IC) in L-T Direction |
Shear Modulus | 26.9 GPa | 3900 ksi | |
Shear Strength | 324 MPa | 47000 psi | AA; Typical |
7050 T7651 Electrical Properties | |||
Electrical Resistivity | 4.4e-006 ohm-cm | 4.4e-006 ohm-cm |
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7050 T7651 Thermal Properties | |||
CTE, linear 68°F | 23 µm/m-°C | 12.8 µin/in-°F | AA; Typical; Average over 68-212°F range. |
CTE, linear 250°C | 25.4 µm/m-°C | 14.1 µin/in-°F | Average over the range 20-300ºC |
Specific Heat Capacity | 0.86 J/g-°C | 0.206 BTU/lb-°F | |
Thermal Conductivity | 153 W/m-K | 1060 BTU-in/hr-ft²-°F | |
Melting Point | 488 - 629 °C | 910 - 1165 °F | AA; Typical range based on typical composition for wrought products 1/4 inch thickness or greater |
Solidus | 488 °C | 910 °F | AA; Typical |
Liquidus | 629 °C | 1165 °F | AA; Typical |
7050 T7651 Processing Properties | |||
Annealing Temperature | 413 °C | 775 °F | |
Solution Temperature | 477 °C | 890 °F | |
Aging Temperature | 121 - 177 °C | 250 - 350 °F |