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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
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