7050 Aluminum T61511 is a high-strength Al-Zn-Mg-Cu alloy in a artificially aged temper (T61511 indicates solution heat-treated, stress-relieved by stretching, then aged) designed for aerospace structures requiring maximum strength-to-weight ratio with improved stress-corrosion cracking (SCC) resistance compared to T7351. This temper delivers tensile strengths in the 70–74 ksi range with enhanced fracture toughness and reduced susceptibility to SCC in thick sections, making it suitable for critical aircraft fuselage and wing components.
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2 interactive curves for this material
Stress-strain, S-N fatigue and environmental knockdown curves are free with an account.
Create free account| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | 73.08 | GPa | 22°C · Hand Forging | ||
Compressive Tangent Modulus vs Stress(Etn(σ)) | Curve (10 pts) | Pa | 21°C · L | ||
Poisson's Ratio(ν) | 0.3300 | - | 22°C | ||
Shear Modulus(G) | 26.89 | GPa | 22°C · Hand Forging | ||
Stress–Strain Curve (buckling region, ≤ 2% strain)(σ–ε (low-strain)) | Curve (7 pts) | Pa | 21°C · L | ||
Young's Modulus(E) | 70.33 | GPa | 22°C · Hand Forging |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Density(ρ) | 2.823 | kg/m³ | 22°C |