7175-T61511 is a high-strength aluminum-zinc-magnesium-copper alloy in a thermally-treated and cold-worked condition, providing tensile yield strengths of approximately 70–75 ksi with improved fracture toughness and stress-corrosion cracking (SCC) resistance compared to overaged T7 tempers. This temper is used in critical aerospace structures including aircraft wing skins and fuselage components where a balance of high strength, damage tolerance, and corrosion resistance is required under sustained tensile stress.
Compliance & Regulations
1 interactive curve 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) | 73.77 | GPa | 22°C · Die forging | ||
Poisson's Ratio(ν) | 0.3300 | - | 22°C | ||
Shear Modulus(G) | 20.68 | GPa | 22°C · Extrusion | ||
S–N Curve (Wöhler)(S–N) | Curve (40 pts) | Pa | 21°C · L | ||
Young's Modulus(E) | 70.33 | GPa | 22°C · Die forging |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Density(ρ) | 2.796 | kg/m³ | 22°C |