7075-T62 is an aluminum-zinc alloy in overaged temper, produced by solution heat treatment, controlled stretching, and artificial aging to lower strength than T6 but with improved stress-corrosion cracking (SCC) resistance and fracture toughness. Primary applications are aerospace structures, aircraft fuselage and wing components, and high-strength fasteners where SCC resistance and damage tolerance are critical despite the 5–10% strength reduction compared to T6 condition.
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14 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) | 72.39 | GPa | 22°C · Bar/Rod | ||
Compressive Tangent Modulus vs Stress(Etn(σ))4 entries | Curve (12 pts) | Pa | 21°C · L | ||
| ↳ | Curve (11 pts) | Pa | 21°C · LT | ||
| ↳ | Curve (13 pts) | Pa | 21°C · L | ||
| ↳ | Curve (13 pts) | Pa | 21°C · LT | ||
Poisson's Ratio(ν) | 0.3300 | - | 22°C | ||
Shear Modulus(G) | 26.89 | GPa | 22°C · Bar/Rod | ||
Stress–Strain Curve(σ–ε)2 entries | Curve (14 pts) | Pa | 21°C · L | ||
| ↳ | Curve (12 pts) | Pa | 21°C · LT | ||
Stress–Strain Curve (buckling region, ≤ 2% strain)(σ–ε (low-strain)) | — | Pa | 8 entriesClick to expand | ||
Young's Modulus(E) | 71.02 | GPa | 22°C · Bar/Rod | ||
3 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 | |
|---|---|---|---|---|---|
CTE vs Temperature(α(T)) | Curve (5 pts) | 1/K | — | ||
Specific Heat vs Temperature(Cp(T)) | Curve (5 pts) | J/(kg·K) | — | ||
Thermal Conductivity vs Temperature(k(T)) | Curve (4 pts) | W/(m·K) | — |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Density(ρ) | 2.796 | kg/m³ | 22°C |