7075-T7351X is a precipitation-hardened aluminum-zinc-magnesium-copper alloy in an overaged temper with controlled stretching, designed to minimize stress-corrosion cracking susceptibility while maintaining high strength (typical yield ~435 MPa) for critical aerospace structural applications. The T7351X condition provides improved resistance to stress-corrosion cracking and exfoliation corrosion compared to T6, making it suitable for highly stressed components in aircraft fuselages and wing structures where environment-assisted cracking risk must be controlled.
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8 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))2 entries | Curve (14 pts) | Pa | 21°C · L | ||
| ↳ | Curve (14 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 (18 pts) | Pa | 21°C · L | ||
| ↳ | Curve (15 pts) | Pa | 21°C · LT | ||
Stress–Strain Curve (buckling region, ≤ 2% strain)(σ–ε (low-strain))4 entries | Curve (10 pts) | Pa | 21°C · L | ||
| ↳ | Curve (9 pts) | Pa | 21°C · L | ||
| ↳ | Curve (10 pts) | Pa | 21°C · LT | ||
| ↳ | Curve (8 pts) | Pa | 21°C · LT | ||
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 |