2124 aluminum alloy is a Cu-containing aerospace aluminum with high strength-to-weight ratio, used primarily in aircraft fuselage and structural applications requiring elevated temperature performance. T851 temper (solution heat-treated, stress-relieved, and overaged) provides controlled strength with improved stress-corrosion cracking resistance suitable for critical loaded components.
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23 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 | |
|---|---|---|---|---|---|
Ultimate Bearing Strength(Fbru) | 641.2 – 896.3 | MPa | 20 entriesClick to expand | ||
Bearing Yield Strength(Fbry) | 544.7 – 682.6 | MPa | 20 entriesClick to expand | ||
Compressive Tangent Modulus vs Stress(Etn(σ))3 entries | Curve (13 pts) | Pa | 21°C · L | ||
| ↳ | Curve (13 pts) | Pa | 21°C · LT | ||
| ↳ | Curve (15 pts) | Pa | 21°C · ST | ||
Compressive Yield Strength(Fcy) | 358.5 – 427.5 | MPa | 32 entriesClick to expand | ||
Elongation at Break(εf) | 1.500 – 6.000 | - | 19 entriesClick to expand | ||
Fatigue Crack Growth Rate(da/dN) | — | m/cycle | 12 entriesClick to expand | ||
Shear Modulus(G) | 27.58 | GPa | 22°C · Plate | ||
Ultimate Shear Strength(Fsu) | 241.3 – 268.9 | MPa | 30 entriesClick to expand | ||
Stress–Strain Curve (buckling region, ≤ 2% strain)(σ–ε (low-strain)) | — | Pa | 6 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 399.9 – 468.8 | MPa | 34 entriesClick to expand | ||
Yield Strength (0.2% offset)(σy) | 351.6 – 420.6 | MPa | 34 entriesClick to expand | ||