7050 is a zinc-copper aluminum alloy with exceptional strength-to-weight ratio and fracture toughness, used primarily in aerospace airframe structures, wings, and fuselage components operating at elevated temperatures. Available in multiple overaged and peak-aged tempers (T6151 through T7751) that balance yield strength (typically 350–520 MPa depending on temper) with improved stress-corrosion cracking resistance and fatigue performance for critical load-bearing applications.
Compliance & Regulations
6 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) | 10,600 | ksi | 22°C · Hand Forging | ||
Compressive Tangent Modulus vs Stress(Etn(σ))2 entries | Curve (10 pts) | ksi | 21°C · L | ||
| ↳ | Curve (11 pts) | ksi | 21°C · LT | ||
Poisson's Ratio(ν) | 0.3300 | - | 22°C | ||
Shear Modulus(G) | 3,900 | ksi | 22°C · Hand Forging | ||
Stress–Strain Curve (buckling region, ≤ 2% strain)(σ–ε (low-strain))4 entries | Curve (7 pts) | ksi | 21°C · L | ||
| ↳ | Curve (8 pts) | ksi | 21°C · LT | ||
| ↳ | Curve (7 pts) | ksi | 21°C · L | ||
| ↳ | Curve (7 pts) | ksi | 21°C · LT | ||
Young's Modulus(E) | 10,200 | ksi | 22°C · Hand Forging |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Density(ρ) | 0.1020 | lb/in³ | 22°C |