7049/7149 Aluminum T77511 is a high-strength Al-Zn-Mg-Cu alloy in the overaged T77511 temper (solution heat-treated, stress-relieved by stretching, and artificially aged) designed for aircraft structural applications requiring balanced strength, fracture toughness, and stress-corrosion cracking (SCC) resistance. This temper provides yield strengths in the 435–475 MPa range with improved SCC resistance compared to peak-aged conditions, making it suitable for thick-section fuselage components and wing structures in military and commercial aircraft.
Compliance & Regulations
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 | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | 73.08 | GPa | 22°C · Hand forging | ||
Poisson's Ratio(ν) | 0.3300 | - | 22°C | ||
Shear Modulus(G) | 26.89 | GPa | 22°C · Die forging | ||
S–N Curve (Wöhler)(S–N)3 entries | Curve (11 pts) | Pa | — | ||
| ↳ | Curve (15 pts) | Pa | — | ||
| ↳ | Curve (16 pts) | Pa | — | ||
Young's Modulus(E) | 70.33 | GPa | 22°C · Die forging |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Density(ρ) | 2.851 | kg/m³ | 22°C |