7249 Aluminum T7751
metal7249 Aluminum T7751 is a precipitation-hardened Al-Zn-Mg-Cu alloy in an overaged condition providing high strength (typical yield ~455 MPa) with improved stress-corrosion cracking (SCC) resistance compared to underaged tempers, commonly used in aircraft fuselage and wing structures where both damage tolerance and corrosion resistance are critical design requirements.
aerospacestructural
Compliance & Regulations
?Conflict Free?FDA?RoHS?REACH?TSCA?Prop 65
Filter by
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | — | ksi | 22°C · Hand forging | — | |
Poisson's Ratio(ν) | — | - | 22°C | — | |
Shear Modulus(G) | — | ksi | 22°C · Hand forging | — | |
Stress–Strain Curve (buckling region, ≤ 2% strain)(σ–ε (low-strain)) | Curve (18 pts) | ksi | 21°C · LT | — | |
Young's Modulus(E) | — | ksi | 22°C · Hand forging | — |
Rows with are inherited from the base material
Verified Unverified Low confidence (<80%) Link to source
Regulatory Screening
Environmental
Safety & Biocompatibility
Quality & Standards
RoHS, REACH, and Prop 65 statuses are validated against official substance lists (ECHA SVHC Candidate List, OEHHA Prop 65, RoHS Annex II). Other regulations are estimated from composition and material classification. All screening is a starting point for due diligence — always verify with your supplier before making compliance decisions.