448 materials
7075-T62 is an aluminum-zinc alloy in overaged temper, produced by solution heat treatment, controlled stretching, and artificial aging to lower strength than T6 but with improved stress-corrosion cracking (SCC) resistance and fracture toughness. Primary applications are aerospace structures, aircraft fuselage and wing components, and high-strength fasteners where SCC resistance and damage tolerance are critical despite the 5–10% strength reduction compared to T6 condition.
7075-T651 is a precipitation-hardened aluminum-zinc-magnesium-copper alloy in a solution heat-treated, stress-relieved, and artificially aged condition, providing tensile strengths of 70–75 ksi (480–520 MPa) with improved stress-corrosion cracking resistance compared to T6. Widely used in aerospace structures, pressure vessels, and highly loaded components requiring high strength-to-weight ratio and controlled residual stress levels.
7075 Aluminum T651X is a precipitation-hardened aluminum-zinc-magnesium-copper alloy in the T651X condition, offering the highest strength-to-weight ratio of wrought aluminum alloys with tensile strengths typically 70–78 ksi, suitable for critical aircraft structural components, fasteners, and aerospace applications requiring fatigue resistance. The T651X condition (solution heat-treated, artificially aged, and stress-relieved by stretching) provides dimensional stability, reduced residual stress, and improved fracture toughness compared to T6, with operating capability up to approximately 250°F, though notch sensitivity and stress-corrosion cracking susceptibility require careful design and protective measures in marine or chloride-bearing environments.
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.
7075 Aluminum T7352 is a high-strength aluminum-zinc alloy (Al-Zn-Mg-Cu) in an overaged temper condition that provides improved stress-corrosion cracking (SCC) resistance compared to T6, with slight sacrifice in yield strength, suitable for critical aircraft structures and pressure vessels exposed to sustained tensile stresses in marine and aerospace environments.
7075 Aluminum T77511 is a precipitation-hardened aluminum-zinc alloy (with copper and magnesium) in an overaged condition that provides high static strength and improved stress-corrosion cracking (SCC) resistance compared to T73 tempers, with reduced notch sensitivity. This temper is commonly specified in aerospace structures where both damage tolerance and resistance to sustained tensile stress in corrosive environments are critical requirements.
7175-T74 is a high-strength aluminum alloy (Zn-Cu-Mg system) in overaged temper, used primarily in aerospace airframes and structures requiring damage-tolerance capability. The T74 condition provides improved stress-corrosion cracking (SCC) resistance and fracture toughness compared to T6, with slightly reduced yield strength, making it suitable for critical aircraft components subject to sustained loads in marine or corrosive environments.
7175 Aluminum T7452 is a high-strength Al-Zn-Mg-Cu alloy in overaged temper, providing excellent stress-corrosion cracking (SCC) resistance with tensile strengths around 435–450 MPa, used primarily in aerospace structures and aircraft components where sustained load and corrosion resistance are critical. The T7452 condition applies controlled overaging and stretching to enhance resistance to intergranular corrosion and SCC while maintaining good fracture toughness compared to the higher-strength T73 tempers.
7175 aluminum T77511 is a high-strength Al-Zn-Mg-Cu alloy in a stabilized temper condition (solution heat-treated, cold-worked, and artificially aged with stress relief) designed for aerospace structural applications requiring sustained elevated temperature performance and stress-corrosion cracking (SCC) resistance. This temper provides tensile yield strength approximately 70–75 ksi with improved toughness and SCC resistance compared to T73 conditions, making it suitable for critical airframe components, fasteners, and pressure vessels in aircraft where long-term thermal and mechanical stability is essential.
7249 aluminum alloy is a zinc-primary precipitation-hardened alloy designed for high-strength aerospace applications requiring excellent fracture toughness and stress-corrosion cracking resistance. The T77511 temper (solution heat-treated, stretched, and artificially aged) provides yield strengths of 415–450 MPa with enhanced toughness and dimensional stability, suitable for critical aircraft structural components operating in high-stress environments.
7475 Aluminum T7351 is a high-strength Al-Zn-Mg-Cu alloy in a stabilized temper condition, providing reduced quench sensitivity and improved stress-corrosion cracking (SCC) resistance compared to T73 through controlled overaging. Primary applications include aerospace structures, fuselage skin, and components requiring sustained strength at service temperatures up to 150°C, with typical yield strengths in the 380–430 MPa range and fracture toughness superior to T7 tempers.
7475 Aluminum T77511 is a high-strength aluminum-zinc-magnesium-copper alloy in a highly-worked temper condition, providing tensile strengths typically in the 500–580 MPa range with improved stress-corrosion cracking (SCC) resistance compared to T73 tempers through controlled overaging. Applications include aircraft structural components, landing gear, and fasteners requiring optimal combinations of strength, fatigue resistance, and fracture toughness in sustained-load environments.
A-286 is an iron-nickel-cobalt superalloy strengthened by gamma-prime precipitation, used in gas turbine engines and high-temperature aerospace applications requiring strength retention to approximately 1,300°F. The F temper represents the as-fabricated condition (annealed after final fabrication without further heat treatment), providing moderate strength and good ductility suitable for demanding structural applications.
A356.0 T6P is a cast aluminum-silicon alloy (7–8% Si) solution heat-treated and precipitation-hardened with thermal stress relief, used primarily in aerospace and automotive applications requiring moderate strength and good castability. The T6P condition provides improved dimensional stability and reduced residual stress compared to standard T6, making it suitable for precision cast components requiring tight tolerances.
AISI 4130 is a chromium-molybdenum alloy steel (0.28–0.33% C, 0.8–1.1% Cr, 0.15–0.25% Mo) widely used in aerospace structures, pressure vessels, and fasteners where moderate strength combined with good fracture toughness and weldability are required. It exhibits tensile strengths of 1,100–1,500 MPa depending on heat treatment, maintains reasonable toughness to moderate temperatures, and offers good fatigue resistance and machinability.
AISI 4340 steel in condition F is a nickel-chromium-molybdenum alloy (0.38-0.43% C, 1.65-2.0% Ni, 0.7-0.9% Cr, 0.2-0.3% Mo) quenched and tempered to achieve high strength with controlled toughness, suitable for high-strength structural components in aerospace and defense applications. Condition F typically provides tensile strengths in the 260–280 ksi range with good fatigue resistance and fracture toughness, making it suitable for critical load-bearing parts such as landing gear, fasteners, and transmission components.
AISI 8630 is a nickel-chromium-molybdenum alloy steel (0.28–0.33% C, 0.55–0.75% Ni, 0.40–0.60% Cr, 0.15–0.25% Mo) used primarily in aerospace applications for landing gear, fasteners, and highly stressed structural components requiring high strength and fatigue resistance. The alloy provides yield strengths in the range of 180–280 ksi depending on heat treatment and section size, with good toughness and moderate hardenability suitable for medium-section forgings and bars.
AZ31B-F is a magnesium alloy containing aluminum and zinc in the as-fabricated (annealed) condition, offering moderate strength and good formability for applications in aerospace components, automotive structures, and general engineering where weight reduction is critical. The F temper provides lower strength compared to aged conditions but maintains excellent ductility and machinability, making it suitable for formed and machined parts operating at temperatures up to approximately 150°C.
Clad 7475-T7351 is a high-strength aluminum alloy (7xxx series, zinc-primary) with a thin corrosion-resistant aluminum or aluminum-alloy cladding layer, solution heat-treated, stress-relieved by controlled stretching, and artificially aged to T7351 condition for maximum stress-corrosion cracking (SCC) resistance while maintaining high yield strength (typically 415–435 MPa). This temper is specified for critical aerospace structures, particularly fuselage skins and other damage-tolerant applications where both strength and SCC resistance in marine or humid environments are required.
Clad 7475 aluminum alloy T77511 is a high-strength aluminum-zinc-magnesium-copper alloy with an alclad surface layer, thermomechanically treated to peak aging with controlled stretching, providing excellent fracture toughness and stress-corrosion-cracking resistance for critical aerospace structures. The T77511 temper achieves tensile strengths of 70–80 ksi with superior damage tolerance compared to overaged tempers, making it suitable for highly stressed fuselage and wing components where fatigue and corrosion resistance are essential.
Inconel 718 is a nickel-iron-based superalloy strengthened by γ'' (Ni₃Nb) precipitates, used extensively in jet engines, gas turbines, and high-temperature aerospace applications requiring strength retention to ~650°C. The F condition is the as-fabricated state (annealed after final fabrication without precipitation hardening), providing lower strength but superior ductility and machinability compared to aged conditions, making it suitable for applications requiring post-delivery aging or intermediate machining operations.
PH15-7Mo is a precipitation-hardening martensitic stainless steel containing 15% chromium, 7% molybdenum, and aluminum as a strengthening agent, offering high strength and corrosion resistance for aerospace and fastener applications. The F condition (as-forged) represents the material in its initial forged state prior to heat treatment, providing baseline mechanical properties and serving as a reference condition before applying precipitation-hardening cycles.
Ti-13V-11Cr-3Al in the F (as-fabricated) condition is a metastable beta titanium alloy used in aerospace fasteners and structural components requiring high strength and fatigue resistance; the F temper provides strength in the 1,200–1,400 MPa range without solution treatment, making it suitable for applications where dimensional stability and repeatable mechanical properties are critical.
Ti-15V-3Cr-3Sn-3Al STA is a metastable beta titanium alloy in solution-treated and aged condition, combining high strength (typically 1200-1400 MPa tensile strength) with excellent fracture toughness and damage tolerance for aerospace fasteners and structural components. The STA condition provides optimized strength-toughness balance through controlled precipitation hardening while maintaining good fatigue resistance and low-temperature impact properties required in critical airframe applications.
Ti-6Al-4V in the F (annealed) condition is a two-phase alpha-beta titanium alloy with 6% aluminum and 4% vanadium, used extensively in aerospace applications including aircraft frames, engines, and fasteners. The F temper provides optimal ductility and fracture toughness through stress-relief annealing, sacrificing some strength compared to aged conditions but delivering enhanced damage tolerance and machinability suitable for complex fabrication.