214 materials
2024 Aluminum T4 is a copper-aluminum alloy in solution heat-treated and naturally aged condition, providing tensile strength of approximately 70 ksi (485 MPa) with good fatigue resistance and machinability, commonly used in aircraft fuselage skin, wing structures, and high-stress fasteners where moderate strength and damage tolerance are required. The T4 temper offers superior fracture toughness compared to the overaged T3 condition, though with slightly lower strength, making it the preferred specification for critical aerospace structures subject to fatigue and impact loading.
2024-T62 is a precipitation-hardened aluminum-copper alloy in an overaged temper condition, providing tensile strengths of 455–505 MPa with enhanced stress-corrosion cracking (SCC) resistance and improved fracture toughness compared to the T4 temper. This condition is widely specified in aerospace applications requiring sustained high-temperature service and damage-tolerant design, particularly in fuselage structures and wing skins operating in the 65–120 °C range.
2024-T851 is a precipitation-hardened aluminum-copper alloy (4.4% Cu, 1.5% Mg, 0.6% Mn) that combines high strength with controlled ductility through solution treatment, controlled cold work, and stress relief; primary applications include aircraft fuselage skin, wing components, and structural fasteners requiring fatigue resistance and damage tolerance in the -65°F to +250°F service range.
2024-T851X is an age-hardened aluminum-copper alloy (4.4% Cu, 1.5% Mg, 0.6% Mn) in a stress-relieved condition achieved through controlled stretching after solution heat treatment and artificial aging, delivering high strength (yield ~405 MPa, ultimate ~485 MPa) with improved stress-corrosion cracking resistance compared to T4 variants. Primary applications include aircraft fuselage skins, stringers, and other structural components requiring fatigue and damage-tolerance performance in the -55°C to +120°C operating range.
2024-T861 is a precipitation-hardened aluminum-copper alloy (Al-Cu-Mg) subjected to solution heat treatment, controlled stretching, and artificial aging to achieve peak strength and improved stress-corrosion cracking (SCC) resistance. This temper provides tensile strength of approximately 65–73 ksi with enhanced resistance to sustained-load cracking compared to T4, making it suitable for highly stressed aerospace structural components where both strength and SCC resistance are critical.
2219 aluminum alloy T62 is a copper-containing aluminum alloy in the T62 temper (solution heat-treated and artificially aged), providing high strength and improved fracture toughness suitable for cryogenic and elevated-temperature aerospace applications. This condition delivers enhanced stress-corrosion cracking resistance and fatigue performance compared to other 2219 tempers, with capability to -423°F (-252°C) and service temperatures up to 600°F (316°C).
2219 aluminum alloy in T81 temper is a copper-alloyed aluminum system solution heat-treated, artificially aged, and stress-relieved by stretching, providing high strength (yield ~40 ksi, ultimate ~57 ksi) with improved stress-corrosion cracking resistance compared to non-stress-relieved tempers. Primary applications include cryogenic tankage and aerospace structures requiring combined tensile strength and fracture toughness at temperatures down to liquid hydrogen (-423°F).
2219 Aluminum T851 is a copper-alloyed aluminum alloy in a solution heat-treated, stress-relieved, and artificially aged condition, providing high strength at elevated temperatures with good fracture toughness and fatigue resistance. Extensively used in aerospace applications including cryogenic tankage, spacecraft structures, and engine components operating at temperatures up to approximately 300°C.
2219 aluminum alloy T87 is a copper-alloyed aluminum (4.8-6.3% Cu, 0.3% Mn, 0.02% Zr) in artificially aged condition (T87) providing high strength at cryogenic and elevated temperatures (to ~300°C) with good fracture toughness and fatigue resistance. Primary applications include aerospace cryogenic tankage, rocket motor cases, and structural components in space launch vehicles where strength-to-weight ratio and thermal cycling durability are critical.
300M is a chromium-molybdenum-vanadium alloy steel (AISI 4340-type) used in high-strength aerospace applications including landing gear, fasteners, and structural components, offering tensile strengths of 1650–1900 MPa with excellent fatigue resistance and fracture toughness when properly heat-treated.
6061-T651X is a precipitation-hardened aluminum-magnesium-silicon alloy in a stretched temper condition that provides improved dimensional stability and reduced residual stress after solution heat treatment and artificial aging. This condition delivers tensile yield strengths of approximately 40 ksi (276 MPa) with enhanced stress-corrosion cracking resistance, making it suitable for aerospace structures, pressure vessels, and applications requiring tight dimensional tolerances and long-term stability.
7049/7149 Aluminum T7351 is a high-strength aluminum-zinc-magnesium-copper alloy in overaged condition, providing improved stress-corrosion cracking (SCC) resistance compared to T73 while maintaining tensile strength suitable for critical aerospace structures. This temper is used in damage-tolerant airframe applications requiring reduced SCC susceptibility and enhanced fracture toughness in thick sections.
7050-T7351X is a high-strength Al-Zn-Mg-Cu alloy in overaged temper with stress relief, providing yield strengths of 455–480 MPa with enhanced stress-corrosion cracking resistance suitable for critical aerospace structural applications requiring damage tolerance. The T7351X condition delivers improved fracture toughness and environmental cracking resistance compared to T73 by controlled overaging and mechanical stress relief, making it preferred for thick-section forgings and extrusions in military aircraft and pressure vessels.
7050 Aluminum T74 is a high-strength Al-Zn-Mg-Cu alloy in the overaged condition, achieving yield strengths of 435–470 MPa with improved stress-corrosion cracking (SCC) resistance and fracture toughness compared to T73 through controlled thermal aging. This temper is specified for critical aerospace structures, particularly in wings and fuselage applications where sustained tensile loads and corrosive environments demand superior damage tolerance and fatigue performance.
7050 Aluminum T7451 is a high-strength Al-Zn-Mg-Cu alloy in an overaged temper condition, designed to provide improved stress-corrosion cracking (SCC) resistance while maintaining tensile strength suitable for critical aerospace structural applications. T7451 combines solution heat treatment, controlled stretching, and elevated-temperature aging to achieve optimal balance between strength (typically 435–480 MPa yield) and corrosion resistance in thick-section forgings and extrusions.
7050 Aluminum T74511 is a high-strength aluminum-zinc-magnesium-copper alloy in the overaged T74511 condition, which combines stress-relief stretching with controlled overaging to provide enhanced fracture toughness and stress-corrosion-cracking resistance while maintaining tensile strength suitable for critical aerospace structure applications. This temper is specifically designed to mitigate sustained-load cracking in thick-section forgings and extrusions operating in corrosive environments.
7050 Aluminum T7451X is a high-strength Al-Zn-Mg-Cu alloy in an overaged temper condition that combines elevated yield strength (>500 MPa) with improved stress-corrosion cracking (SCC) resistance and fracture toughness suitable for critical aircraft structural applications. The T7451X condition—stress-relieved by stretching and then overaged—provides enhanced resistance to exfoliation corrosion and sustained-load cracking compared to T73, making it preferred for thick-section wing and fuselage components operating in aerospace environments.
7050 is a high-strength Al-Zn-Mg-Cu alloy designed for critical aerospace structures requiring maximum strength-to-weight ratio and damage tolerance. T7651 is an overaged temper (solution heat-treated, stress-relieved by stretching, then artificially aged) that reduces quench sensitivity and stress-corrosion cracking susceptibility while maintaining tensile strength above 500 MPa, making it suitable for thick-section fuselage and wing components in military and commercial aircraft.
7050 Aluminum T7651X is a high-strength Al-Zn-Mg-Cu alloy in an overaged temper condition that provides improved stress-corrosion cracking (SCC) resistance and exfoliation corrosion resistance compared to T73, while maintaining excellent mechanical properties for critical aerospace structural applications. The T7651X condition delivers reduced fracture toughness but enhanced environmental durability, making it suitable for damage-tolerant design in fuselage skins, wing structures, and other components requiring long-term corrosion resistance in marine and high-altitude environments.
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.
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.
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.
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 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.
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.