371 materials
Ti-6Al-4V (titanium–6% aluminum–4% vanadium) is a two-phase alpha-beta titanium alloy manufactured via laser powder bed fusion (L-PBF) and stress-relieved to reduce residual stresses from the additive manufacturing process. This material combines the lightweight, corrosion-resistant properties of titanium with excellent strength-to-weight ratio, making it a preferred choice for aerospace, medical device, and demanding industrial applications where weight savings and durability are critical. The L-PBF processing route enables complex near-net-shape geometries and reduced material waste compared to wrought forms, though the stress-relieved condition represents an intermediate heat treatment state positioned between as-built and fully annealed material.
Ti-6Al-4V STA is a solution heat-treated and aged (STA) condition of the titanium alloy Ti-6Al-4V, providing improved strength and creep resistance compared to annealed conditions through precipitation hardening, with typical yield strengths in the 140–160 ksi range. This condition is widely used in aerospace applications including jet engine compressor blades, landing gear, and airframe components requiring high specific strength, fatigue resistance, and reliable performance up to approximately 300°C.
Ti-6Al-6V-2Sn is a near-alpha titanium alloy containing 6% aluminum, 6% vanadium, and 2% tin, designed for elevated-temperature aerospace applications requiring moderate strength and creep resistance up to approximately 600°C. The alloy offers good fatigue performance and weldability with moderate density, making it suitable for jet engine components, airframes, and other high-temperature structural applications.
Ti-6Al-6V-2Sn is a near-alpha titanium alloy combining aluminum and vanadium for strength with tin for elevated-temperature stability, commonly used in gas turbine engines and airframes requiring sustained performance to approximately 600°C. The annealed condition provides a stable microstructure with moderate strength and good ductility, suitable for components requiring damage tolerance and fracture toughness over maximum strength.
Ti-6Al-6V-2Sn is a near-alpha titanium alloy containing 6% aluminum, 6% vanadium, and 2% tin, designed for elevated-temperature aerospace applications requiring high strength retention to approximately 600°C. The STA (solution-treated and aged) condition provides a controlled microstructure with excellent creep resistance, high yield and tensile strength, and good fracture toughness, making it suitable for compressor blades, casings, and other critical jet engine and airframe components.
Ti-6Al-7Nb is a near-alpha titanium alloy that substitutes niobium for vanadium in the classic Ti-6Al-4V formulation, eliminating concerns about vanadium cytotoxicity in biomedical applications. It is widely used in orthopedic and dental implants, cardiovascular devices, and surgical instruments where biocompatibility, corrosion resistance, and load-bearing reliability are critical. Engineers select this alloy over Ti-6Al-4V specifically for long-term implantable devices where material-body interaction must be minimized, while maintaining comparable mechanical performance and superior fatigue resistance in cyclic loading environments.
Ti-8Al-1Mo-1V is a near-alpha titanium alloy with moderate strength and superior creep resistance, designed for elevated-temperature aerospace applications requiring service to approximately 1200°F. The alloy combines aluminum for strength and low density with molybdenum and vanadium for creep and heat-resistance properties, with Duplex Annealed condition providing optimized toughness and Solution Treated condition delivering maximum strength.
Ti-8Al-1Mo-1V is a near-alpha titanium alloy with moderate strength and excellent creep resistance, designed for elevated-temperature applications in jet engines and gas turbines. Duplex Annealed condition provides balanced strength and ductility through dual-phase heat treatment, yielding tensile strengths in the 140–160 ksi range with good elongation for damage-tolerant design in aircraft powerplant components operating to approximately 600°C.
Ti-8Al-1Mo-1V is an alpha-beta titanium alloy with moderate strength and excellent creep resistance, used primarily in aerospace gas turbine engines and high-temperature structural applications. The solution-treated condition provides optimal combination of strength and ductility for forged components operating at temperatures up to 300°C, as defined in AMS 4973.
Udimet 720 is a nickel-based superalloy designed for high-temperature structural applications requiring exceptional strength retention at elevated temperatures. It is widely used in jet engine components—particularly turbine blades, vanes, and casings—where it must withstand sustained thermal cycling and mechanical stress in the 700–800 °C operating range. Engineers select Udimet 720 over conventional superalloys when creep resistance, fatigue life, and damage tolerance are critical in demanding aerospace and power-generation environments.
Nickel-based superalloy (Ni-19.5Cr-13.5Co-4.3Mo-3Al-1.4Ti). 795 MPa yield, 1275 MPa UTS. Workhorse disc alloy for intermediate-temperature turbine stages (up to ~700°C). Good forgeability and weldability for a superalloy.
Waspaloy is a nickel-based superalloy containing cobalt, chromium, molybdenum, and tungsten alloying elements, designed for high-temperature structural applications in gas turbine engines and other demanding aerospace environments. The solution, stabilization, and precipitation heat-treated condition provides optimized strength and creep resistance through controlled gamma-prime precipitation, with tensile properties (yield strength, ultimate tensile strength, elongation, and reduction of area) suitable for elevated-temperature service up to approximately 1200°F (650°C).
ZE41A is a magnesium alloy containing zinc and rare-earth elements (primarily cerium mischmetal), designed for elevated-temperature aerospace applications requiring good creep resistance and castability. The T5 temper (artificially aged without prior solution heat treatment) provides moderate strength and improved dimensional stability for service up to approximately 250°C.
ZE41A is a magnesium alloy containing zinc, rare earth elements, and zirconium, designed for elevated-temperature aerospace castings requiring moderate strength and creep resistance up to approximately 150°C. The T5 temper (artificially aged) provides improved yield and bearing strength characteristics in sand-cast form per AMS 4439, suitable for engine components and structural aircraft parts operating under sustained thermal loads.
ZK60A is a high-strength magnesium alloy containing zinc and zirconium, used in aerospace and defense applications requiring excellent strength-to-weight ratio and moderate elevated-temperature capability. The alloy provides superior creep resistance compared to other magnesium alloys, with T5 temper offering improved mechanical properties through controlled heat treatment and natural aging.
ZK60A-F is a magnesium alloy containing zinc and zirconium, used in aerospace applications requiring lightweight structural components with moderate strength and operating temperatures up to approximately 150°C; the F (as-fabricated) temper represents the material in its extruded condition without heat treatment, providing consistent properties suitable for cast and wrought magnesium applications per ASTM B 107.
ZK60A is a magnesium alloy containing zinc and zirconium, heat-treated to the T5 condition (stress-relieved after artificial aging) for use in aerospace forgings and extrusions requiring moderate strength and creep resistance at elevated temperatures. T5 condition provides improved dimensional stability and controlled strength levels suitable for structural applications in aircraft engines and airframes, with yield strength around 25-35 ksi and operating capability to approximately 250°C.
17-4PH Stainless Steel in the F (as-fabricated) condition is a precipitation-hardening martensitic stainless steel used primarily in aerospace and defense applications for components requiring high strength and corrosion resistance. The F condition represents the material in its initial state following fabrication but prior to precipitation hardening heat treatment, offering lower strength and hardness compared to the H900/H1025 aged conditions, with moderate toughness suitable for machining and forming operations.
2014 Aluminum T651 is a copper-alloyed aerospace aluminum with solution heat treatment, stress relief, and artificial aging, delivering tensile strength of approximately 70–75 ksi with enhanced fatigue resistance and dimensional stability for structural aircraft components. The T651 temper provides improved crack resistance compared to T4 while maintaining good machinability, making it suitable for forged and machined airframe fittings, wings, and fuselage sections where fatigue and sustained loads are critical.
2014 aluminum (T651X) is a copper-alloyed wrought aluminum alloy in an artificial age-hardened condition with controlled stretching, providing high strength (ultimate tensile strength ~70 ksi / 485 MPa) and improved stress-relief characteristics suitable for aerospace structural applications. The T651X temper delivers enhanced fracture toughness and reduced quench sensitivity compared to unstretched T651, making it preferred for thick-section forgings and extrusions in critical load-bearing components where damage tolerance is required.
2024 Aluminum T351 is a solution heat-treated and stress-relieved aluminum-copper alloy (nominally 4.4% Cu, 1.5% Mg, 0.6% Mn) used in high-strength aerospace and defense structures. The T351 temper provides excellent fatigue resistance and fracture toughness through controlled stress relief, making it the preferred condition for aircraft wing skins, fuselage components, and highly stressed fasteners operating in service environments.
2024 Aluminum T351X is a copper-aluminum alloy in an artificially aged condition following solution heat treatment and stress relief stretching, providing high strength-to-weight ratio (ultimate tensile strength ~70 ksi) with improved stress-corrosion cracking resistance compared to T4 temper. Primary applications include aircraft fuselage skin, wing components, and fasteners requiring sustained strength at elevated temperatures up to ~300°F with controlled residual stress levels.
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.
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.
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.
7050 aluminum T77511 is a high-strength Al-Zn-Mg-Cu alloy in overaged condition with controlled stretching, providing tensile strength around 470–500 MPa with improved stress-corrosion cracking (SCC) resistance compared to T7351, suitable for highly stressed aerospace structures including aircraft fuselage and wing components.
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.