448 materials
Ti-13V-11Cr-3Al is a metastable beta titanium alloy containing vanadium and chromium additions for enhanced strength and hardenability, primarily used in aerospace fasteners, springs, and bearing applications. The annealed condition provides moderate strength levels (approximately 130–150 ksi yield) with improved ductility and fracture toughness compared to aged conditions, suitable for applications requiring good fatigue resistance and damage tolerance.
Ti-13V-11Cr-3Al is a metastable beta titanium alloy containing 13% vanadium, 11% chromium, and 3% aluminum, designed for high-strength aerospace fastener and structural applications requiring superior bearing strength and fatigue resistance. The STA (solution-treated and aged) condition provides yield strengths in the 1,200–1,400 MPa range with excellent compressive properties and damage tolerance, making it suitable for critical bearing surfaces and highly stressed mechanical components in aircraft structures and engines.
Ti-15Mo is a metastable beta-phase titanium alloy containing 15 wt% molybdenum, designed to combine the corrosion resistance and biocompatibility of titanium with the strength and lower modulus benefits of beta-stabilized microstructures. It is used in biomedical implants (orthopedic and dental), aerospace components, and chemical processing equipment where corrosion resistance, biocompatibility, and moderate strength are prioritized; compared to α+β titanium alloys like Ti-6Al-4V, Ti-15Mo offers improved corrosion resistance and lower stiffness while maintaining good strength, making it particularly valuable in load-bearing implants where modulus matching to bone or tissue is beneficial.
Ti-15V-3Cr-3Sn-3Al is a metastable beta titanium alloy designed for high-strength aerospace applications requiring excellent damage tolerance and fatigue resistance. The alloy offers tensile strengths exceeding 150 ksi with good fracture toughness, making it suitable for aircraft fuselage structure, fasteners, and landing gear components.
Ti-15V-3Cr-3Sn-3Al is a near-beta titanium alloy designed for high-strength applications requiring excellent damage tolerance and formability, with applications in aerospace fasteners, springs, and structural components. The STA (solution treated and aged at 1000°F for 8 hours) condition provides optimized strength and ductility balance, typically yielding tensile strengths in the 140-160 ksi range with good fatigue resistance and fracture toughness retention.
Alpha titanium alloy with excellent weldability and cryogenic toughness. 795 MPa yield. Used in cryogenic applications (liquid hydrogen/oxygen), high-pressure gas bottles, and airframe forgings. One of the oldest aerospace titanium alloys.
Ti-5Al-2.5Sn is a near-alpha titanium alloy used primarily in aircraft engines and high-temperature aerospace applications, offering good creep resistance and tensile strength up to approximately 600°F. The annealed condition provides optimal ductility and dimensional stability after hot forming operations, with yield strength around 70-90 ksi and excellent damage tolerance characteristics.
Ti-6Al-2Sn-4Zr-2Mo is a near-alpha titanium alloy combining aluminum, tin, zirconium, and molybdenum additions for elevated temperature strength and creep resistance; used primarily in compressor and fastener applications in military and commercial jet engines operating up to ~600°C with good fatigue and stress-rupture performance.
Ti-6Al-2Sn-4Zr-2Mo is a near-alpha titanium alloy with aluminum, tin, zirconium, and molybdenum additions designed for elevated temperature applications requiring creep resistance and thermal stability. The annealed condition provides optimal combination of strength retention at intermediate temperatures (up to ~300°C), good fracture toughness, and formability in sheet form for aerospace engines, compressor blades, and casings.
Ti-6Al-2Sn-4Zr-2Mo is a near-alpha titanium alloy strengthened by aluminum and molybdenum additions, designed for elevated-temperature applications requiring moderate strength and creep resistance up to approximately 600°C in aerospace gas turbine engines and compressor casings. Duplex annealed condition provides optimal combination of strength and fracture toughness through controlled recrystallization and alpha-phase stabilization, with yield strengths typically 800–1000 MPa and good ductility (8–15% elongation) across bar, forging, and sheet product forms.
Ti-6242 is a near-alpha titanium alloy combining aluminum, tin, zirconium, and molybdenum additions to create a material with excellent creep resistance and thermal stability at intermediate temperatures. It is used primarily in gas turbine engines, compressor casings, and other high-temperature structural applications where sustained performance in the 300–500 °C range is critical. Engineers select Ti-6242 over conventional Ti-6Al-4V when creep resistance and extended service life at elevated temperatures are priorities, making it particularly valuable in military and commercial aerospace propulsion systems where weight savings and durability directly impact performance.
Ti-6Al-4V is the most widely used titanium alloy, offering an excellent strength-to-weight ratio, good corrosion resistance, and biocompatibility. Standard workhorse alloy for aerospace, biomedical, and high-performance applications.
Ti-6Al-4V annealed is a two-phase titanium alloy (6% aluminum, 4% vanadium) in a stress-relieved condition offering moderate strength with improved ductility and fracture toughness compared to higher-strength tempers. Widely used in aerospace engine casings, compressor blades, and airframe components where operating temperatures to 300°C and damage tolerance are critical; available in forgings, extrusions, castings, and wrought forms per MIL specifications.
Ti-6Al-4V produced via laser powder bed fusion (L-PBF) in the as-built condition is a titanium alloy renowned for its strength-to-weight ratio and biocompatibility, commonly used in aerospace, medical device, and high-performance industrial applications. The as-built microstructure—characterized by rapid solidification from the additive manufacturing process—exhibits high strength but lower ductility compared to wrought or heat-treated variants, making it suitable for load-bearing components where weight reduction and design complexity are critical. Engineers select this material when the ability to fabricate near-net-shape geometries, integrate functional features, and avoid traditional machining waste outweighs the need for maximum elongation or when post-process heat treatment is planned.
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.
Ultra-high-molecular-weight polyethylene (UHMWPE) is a linear polymer with an exceptionally long chain structure, specified under ASTM F648, offering an unusual combination of low density, high impact resistance, and excellent wear behavior. It is widely used in orthopedic implants (joint replacements, bearing surfaces), industrial wear components (conveyor systems, chute liners), marine applications, and medical devices where its low friction and self-lubricating properties reduce component degradation. Engineers select UHMWPE over standard polyethylene or competing polymers when prolonged wear life, biocompatibility, and minimal friction are critical, though its relatively low stiffness and moderate temperature ceiling require careful design consideration.
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).
Yttria-stabilized zirconia (Y-TZP) is a high-performance ceramic composed of zirconia matrix reinforced with yttrium oxide, engineered to prevent phase transformations that would otherwise cause brittleness. It is widely deployed in demanding applications requiring wear resistance, high temperature stability, and reliability in corrosive or biocompatible environments—notably in dental crowns and implants, precision bearing balls, cutting tool inserts, and oxygen sensor elements in exhaust systems. Y-TZP is chosen over alumina and other structural ceramics when engineers need superior toughness combined with hardness, particularly for components subject to cyclic loading or thermal shock; its transformation-toughening mechanism makes it significantly more damage-tolerant than conventional ceramics while maintaining chemical inertness and biocompatibility.
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.
Zinc oxide (ZnO) is a wide-bandgap semiconductor ceramic compound with a hexagonal wurtzite crystal structure, widely available as both bulk material and thin films. It is extensively used in optoelectronic devices (LEDs, UV detectors, laser diodes), transparent conducting coatings, varistors for surge protection, and as a pigment and filler in rubber, plastics, and cosmetics. ZnO is favored over competing wide-bandgap semiconductors for UV applications due to its large exciton binding energy, abundance, and cost-effectiveness; it also offers good thermal stability and non-toxicity, making it a preferred alternative to cadmium-based compounds in many consumer and industrial applications.
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.