24,657 materials
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 T7751 is a high-strength Al-Zn-Mg-Cu alloy in an overaged temper condition that provides excellent stress-corrosion cracking (SCC) resistance and fracture toughness at the expense of some peak strength compared to T7351. T7751 is specified for critical aerospace structure, particularly thick-section forgings and extrusions where sustained tensile stresses and corrosive environments necessitate resistance to SCC initiation and propagation.
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-T6151 is a high-strength aluminum-zinc alloy (with copper and magnesium) solution heat-treated and artificially aged with controlled stretching, delivering tensile strength of 505–530 MPa and improved fracture toughness and stress-corrosion cracking (SCC) resistance compared to T6, suited for critical aerospace and defense structural applications subject to sustained tensile loading. The T6151 condition is specified for components where the controlled residual compressive stress from stretching is beneficial for fatigue life and crack propagation resistance.
7075 aluminum T61511 is a high-strength Al-Zn-Mg-Cu alloy in a stress-relieved condition achieved through controlled stretching and artificial aging, designed for critical aerospace structures requiring maximum strength-to-weight ratio and fatigue resistance. This temper provides tensile strengths in the 70–80 ksi range with improved stress-corrosion cracking (SCC) resistance compared to T6, making it suitable for fuselage skin, wing components, and highly stressed fasteners in military and commercial aircraft.
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 T7451 7075 is a high-strength aluminum-zinc-magnesium-copper alloy used primarily in aerospace structures where maximum strength-to-weight ratio is critical. T7451 is an overaged temper (solution heat-treated, stress-relieved, and artificially aged) that trades some peak hardness for improved stress-corrosion cracking (SCC) resistance and dimensional stability, making it suitable for thick-section applications and components subject to sustained tensile stress.
7075-T7651 is a high-strength aluminum-zinc alloy with copper and magnesium additions, overaged to reduce susceptibility to stress-corrosion cracking while maintaining excellent strength-to-weight ratio. This temper is widely used in aircraft structures, landing gear, and fasteners where sustained tensile loads and corrosion resistance in salt-spray environments are critical.
7075 Aluminum T7751 is a zinc-primary aluminum alloy (with magnesium and copper) that is solution heat-treated, overaged, and stress-relieved to provide high strength (yield ~435 MPa) with improved stress-corrosion cracking (SCC) resistance compared to T6 temper, making it suitable for critical aerospace structural applications where both strength and environmental durability are required.
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 aluminum T6151 is a high-strength Al-Zn-Mg-Cu alloy in a solution heat-treated, stress-relieved, and overaged temper used primarily in aircraft structural applications demanding exceptional fatigue resistance and stress-corrosion cracking (SCC) resistance. The T6151 condition provides yield strengths of 435–505 MPa with improved toughness and corrosion performance compared to T6, making it suitable for critical fuselage and wing components operating under sustained or fluctuating loads.
7175-T61511 is a high-strength aluminum-zinc-magnesium-copper alloy in a thermally-treated and cold-worked condition, providing tensile yield strengths of approximately 70–75 ksi with improved fracture toughness and stress-corrosion cracking (SCC) resistance compared to overaged T7 tempers. This temper is used in critical aerospace structures including aircraft wing skins and fuselage components where a balance of high strength, damage tolerance, and corrosion resistance is required under sustained tensile stress.
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 T7451 is a high-strength Al-Zn-Mg-Cu alloy in an over-aged temper condition that provides reduced susceptibility to stress-corrosion cracking while maintaining tensile strength typically 70–75 ksi yield and 80–85 ksi ultimate in thin sheet. This temper is used in aerospace pressure vessels, wing skins, and fuselage components where sustained loads, environmental exposure, and resistance to stress-corrosion cracking in the short-transverse direction are critical design drivers.
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-T7651 is a high-strength aluminum alloy (Zn-Mg-Cu system) overaged to T7651 condition, providing improved stress-corrosion cracking resistance and fatigue performance compared to T73, with yield strength around 435-470 MPa and sustained service capability to approximately 150°C in aerospace structural applications.
7175 Aluminum T7751 is a high-strength Al-Zn-Mg-Cu alloy in a stabilized temper (solution heat-treated, artificially aged, and stress-relieved) designed to reduce stress-corrosion-cracking susceptibility while maintaining tensile strength of ~480 MPa and excellent damage tolerance for critical aerospace structural applications.
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 is a zinc-aluminum-magnesium-copper alloy used primarily in high-strength aerospace applications requiring superior fracture toughness and stress-corrosion-cracking (SCC) resistance compared to 7075. The T6151 temper (solution heat-treated, artificially aged, and stress-relieved) provides yield strengths in the 435–480 MPa range with improved toughness and dimensional stability, particularly suited for critical fuselage and structural components where both strength and damage tolerance are essential.
7249 Aluminum T61511 is a high-strength Al-Zn-Mg-Cu alloy in a precipitation-hardened condition (T61511 involves solution treatment, controlled stretching, and artificial aging) designed for aerospace structural applications requiring exceptional fracture toughness and damage tolerance. This temper provides superior resistance to stress-corrosion cracking and fatigue crack propagation compared to peak-hardness conditions, making it suitable for critical airframe components and pressure vessels operating at service temperatures up to approximately 120°C.
7249 Aluminum T7451 is a high-strength Al-Zn-Mg-Cu alloy in a overaged condition (T7451) that provides improved stress-corrosion cracking (SCC) resistance compared to T73, while maintaining tensile strength suitable for aerospace structural applications. The T7451 temper delivers controlled yield strength with enhanced resistance to sustained-load cracking in marine and high-humidity environments, making it suitable for critical aircraft components where both strength and corrosion durability are required.
7249 Aluminum T7651 is an Al-Zn-Mg-Cu alloy in a stabilized temper condition (solution heat-treated, artificially aged, then stress-relieved), providing high strength (yield ~450 MPa) with improved stress-corrosion cracking resistance suitable for critical aerospace structural applications where fatigue and sustained tensile loading are concerns. The T7651 condition balances strength retention with dimensional stability and reduced susceptibility to environmental stress cracking compared to T76 temper.
7249 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.
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 T6151 is a high-strength Al-Zn-Mg-Cu aerospace alloy in a solution heat-treated and artificially aged condition with controlled cold-working, delivering tensile strengths of 435–495 MPa with improved fracture toughness and stress-corrosion cracking resistance compared to standard T6 temper. Primary applications include critical aircraft structural components, fuselage skins, and fastener applications requiring damage-tolerant performance in sustained-load environments.
7475 Aluminum T61511 is a high-strength Al-Zn-Mg-Cu alloy in a T61511 temper (solution heat-treated, stress-relieved by stretching, and artificially aged) designed for critical aerospace structural applications requiring maximum strength-to-weight ratio and damage tolerance. This temper provides tensile strengths in the 70–80 ksi range with improved stress-corrosion cracking resistance and fracture toughness compared to T6 tempers, making it suitable for highly loaded fuselage skins, wing components, and fastener applications in military and commercial aircraft.
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 T7451 is a high-strength Al-Zn-Mg-Cu alloy subjected to solution heat treatment, controlled stretching, and overaging, delivering enhanced stress-corrosion cracking (SCC) resistance and fracture toughness with minimal loss in yield strength compared to T651. Primary applications include critical aerospace structures, pressure vessels, and military aircraft components where SCC susceptibility must be minimized without sacrificing damage tolerance.
7475 Aluminum T7751 is a zinc-aluminum-magnesium-copper alloy in the overaged T7751 temper, providing tensile strengths of 435–470 MPa with improved stress-corrosion cracking (SCC) resistance through controlled precipitation. This condition is used in aircraft fuselage skins and fastener applications where resistance to sustained tensile stress in saltwater environments is critical, sacrificing some peak strength for enhanced fracture toughness and corrosion durability.
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.
7475-T761 is a high-strength aluminum-zinc-magnesium-copper alloy reinforced with aramid fibers, solution heat-treated, stress-relieved by stretching, and artificially aged to provide enhanced stiffness and damage tolerance for aerospace structural applications. The T761 temper and aramid reinforcement combination delivers improved fatigue resistance, reduced notch sensitivity, and better impact performance compared to unreinforced 7475-T761 while maintaining the alloy's high strength-to-weight ratio and fracture toughness suitable for critical aircraft components.
7Ni-12Co Maraging Steel is an iron-nickel-cobalt precipitation-hardened steel designed for ultra-high-strength applications requiring excellent toughness and dimensional stability. This grade combines high cobalt content (12.3%) with nickel and molybdenum additions to enable age-hardening without sacrificing ductility—a critical advantage over conventional high-strength steels that often become brittle. It is used in demanding aerospace, tooling, and precision manufacturing sectors where weight savings and reliability under shock or fatigue loading justify the premium material cost, and it is valued for applications requiring both strength and damage tolerance that cannot tolerate delayed cracking or stress-corrosion sensitivity.
An ultra-high-strength low-alloy steel combining significant chromium (8.1%), molybdenum (1.9%), and nickel (10.1%) content to achieve excellent hardenability, fatigue resistance, and corrosion resistance in a martensitic matrix structure. This composition is typical of premium aerospace and defense alloy steels, particularly those specified for highly stressed components requiring both strength and damage tolerance in demanding environments.
8Ni-12Co Maraging steel is a precipitation-hardened iron-nickel-cobalt alloy engineered for extremely high strength with retained toughness, typically used in high-demand aerospace and defense applications where weight savings and damage tolerance are critical. The alloy achieves its strength through aging-induced intermetallic precipitation rather than carbon content, making it amenable to welding and machining before heat treatment—a key advantage over conventional high-strength steels. This material is selected when applications require the combination of ultra-high strength and fracture toughness that conventional martensitic or tool steels cannot reliably deliver, such as landing gear, missile casings, and spacecraft structures.
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.
Actinium (Ac) is a silvery radioactive metal belonging to the actinide series of the periodic table. It is primarily encountered in nuclear research, medical isotope production, and specialized scientific applications rather than mainstream engineering. Engineers considering actinium should recognize it as a material constrained by extreme rarity, radioactivity, and regulatory oversight—its use is limited to institutional laboratories and nuclear facilities where its nuclear properties (not mechanical properties) drive selection.
Ac2AgIr is a ternary intermetallic compound combining actinium, silver, and iridium. This is a research-phase material studied primarily for its fundamental metallurgical properties rather than established commercial applications. The material family represents exploration into high-density intermetallic systems that could potentially offer extreme strength or specialized electronic/thermal properties, though practical engineering use cases remain limited pending further development and characterization.
Ac2AgPb is a ternary intermetallic compound composed of actinium, silver, and lead. This material exists primarily in research contexts as part of actinium-based alloy systems; its practical industrial use is extremely limited due to actinium's scarcity, high radioactivity, and cost. The compound is studied in fundamental materials science to understand intermetallic phase formation and crystal structures in rare-element systems, rather than for direct engineering applications.
Ac2Co is an intermetallic compound composed of actinium and cobalt, representing a research-phase material in the actinium-transition metal family. This compound exists primarily in materials science literature and high-performance metallurgy studies rather than established commercial production, making it relevant to advanced materials development and fundamental property investigation of actinium-based systems. Interest in actinium intermetallics stems from potential applications in specialized high-temperature or radiation-resistant environments where the unique nuclear and electronic properties of actinium could provide advantages over conventional alloys.
Ac2CuGe is an intermetallic compound composed of actinium, copper, and germanium, representing a research-phase material from the rare-earth and actinide metallurgy family. This compound is primarily of scientific and academic interest rather than established industrial use, being studied for its crystallographic structure and potential electronic or magnetic properties within advanced materials research. Engineers would encounter this material in specialized nuclear materials science, solid-state physics investigations, or exploratory alloy development programs rather than in conventional engineering applications.
Ac2CuIr is an intermetallic compound composed of actinium, copper, and iridium. This is a research-phase material studied primarily for its potential in high-performance applications requiring extreme corrosion resistance and thermal stability, though it remains largely experimental with limited industrial deployment.
Ac₂CuRu is a ternary intermetallic compound combining actinium, copper, and ruthenium. This is a research-phase material studied primarily in fundamental materials science rather than established engineering practice; intermetallics in this family are explored for their potential high-temperature stability, electronic properties, and wear resistance, though practical applications remain limited pending further development and characterization.
Ac2CuSi is an intermetallic compound in the actinium-copper-silicon ternary system, representing a research-phase material with limited industrial deployment. This compound belongs to the broader family of actinium-based intermetallics, which are primarily of scientific interest due to actinium's radioactive properties and scarcity; applications would be restricted to specialized nuclear, fundamental physics, or advanced metallurgical research contexts rather than conventional engineering.
Ac2CuSn is an intermetallic compound combining actinium, copper, and tin in a fixed stoichiometric ratio. This material belongs to the rare intermetallic family and is primarily of research interest rather than established industrial production, as actinium's extreme scarcity and radioactivity limit practical applications. The compound is studied in fundamental materials science for understanding phase behavior in actinide-based systems and potential applications in nuclear materials research, though its extreme cost and handling requirements make it unsuitable for conventional engineering applications.
Ac2GaCu is an intermetallic compound combining actinium, gallium, and copper in a ternary phase system. This is a research-stage material primarily of interest in fundamental materials science and metallurgical studies rather than established industrial production. The material represents exploration of actinium-based intermetallics, which remain largely experimental due to actinium's scarcity and radioactivity, making practical engineering applications extremely limited and confined to specialized nuclear or advanced research contexts.
Ac2IrAu is a ternary intermetallic compound combining actinium, iridium, and gold in a defined stoichiometric ratio. This is a research-phase material primarily of interest in fundamental materials science and solid-state chemistry rather than established commercial engineering applications. The compound belongs to the family of noble-metal intermetallics and actinide-containing phases, which are studied for understanding phase stability, electronic structure, and potential specialized properties in extreme environments or high-performance contexts.
Ac₂Ni is an intermetallic compound in the actinide-nickel system, representing a specialized metallic material combining actinide and transition metal elements. This compound is primarily of research and development interest rather than established in broad industrial production, with potential applications in nuclear materials science, advanced metallurgy, and specialized alloy development where actinide-containing phases offer unique properties. Engineers considering this material would typically be engaged in nuclear fuel systems, advanced reactor materials, or fundamental materials research where the phase stability and mechanical characteristics of actinide intermetallics are critical to performance.
Ac2NiGe is an intermetallic compound combining actinium, nickel, and germanium elements, representing a specialized metallic material from the intermetallic family. This material is primarily of research interest rather than established industrial production, studied for its potential electronic, thermal, or magnetic properties that could arise from its three-element composition. Engineers would consider this material in advanced applications requiring novel combinations of metallic bonding and electronic behavior, though practical adoption remains limited to specialized research environments and specialized high-performance applications.
Ac2NiIr is an intermetallic compound combining actinium, nickel, and iridium in a stoichiometric ratio. This is a research-phase material studied primarily for its potential in high-temperature and nuclear applications, where the combination of actinium's nuclear properties with the refractory characteristics of nickel and iridium offers theoretical advantages. The material remains largely experimental; its development is driven by interest in advanced metallic systems for extreme environments rather than established industrial production.
Ac2ZnAu is an intermetallic compound combining actinium, zinc, and gold—a rare ternary metal system primarily explored in materials research rather than established industrial production. This compound belongs to the family of actinium-based intermetallics, which are investigated for fundamental studies of actinium chemistry and potential applications in nuclear materials, specialized alloys, and high-density systems where actinium's unique nuclear and chemical properties may offer advantages. The combination with gold and zinc suggests potential interest in high-density applications or niche electronics/catalysis research, though widespread commercial use remains limited due to actinium's scarcity, radioactivity (if using radioisotopes), and cost.
Ac3Ag is a silver-containing alloy with a composition that suggests potential applications in specialized joining or electrical applications where silver's high conductivity and corrosion resistance are valued. This material appears to be a research or specialized industrial alloy rather than a broadly commoditized material; its specific composition and processing characteristics would determine whether it offers advantages in electrical contact systems, brazing applications, or thermal management where silver alloying is critical.