103,121 materials
This is a precipitation-hardening nickel-chromium-molybdenum low alloy steel, strengthened through martensitic transformation and age-hardening mechanisms. The high nickel content (11.4%) combined with chromium and molybdenum provides exceptional strength-to-weight ratio, corrosion resistance, and toughness at both ambient and cryogenic temperatures. Commonly used in aerospace landing gear, high-strength fasteners, and defense applications where demanding fatigue, impact, and environmental resistance are required; it competes favorably with maraging steels and titanium alloys in cost-sensitive applications requiring both ultra-high strength and damage tolerance.
5.6Cr-1.9Mo-9.8Ni is a low-alloy steel engineered for high-strength applications requiring good toughness and fatigue resistance, achieved through careful balance of chromium (corrosion and wear resistance), molybdenum (strength and hardness), and nickel (ductility and impact toughness). Primarily used in aerospace landing gear, high-performance automotive components, and heavy-duty machinery requiring both strength and damage tolerance. This composition is notable for maintaining reliable performance in cyclically loaded or shock-prone environments where brittle failure must be avoided, making it preferable to higher-carbon martensitic steels in applications where impact resistance and fatigue life are critical.
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.
6Ni-12Co Maraging Steel is a precipitation-hardened iron-nickel alloy strengthened by cobalt, molybdenum, and vanadium intermetallic phases, representing a high-strength variant within the maraging steel family. This alloy is used in aerospace and defense applications where exceptional strength-to-weight ratios and damage tolerance are critical, including landing gear, missile casings, and structural components in high-performance aircraft. Engineers select maraging steels over conventional high-strength steels when lightweight designs with superior fracture toughness and dimensional stability are required, and this cobalt-rich composition pushes the upper strength envelope while maintaining acceptable ductility for structural reliability.
7049/7149 Aluminum T6151 is a high-strength Al-Zn-Mg-Cu aerospace alloy in a overaged temper condition that provides improved stress-corrosion cracking (SCC) resistance and fracture toughness compared to T6, with typical yield strengths of 65–75 ksi and applications in highly stressed structural components, fuselage skins, and wing elements where damage tolerance is critical.
7049/7149 Aluminum T61511 is a high-strength Al-Zn-Mg-Cu alloy in a premium temper condition (solution heat-treated, artificially aged, and stress-relieved by stretching) that delivers exceptional fatigue resistance and fracture toughness for primary aircraft structures. This temper is used extensively in fighter aircraft and military transport applications where sustained cyclic loading, damage tolerance, and corrosion resistance are critical performance requirements.
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 T7451 is a high-strength aluminum-zinc-magnesium alloy in overaged condition, providing reduced susceptibility to stress-corrosion cracking while maintaining tensile strength in the 470–510 MPa range, primarily used in aerospace airframe structures and pressure vessels. The T7451 temper achieves stress relief through controlled overaging, making it suitable for critical applications requiring both high strength and enhanced resistance to environmental stress-corrosion cracking in chloride-containing environments.
7049/7149 Aluminum T7651 is a high-strength Al-Zn-Mg-Cu alloy in overaged temper condition, providing reduced susceptibility to stress-corrosion cracking while maintaining tensile strength in the 470–510 MPa range; primary use is in aircraft structural components and landing gear where combined strength, damage tolerance, and SCC resistance are critical.
7049/7149 Aluminum T7751 is a high-strength Al-Zn-Mg-Cu alloy in an overaged temper condition that provides enhanced stress-corrosion cracking (SCC) resistance and fracture toughness compared to T73 variants, with typical yield strengths of 435–450 MPa and primary use in critical aerospace structural applications requiring damage tolerance and saltwater/corrosive environment resistance.
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 Aluminum T6151 is a high-strength Al-Zn-Mg-Cu alloy in the overaged temper condition, providing ultimate tensile strength of ~495–570 MPa with improved stress-corrosion cracking (SCC) resistance and fracture toughness compared to peak-hardened T6 condition. Specified in military applications including aircraft structures and fasteners where damage tolerance and resistance to sustained-load SCC are critical requirements.
7050 Aluminum T61511 is a high-strength Al-Zn-Mg-Cu alloy in a artificially aged temper (T61511 indicates solution heat-treated, stress-relieved by stretching, then aged) designed for aerospace structures requiring maximum strength-to-weight ratio with improved stress-corrosion cracking (SCC) resistance compared to T7351. This temper delivers tensile strengths in the 70–74 ksi range with enhanced fracture toughness and reduced susceptibility to SCC in thick sections, making it suitable for critical aircraft fuselage and wing components.
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 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.