24,657 materials
18Cr-4Ni is a lean duplex stainless steel combining ferritic and austenitic phases to deliver a balanced mix of strength, corrosion resistance, and cost efficiency compared to conventional austenitic stainless steels. It is widely used in chemical processing, desalination plants, pulp and paper production, and offshore equipment where moderate corrosion resistance and good mechanical properties are required without the expense of higher-alloyed duplex grades. Engineers select this grade when weight savings, fabricability, and resistance to chloride stress-corrosion cracking are priorities, and where the lower nickel content offers cost advantages over 304/316L austenitic stainless steels in non-severe corrosive environments.
This is a lean duplex stainless steel with 18% chromium and ~4% nickel, alloyed with molybdenum for enhanced corrosion resistance and modest cobalt addition. It occupies a middle ground between austenitic 300-series and fully ferritic duplex grades, offering a dual-phase microstructure that balances strength with corrosion performance—making it suitable for moderately aggressive environments where cost must be controlled relative to super-duplex alternatives. The material is employed in offshore oil & gas piping, desalination plants, chemical processing equipment, and seawater cooling systems where chloride-induced pitting and stress corrosion cracking are concerns but where the expense of 6Mo super-duplex is not justified.
18Cr-4Ni duplex stainless steel is a two-phase ferritic-austenitic alloy that combines the corrosion resistance of austenitic stainless steels with the strength and stress-corrosion cracking resistance of ferritic grades, positioned as a cost-effective alternative to higher-nickel duplex variants. This material is widely employed in chemical processing, desalination plants, offshore platforms, and pulp-and-paper manufacturing where resistance to chloride corrosion and pitting is critical, particularly in moderately aggressive environments where standard austenitic grades (like 304/316) would require thicker sections or more frequent maintenance. Engineers select this composition for applications demanding both corrosion performance and mechanical strength without the premium cost or nickel supply constraints of super-duplex grades, making it especially attractive for large structural components and pressure equipment in marine and industrial settings.
18Cr-4Ni duplex stainless steel is a two-phase ferritic-austenitic stainless steel combining moderate chromium content with balanced nickel levels to achieve good corrosion resistance and workability. This variant is used in moderate-corrosion environments where both strength and ductility matter, such as structural fasteners, process equipment, and general industrial piping; it offers better toughness than ferritic grades while remaining more cost-effective than higher-alloyed duplex or super-duplex stainless steels, making it a practical choice when 300-series austenitic grades would be over-specified.
18Cr-6Ni is a precipitation-hardened austenitic stainless steel combining the corrosion resistance of the chromium-nickel austenitic family with enhanced strength through aluminum and carbon-driven strengthening mechanisms. This material targets high-strength applications where traditional 300-series austenitic stainless steels (like 304 or 316) fall short mechanically, finding use in aerospace fasteners, high-performance springs, and demanding structural components in chemical and oil & gas environments. Its aluminum content positions it between conventional austenitic and martensitic hardened stainless grades, offering a balance of corrosion resistance and yield strength that makes it valuable for weight-critical or high-load bearing applications where standard austenitic grades would require thicker sections.
18Ni-12Co-2.1Mo-2.3Ti maraging steel is a precipitation-hardened iron-nickel alloy engineered to achieve ultrahigh strength through a low-temperature aging heat treatment rather than carbon-based hardening. This material is used in aerospace, defense, and precision tooling applications where exceptional strength-to-weight ratio and dimensional stability are critical, particularly in landing gear, missile components, mold inserts, and high-performance fasteners. Engineers select maraging steels over conventional high-strength steels when weight reduction is essential, when toughness must be maintained at extreme strength levels, or when superior corrosion resistance and weldability are needed alongside high performance.
18Ni-13Co-2.1Mo-1.9Ti is a precipitation-hardening (maraging) steel engineered for exceptional strength-to-weight ratio and toughness without requiring quenching, achieved through controlled aging of a soft, machinable austenitic matrix. This alloy is critical in aerospace and defense applications where extreme strength combined with damage tolerance and dimensional stability are non-negotiable, particularly in landing gear, missile bodies, and structural forgings where traditional quenched-and-tempered steels would be brittle or difficult to machine to final dimensions.
18Ni-13Co-2.1Mo-2.2Ti is a high-strength maraging steel—an iron-nickel precipitation-hardened alloy that achieves exceptional strength through aging heat treatment rather than carbon hardening, resulting in very low carbon content (~0.05%) and excellent toughness-to-strength ratio. This grade is employed in aerospace and defense applications requiring damage-tolerant structures, including missile cases, aircraft landing gear, and pressure vessels, where the combination of ultra-high strength, low distortion during heat treatment, and superior fracture toughness outweighs the cost premium versus conventional alloy steels. Engineers select maraging steels when weight savings and reliability under extreme loads justify the investment, and when welding or precision machining are critical—properties where carbon-hardened steels exhibit brittleness or dimensional instability.
An 18% nickel maraging steel strengthened by precipitation hardening of intermetallic phases (cobalt, molybdenum, and titanium), achieving ultrahigh strength with relatively good toughness compared to conventional high-strength steels. This material is used in aerospace structures, rocket casings, and precision tooling where extreme strength-to-weight ratio and dimensional stability are critical; it is valued over alternatives because it can be solution-treated in thick sections and then aged to full strength without significant distortion, making it ideal for large forged components that demand both strength and machinability.
This is a precipitation-hardening maraging steel, a high-strength iron-nickel alloy strengthened by intermetallic phases (primarily Ni₃Mo and related compounds) rather than by carbon content, making it extremely tough and weldable despite its high strength. Used predominantly in aerospace and defense applications—particularly landing gear, missile casings, and structural components in spacecraft—where the combination of exceptional strength, fracture toughness, and low distortion during heat treatment is critical. Engineers select maraging steels when conventional high-strength steels would sacrifice ductility or introduce welding difficulties; this alloy's low carbon content virtually eliminates brittleness and allows field repairs without embrittlement concerns.
18Ni-7Co-2.9Mo is a precipitation-hardened maraging steel engineered for ultra-high strength with retained toughness and ductility. This nickel-cobalt-molybdenum system gains its strength through age-hardening rather than carbon content, making it exceptionally clean and damage-tolerant compared to conventional high-strength steels. It is widely used in aerospace structures, tooling, and precision engineering where the combination of high strength, excellent fatigue resistance, and superior fracture toughness is critical, and where the material's ability to be welded and machined before hardening offers significant manufacturing advantages.
18Ni-7Co-3.1Mo-0.8Ti is a precipitation-hardening maraging steel engineered for ultra-high strength with controlled ductility, achieved through aging heat treatment rather than carbon content. This composition is used in aerospace and defense applications including rocket motor cases, landing gear, and high-performance tooling where weight savings and damage tolerance are critical; it is also employed in specialized industrial applications demanding both strength and toughness without brittleness. The material's combination of low carbon content, strategic alloying with cobalt and molybdenum, and age-hardening response makes it a preferred choice over conventional high-strength steels when high strength-to-weight ratio and excellent fracture toughness must coexist.
18Ni-7Co-3.1Mo-0.8Ti maraging steel is a precipitation-hardened iron-nickel alloy designed to achieve ultra-high strength through controlled aging heat treatment, with cobalt and molybdenum additions enhancing strength development and titanium contributing to the hardening mechanism. This variant is employed in aerospace structures, defense systems, and tooling applications where the combination of very high strength with reasonable toughness and machinability is critical—particularly where conventional high-strength steels would require extensive stress relief or prove too brittle. Engineers select maraging steel when weight reduction and damage tolerance are equally important, avoiding the brittleness of tool steels or the processing difficulty of superalloys in moderately demanding applications.
18Ni-7Co-3.1Mo-1.1Ti is a precipitation-hardening maraging steel engineered for extremely high strength with retained toughness through controlled aging of a low-carbon, nickel-rich matrix. This alloy is used in aerospace, defense, and high-performance tooling applications where weight savings and reliability under extreme stress are critical, competing with titanium alloys and other superalloys where cost and machinability are also constraints. Its combination of very high strength, good ductility, excellent weldability, and superior toughness compared to conventional hardened steels makes it preferred for components requiring damage tolerance and fracture resistance alongside extreme load capacity.
18Ni-8Co-2.9Mo-0.8Ti is a precipitation-hardening maraging steel engineered for extreme strength-to-weight performance without relying on carbon hardening. The cobalt, molybdenum, and titanium additions enable age-hardening through intermetallic precipitation, yielding a martensitic steel that maintains toughness and ductility even at ultra-high strength levels. This material is chosen for critical aerospace and defense components, precision tooling, and sporting equipment where lightweight design, damage tolerance, and repeatability cannot be compromised—applications where conventional high-strength steels would be too brittle or require prohibitive thickness.
18Ni-8Co-2.9Mo-0.9Ti is a precipitation-hardening maraging steel engineered for extreme strength with retained toughness, developed through aging heat treatment rather than carbon hardening. This alloy is used in critical aerospace components, tooling for high-pressure molding, and precision machinery where weight savings and damage tolerance are essential—particularly applications requiring both exceptional strength and ability to absorb impact without brittle failure. The cobalt and molybdenum additions enable superior hardening response compared to conventional steels, making maraging steel the material of choice when conventional high-strength alloys prove inadequate or too brittle.
18Ni-8Co-3.6Mo-0.5Ti is a precipitation-hardening maraging steel engineered for ultra-high strength with excellent toughness and dimensional stability. This alloy is widely deployed in aerospace structures (landing gear, fasteners, critical forgings), tool steels for high-performance dies, and defense applications where weight savings and damage tolerance are critical. Engineers select maraging steels over conventional high-strength alloys when damage-tolerant fracture mechanics, low distortion during heat treatment, and repeatable performance in critical load-bearing roles are essential—making it the reference material for applications where strength-to-weight ratios and reliability cannot be compromised.
18Ni-9Co-2.8Mo-0.8Ti is a precipitation-hardening maraging steel engineered for ultra-high strength with exceptional toughness and ductility. The nickel-cobalt-molybdenum-titanium system produces a martensitic matrix strengthened by intermetallic precipitates formed during low-temperature aging, eliminating the brittleness typically associated with ultra-high-strength steels. This alloy is employed in aerospace structures, pressure vessels, tooling, and sporting equipment where the combination of extreme strength, damage tolerance, and fatigue resistance justifies the material cost; it is preferred over conventional high-strength steels and some titanium alloys when weight savings and fracture toughness must both be optimized.
19Cr-4Ni duplex stainless steel is a lean duplex stainless alloy combining chromium and molybdenum for corrosion resistance with a dual-phase microstructure (austenite + ferrite) that enhances strength and toughness. It is widely used in oil and gas pipelines, desalination plants, chemical processing equipment, and marine structures where resistance to pitting and stress-corrosion cracking is critical and cost must be controlled relative to super-duplex grades. Engineers choose this alloy when corrosion resistance and strength must be balanced against material cost and machinability, offering a middle ground between austenitic stainless steels and more expensive duplex variants.
19Ni-14Co-1.8Ti maraging steel is an ultra-high-strength iron-nickel alloy hardened by precipitation of intermetallic phases rather than carbon, resulting in a martensitic matrix with exceptional strength and toughness at relatively low carbon content. It is used in demanding aerospace, defense, and precision engineering applications where extreme strength-to-weight ratios, dimensional stability, and fracture resistance are critical, such as rocket casings, landing gear, and high-performance tooling; this alloy family is preferred over conventional tool steels and other ultra-high-strength materials when designers need to combine very high yield strength with adequate ductility and minimal distortion during heat treatment.
19Ni-15Co-1.8Mo-1.9Ti is a precipitation-hardening maraging steel engineered for extreme strength with minimal ductility loss, achieving hardness through intermetallic phase formation rather than carbon content. Its nickel-cobalt-molybdenum-titanium system is deployed in aerospace structural components, defense systems, and precision tooling where weight savings and damage tolerance are critical; engineers select maraging steels over conventional high-strength steels when fatigue resistance, toughness, and dimensional stability during heat treatment are equally important to raw strength.
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.
2024-T3 aluminum alloy with aramid fiber reinforcement is a copper-alloyed aluminum composite combining high strength-to-weight ratio with enhanced damage tolerance and impact resistance for primary aircraft structure applications. The T3 temper (solution heat-treated and naturally aged) provides improved fracture toughness and reduced residual stress compared to artificially aged conditions, making it suitable for critical load-bearing components in aerospace environments.
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.
5.2Cr-1.7Mo-11.0Ni is a precipitation-hardening low-alloy steel designed to achieve very high strength through age-hardening heat treatment, combining chromium and molybdenum for hardenability with substantial nickel content for toughness and corrosion resistance. This material is primarily used in aerospace and defense applications where both extreme strength and damage tolerance are critical—particularly in landing gear, fasteners, and structural components that must survive high-cycle fatigue and occasional impact. The high nickel and chromium content also provides good corrosion resistance compared to conventional steels, making it suitable for environments with salt spray or chemical exposure, while the controlled molybdenum level ensures through-hardening without excessive brittleness.
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.