355 materials
2014-T6 is a copper-alloyed aluminum alloy in the 2xxx series, solution heat-treated and artificially aged to peak strength, offering high yield strength (typical 60 ksi) and ultimate tensile strength (typical 70 ksi) with moderate ductility for aerospace structural applications requiring fatigue resistance. Primary applications include aircraft fuselage and wing components, forgings, and structural details where strength-to-weight ratio and bearing load capability are critical, with continuous service capability to approximately 250°F.
2014 aluminum is a copper-alloyed, high-strength aluminum alloy used primarily in aerospace airframe structures and components requiring elevated strength-to-weight ratios. The T62 temper (solution heat-treated and artificially aged) delivers high yield and tensile strength with moderate ductility, suitable for aircraft skin, fuselage, and structural applications operating at room temperature.
2014 aluminum is a copper-alloyed high-strength aluminum used primarily in aircraft structural forgings and landing gear components, offering tensile strengths in the 60–70 ksi range with good fatigue resistance. The T652 temper (solution heat-treated, stress-relieved, and artificially aged) provides dimensional stability and controlled strength suitable for precision forged parts requiring consistent mechanical properties and minimal distortion.
2017 Aluminum (T4) is a copper-alloyed aluminum with high strength and good machinability, historically used in aircraft structures and fasteners where moderate strength and damage tolerance are required. The T4 temper (solution heat-treated and naturally aged) provides a balance of strength and ductility suitable for riveted airframe applications, with tensile strength approximately 280–310 MPa and superior fatigue resistance compared to harder tempers.
2017 is a copper-alloyed aluminum alloy with high strength and excellent machinability, primarily used in aerospace fasteners and structural components requiring good fatigue resistance. The T4 temper (solution heat-treated and naturally aged) provides tensile strengths around 62 ksi yield and 90+ ksi ultimate with moderate ductility, suitable for applications up to approximately 250°F.
2024 aluminum is a high-strength Al-Cu-Mg alloy widely used in aircraft structures and aerospace applications, offering excellent fatigue resistance and damage tolerance despite moderate corrosion susceptibility. Available tempers range from T3 (solution-treated and cold-worked) through T851 (solution-treated, stress-relieved, and artificially aged), providing tensile strengths from ~290 MPa to ~505 MPa depending on condition, with Young's modulus approximately 73 GPa across all tempers.
2024 aluminum is a high-strength aluminum-copper alloy used extensively in aerospace structures for applications requiring excellent fatigue resistance and damage tolerance at temperatures up to approximately 150°C. T3 temper (solution heat-treated and cold-worked) provides optimal strength-to-weight ratio and fracture toughness, making it the preferred condition for drawn tubing in aircraft fuselage skins, fastener holes, and other primary load-bearing components.
2024 aluminum is a high-strength Cu-Mg-Mn alloy used primarily in aircraft structural applications where superior fatigue resistance and damage tolerance are required. The T42 temper (solution heat-treated and naturally aged) provides yield strength around 35 ksi with excellent bearing and shear strength characteristics, suitable for fastener holes and highly stressed airframe components in drawn tubing form.
2024-T81 aluminum is a high-strength aluminum-copper alloy in drawn tube form, developed for aerospace applications requiring elevated strength with controlled properties. The T81 temper—achieved through solution heat treatment, controlled stretching, and natural aging—delivers ultimate tensile strength around 70 ksi with good dimensional stability suitable for structural tubing in aircraft fuselage and hydraulic systems per WW-T-700/3 specification.
2025 aluminum alloy (Cu-Mg primary alloying elements) is a heat-treatable aerospace alloy used in aircraft structural components requiring high strength-to-weight ratio; T6 temper (solution heat-treated and artificially aged) provides yield strengths in the 50-57 ksi range with moderate elongation, suitable for die-forged critical aircraft parts operating at room temperature with good fatigue resistance.
2090 aluminum is a copper-lithium wrought alloy designed for aerospace applications requiring high strength-to-weight ratio and cryogenic performance. T83 temper (solution heat-treated, stress-relieved, and artificially aged) delivers high yield and ultimate tensile strength with controlled elongation, suitable for aircraft structural components and cryogenic tankage in sheet form per AMS 4251.
2124 aluminum alloy is a Cu-containing aerospace aluminum with high strength-to-weight ratio, used primarily in aircraft fuselage and structural applications requiring elevated temperature performance. T851 temper (solution heat-treated, stress-relieved, and overaged) provides controlled strength with improved stress-corrosion cracking resistance suitable for critical loaded components.
2219 aluminum alloy is a copper-containing wrought aluminum alloy designed for cryogenic and elevated-temperature aerospace applications, offering high strength retention at temperatures down to -452°F and excellent fracture toughness in thick sections. Primary uses include Space Shuttle external tank structures, rocket bodies, and other aerospace applications requiring superior strength-to-weight ratios combined with resistance to stress-corrosion cracking in the T8x temper conditions.
2219 aluminum alloy (Cu-Mn primary alloying elements) is a high-strength aerospace material used in cryogenic tankage and structural applications requiring superior strength at low temperatures. The T852 temper (solution heat-treated, stress-relieved, and artificially aged) provides excellent damage tolerance and fracture toughness combined with high yield and tensile strength, making it suitable for critical pressure vessels and cryogenic service in hand-forged form per AMS 4144.
250 Maraging Steel is a nickel-iron-cobalt alloy designed for ultra-high-strength aerospace and defense applications, offering yield strengths exceeding 200 ksi when age-hardened. The material provides exceptional toughness-to-strength ratios, low thermal expansion, and excellent dimensional stability, making it suitable for critical structural components, tooling, and pressure vessels in extreme-performance environments.
250 Maraging Steel is an iron-nickel-cobalt alloy (18% Ni, 8-9% Co, 3-5% Mo) aged at 900°F to achieve ultrahigh strength (typically 250 ksi yield) with excellent toughness and fatigue resistance; widely used in aerospace applications including landing gear, fasteners, and structural components requiring high strength-to-weight ratio and damage tolerance.
2519 aluminum alloy is a copper-lithium-magnesium aluminum alloy designed for cryogenic and elevated-temperature aerospace applications, offering high strength-to-weight ratio with excellent fracture toughness at temperatures from -320°F to 350°F. The T87 temper (solution heat-treated, overaged, and artificially aged) provides controlled yield and ultimate strength with improved stress-corrosion cracking resistance compared to T8 tempers, making it suitable for critical aircraft fuselage and structural applications per MIL-DTL-46192 specifications.
2618 aluminum is a copper-aluminum alloy with magnesium and iron additions designed for elevated-temperature aerospace applications, offering strength retention up to 300°C. The T61 temper (solution heat-treated, artificially aged, and stress-relieved) provides optimal combination of tensile strength and thermal stability in die-forged components for aircraft engines and gas turbine applications.
280 Maraging Steel is a nickel-cobalt-molybdenum maraging steel (18% Ni, 8% Co, 5% Mo) used in aerospace and defense applications requiring very high strength with good toughness and damage tolerance. The maraged 900°F condition provides yield strengths around 280 ksi (1930 MPa) through precipitation hardening, maintaining relatively good fracture toughness and fatigue resistance compared to conventional ultrahigh-strength steels at equivalent strength levels.
280 Maraging Steel aged at 900°F is a nickel-cobalt-molybdenum maraging steel offering ultra-high strength (typically 280 ksi yield) with exceptional toughness and fracture resistance, primarily used in aerospace structures, die-casting dies, and precision tooling. This aging condition provides optimal strength-to-toughness balance through controlled precipitation hardening, with good dimensional stability and machinability.
304L stainless steel is a low-carbon austenitic stainless steel alloy (Fe-Cr-Ni base) in wrought form, designed to minimize chromium carbide precipitation and intergranular corrosion during welding and high-temperature service. It is widely used in chemical processing, food and beverage production, pharmaceutical equipment, and marine environments where corrosion resistance combined with weldability is critical; engineers select 304L over standard 304 grade specifically when welded assemblies must maintain corrosion immunity in aggressive media without post-weld heat treatment.
304 stainless steel is an austenitic iron-based alloy containing 18–20% chromium and 8–10.5% nickel, representing the most widely used stainless steel grade in industrial applications. It offers excellent corrosion resistance across a broad range of chemical environments and is readily weldable and formable, making it the default choice for applications requiring durability without specialized high-temperature or high-strength demands. Engineers select 304 over ferritic alternatives when corrosion performance is critical, and over duplex or precipitation-hardening grades when cost, ease of fabrication, and reliable room-temperature toughness are prioritized.
316L stainless steel produced via selective laser melting (SLM) in the as-built condition is an austenitic stainless steel optimized for additive manufacturing. The low-carbon variant (L grade) reduces carbide precipitation and sensitization, making it particularly suitable for applications requiring corrosion resistance after printing without post-weld heat treatment. As-built SLM material exhibits relatively high strength and ductility directly from the powder bed fusion process, making it attractive for engineers seeking to consolidate component geometry and reduce secondary machining, though microstructural gradients and residual stresses typical of additive manufacturing must be managed depending on application criticality.
316L stainless steel is a low-carbon austenitic stainless steel alloyed with molybdenum, designed to resist corrosion in severely aggressive environments—particularly chloride-bearing and acidic media. It is widely used in chemical processing, offshore oil and gas, pharmaceutical manufacturing, and food processing where both corrosion resistance and ease of welding are critical; the low carbon content minimizes carbide precipitation during welding, making it superior to standard 316 for applications involving repeated thermal cycling or extended service in corrosive solutions.
316LVM is a low-carbon austenitic stainless steel specified by ASTM F138 for biomedical implant applications, characterized by controlled chromium, nickel, and molybdenum content that balances corrosion resistance with mechanical workability. It is the material of choice for permanent and semi-permanent implants in orthopedic and cardiovascular devices due to its superior resistance to bodily fluids and its ability to maintain structural integrity under cyclic loading in the human body. Engineers select 316LVM over commodity stainless steels (like 304) because the low-carbon content and molybdenum addition minimize sensitization and intergranular corrosion, while its fatigue and tensile properties reliably support load-bearing implant designs.
355.0 is a copper-silicon aluminum casting alloy designed for high-strength aerospace and automotive applications requiring good castability and elevated-temperature service. T6 temper (solution heat-treated and artificially aged) provides optimal strength and hardness for structural castings operating up to approximately 150°C.
356.0 is a aluminum-silicon casting alloy (7-9% Si) with copper additions, designed for high-temperature applications requiring good castability and moderate strength. The T6 temper (solution heat-treated and artificially aged) provides improved mechanical properties suitable for aerospace engine components, transmission housings, and other applications requiring strength retention up to approximately 200°C.
5083 aluminum is a non-heat-treatable Al-Mg alloy (approximately 4.4–5.0% Mg) with excellent seawater corrosion resistance and moderate strength, widely used in marine structures, pressure vessels, and cryogenic applications. The H112 temper (solution heat-treated and stress-relieved) provides controlled strength and ductility suitable for extrusions and plate stock, with typical yield strengths around 215–230 MPa and elongation values of 10–15% depending on section size.
5083 Aluminum is a non-heat-treatable Al-Mg alloy (approximately 4.4% Mg) with excellent seawater corrosion resistance, used primarily in marine structures, shipbuilding, and chemical storage applications. The O temper is fully annealed, providing maximum ductility and formability with minimum strength, making it suitable for applications requiring extensive cold-working or complex forming operations.
5086 aluminum is a non-heat-treatable Al-Mg alloy (nominally 3-4% Mg) with excellent seawater corrosion resistance and moderate strength, commonly used in marine vessels, automotive fuel tanks, and pressure vessels; H112 temper provides stress-relieved, partially annealed conditions suitable for applications requiring improved dimensional stability after fabrication while maintaining workability for extrusions and plate stock.
5086-H32 is a non-heat-treatable aluminum-magnesium alloy (approximately 3.5-4.5% Mg) strain-hardened to H32 temper, providing moderate strength with excellent seawater corrosion resistance suitable for marine structures, pressure vessels, and welded aerospace components. The H32 condition (half-hard after strain-hardening and stress relief) balances strength and ductility for applications requiring good formability while maintaining corrosion performance in salt-water and chemical environments.
5086 aluminum is a non-heat-treatable Al-Mg alloy (typically 3-4% Mg) widely used in marine and aerospace applications requiring superior corrosion resistance and moderate strength. The H34 temper (strain-hardened and partially annealed) provides balanced mechanical properties suitable for sheet and plate applications in seawater service and structural components exposed to corrosive environments.
5086-H36 is a non-heat-treatable aluminum-magnesium alloy (approximately 3-4% Mg) commonly used in marine, pressure vessel, and aerospace applications requiring superior seawater corrosion resistance and weldability. The H36 temper (strain-hardened and partially annealed) provides moderate strength with enhanced formability compared to fully hard conditions, making it suitable for structural applications in sheet and plate form where both strength and corrosion resistance are critical.
5086 aluminum is a non-heat-treatable Al-Mg alloy (approximately 3-4% Mg) offering excellent seawater corrosion resistance and weldability, widely used in marine structures, pressure vessels, and cryogenic applications. The O temper represents the fully annealed condition, providing maximum ductility and elongation at the expense of strength, making it suitable for applications requiring formability or as an intermediate condition before further processing.
5454 aluminum alloy is a non-heat-treatable 3% magnesium alloy offering excellent seawater corrosion resistance and good weldability, primarily used in marine structures and pressure vessels. The H32 temper (strain-hardened and partially annealed) provides moderate strength suitable for sheet and plate applications requiring a balance between formability and work-hardening characteristics, as documented in AMS-QQ-A-250/10 and MIL-HDBK-5J.
5454 aluminum alloy is a non-heat-treatable Al-Mg system (3–5% Mg) offering excellent seawater corrosion resistance and weldability, commonly used in marine and chemical handling applications. The H34 temper (strain-hardened and partially annealed) provides moderate strength with maintained ductility, suitable for sheet and plate fabrication where corrosion resistance and formability are prioritized over maximum strength.
5454 is an aluminum-magnesium alloy (nominally 2.7–3.6% Mg) with excellent corrosion resistance in marine and seawater environments, used in structural applications requiring weldability and moderate strength. The O temper represents the fully annealed condition, providing maximum ductility and formability with reduced strength, suitable for applications requiring cold-working after fabrication or maximum corrosion resistance without strength demands.
5456 Aluminum is a 5xxx-series (Al-Mg) alloy with magnesium as the primary alloying element, offering excellent seawater corrosion resistance and weldability for marine and offshore applications. The H111 temper (strain-hardened and stress-relieved) provides moderate strength suitable for extruded structural components requiring controlled work-hardening without full annealing, with typical yield strength around 180 MPa and elongation of 10-12%.
5456 aluminum is a non-heat-treatable Al-Mg alloy (nominally 5% Mg) with excellent seawater corrosion resistance, widely used in marine structures and welded pressure vessels. The H321 temper (strain-hardened and stress-relieved) provides moderate strength with improved stress-corrosion cracking resistance compared to fully work-hardened conditions, making it suitable for service in aggressive marine environments.
5456-O is an aluminum-magnesium alloy (nominally 5% Mg) in the fully annealed condition, providing excellent corrosion resistance in marine and seawater environments with moderate strength suitable for welded structures and pressure vessels. The O temper offers maximum ductility and elongation at break, making it ideal for applications requiring formability and weldability over strength, with availability in extruded and rolled forms per aerospace specifications AMS-QQ-A-200/7 and AMS-QQ-A-250/9.
5Cr-Mo-V is a chromium-molybdenum-vanadium alloy steel used in aircraft landing gear, fasteners, and structural components requiring high strength and fatigue resistance at ambient temperatures. The Q&T (quenched and tempered) condition delivers tensile strengths typically in the 1,400–1,900 MPa range with good fracture toughness and fatigue performance, making it suitable for highly stressed aerospace applications where weight efficiency and reliability are critical.
6013-T6 is a medium-strength aluminum alloy containing copper and magnesium, solution heat-treated and artificially aged to peak hardness, offering good fatigue resistance and moderate corrosion resistance suitable for aircraft skin and structural sheet applications. This temper provides balanced strength (yield ~35 ksi, ultimate tensile ~45-48 ksi) with adequate ductility and bearing capabilities for riveted airframe structures per AMS 4216 and AMS 4347 specifications.
6061 is an aluminum-magnesium-silicon alloy offering moderate strength with excellent corrosion resistance and weldability, widely used in aerospace structures, marine applications, and general engineering. Available in multiple tempers ranging from T4 (solution heat-treated) to T651 (solution heat-treated, stress-relieved, and artificially aged) to meet varying strength and dimensional stability requirements.
6061 Aluminum T42 is a precipitation-hardened aluminum-magnesium-silicon alloy in a solution heat-treated and artificially aged condition, providing moderate strength with good corrosion resistance and weldability suitable for aerospace structural applications. Available in rolled, drawn, or cold-finished rod and special shapes per AMS-QQ-A-225/8, this temper balances tensile strength, yield strength, and ductility for applications requiring reliable performance at moderate temperatures.
6061-T6 is a precipitation-hardened aluminum-magnesium-silicon alloy in a solution heat-treated and artificially aged condition, providing tensile yield strength around 40 ksi with good corrosion resistance and machinability. Widely used in aerospace, automotive, and structural applications where moderate strength, weldability, and environmental resistance are required, particularly in forgings, extrusions, and drawn shapes.
6061-T62 is a heat-treatable aluminum alloy with magnesium and silicon as primary alloying elements, solution heat-treated and artificially aged to T62 condition for moderate strength and good corrosion resistance suitable for aerospace structural components, fasteners, and general engineering applications. This temper provides controlled strength levels with adequate ductility and toughness, commonly supplied as rolled, drawn, or cold-finished rod and special shapes per AMS 4115/4116 specifications.
6061-T651 is a medium-strength Al-Mg-Si alloy in a solution heat-treated and stress-relieved condition, widely used in aerospace structural applications, marine hardware, and general engineering components where moderate strength and excellent corrosion resistance are required. This temper provides controlled mechanical properties suitable for precision machining with residual stress relief to minimize distortion in service.
6151-T6 is a heat-treated aluminum alloy (Al-Mg-Si) used in aerospace forgings that achieves high strength through solution heat treatment and artificial aging. T6 temper provides enhanced yield strength and tensile strength suitable for structural aircraft components requiring good fatigue resistance and moderate corrosion resistance.
7049/7149 aluminum is a high-strength zinc-copper-magnesium alloy used primarily in aircraft structural components and landing gear requiring superior fatigue resistance and stress-corrosion cracking (SCC) resistance. The T73 temper is overaged to provide improved SCC resistance at slight strength reduction compared to T6, maintaining excellent bearing and shear properties with yield strength around 450-475 MPa and ultimate tensile strength around 520-540 MPa.
7050 is a zinc-copper aluminum alloy with exceptional strength-to-weight ratio and fracture toughness, used primarily in aerospace airframe structures, wings, and fuselage components operating at elevated temperatures. Available in multiple overaged and peak-aged tempers (T6151 through T7751) that balance yield strength (typically 350–520 MPa depending on temper) with improved stress-corrosion cracking resistance and fatigue performance for critical load-bearing applications.
7050 aluminum is a high-strength Al-Zn-Mg-Cu alloy used in aerospace structures and airframes where exceptional damage tolerance and fracture toughness are required. The T7452 temper provides stress-relief through controlled heat treatment to minimize residual stresses from forging while maintaining high static strength (yield and ultimate tensile strengths in the 435–480 MPa range) and improved resistance to stress-corrosion cracking compared to peak-aged tempers.
7075 aluminum is a high-strength Al-Zn-Mg-Cu alloy used primarily in aerospace structures, offering yield strengths of 70–80 ksi in peak-hardness T6 condition with moderate corrosion resistance improved in overaged T73 and T7351 variants at reduced strength levels. The extensive temper range (T6 through T7751) provides design flexibility from maximum strength applications to enhanced stress-corrosion cracking resistance in critical components, with elastic properties (Young's modulus ~10.4 Msi, density 0.101 lb/in³) consistent across temper variants.
7075 Aluminum T6 is a high-strength aluminum-zinc alloy (with magnesium and copper) solution heat-treated and artificially aged to peak hardness, providing tensile strengths in the 70–80 ksi range with excellent bearing strength and rigidity for critical aerospace structural applications requiring high strength-to-weight ratios. The T6 temper delivers superior fatigue and bearing properties compared to other 7075 conditions but exhibits lower fracture toughness and stress-corrosion resistance, limiting use to applications where sustained tensile stress and corrosive environments are not simultaneously severe.
7075 aluminum alloy in T73 temper is a high-strength aluminum-zinc-magnesium-copper alloy overaged to improve stress-corrosion cracking resistance while maintaining excellent strength characteristics; it is widely used in aircraft structures, fuselage skins, and aerospace components requiring superior fatigue and corrosion resistance in the 40,000–70,000 psi yield strength range.
7175 aluminum is a high-strength Al-Zn-Mg-Cu alloy used primarily in aircraft primary structure and military applications, offering tensile strengths exceeding 500 MPa with good fatigue resistance and damage tolerance. The alloy exhibits limited corrosion resistance in marine environments and reduced fracture toughness at higher tempers, necessitating careful temper selection and protective coatings for critical applications.
7175 aluminum T73511 is a high-strength zinc-copper-magnesium alloy in an overaged temper condition that provides enhanced stress-corrosion cracking resistance with tensile yield strength around 435 MPa, suitable for aircraft structural components and fasteners requiring superior corrosion performance in humid environments. The T73511 condition (solution heat-treated, cold-worked, and artificially overaged) balances strength retention with improved exfoliation corrosion resistance compared to T6 tempers, making it preferred for long-term durability in aerospace applications per AMS 4344 specification.
7249 is an Al-Zn-Mg-Cu alloy in the 7xxx series designed for high-strength aerospace applications requiring excellent fatigue resistance and stress-corrosion cracking (SCC) resistance; it combines strength levels comparable to 7075 with improved SCC resistance through controlled grain structure and overaging tempers (T74xx, T75xx, T77xx variants).
7249 is a high-strength aluminum-copper-magnesium-zinc alloy designed for aircraft structural applications requiring superior fatigue resistance and damage tolerance; the T7452 temper (solution heat-treated, artificially aged, and stress-relieved by stretching) provides optimized toughness and reduced residual stress in hand-forged components while maintaining yield strengths exceeding 400 MPa and excellent bearing load capability.
7475 Aluminum T61 is a high-strength aluminum-zinc-magnesium-copper alloy in an artificially aged condition, providing ultimate tensile strengths in the 500+ MPa range with improved stress-corrosion cracking resistance compared to 7075. Used primarily in aerospace airframe structures and military applications where damage tolerance, fatigue performance, and bearing strength are critical, available as sheet per AMS 4084 specification.
7475 aluminum is a zinc-copper-magnesium precipitation-hardened alloy engineered for high-strength aerospace structural applications, particularly where exfoliation corrosion resistance is critical; T651 temper (solution heat-treated, artificially aged, and stress-relieved by controlled stretching) provides ultimate tensile strengths in the 470–510 MPa range with improved through-thickness properties and corrosion resistance compared to T73 variants, making it suitable for highly loaded aircraft components including wing skins, fuselage frames, and pressure vessels.