292 materials
15-5PH is a precipitation-hardening stainless steel (Fe-Cr-Ni-Cu-Nb) that combines moderate corrosion resistance with high strength and good fatigue properties, widely used in aerospace fasteners, springs, and structural components requiring performance to approximately 300°C. Available tempers range from H1025 (lowest strength) through H1150 (highest strength), with H900/H925/H935 providing intermediate strength levels optimized for specific applications balancing strength, toughness, and stress-corrosion cracking resistance.
15-5PH is a precipitation-hardened martensitic stainless steel (15% Cr, 5% Ni, 3% Cu) designed for high-strength aerospace and mechanical applications requiring excellent corrosion resistance and fatigue performance up to approximately 550°C. The H1025 condition provides maximum hardness and strength through precipitation hardening, typically yielding tensile strengths in the 1310–1380 MPa range with good toughness relative to other high-strength stainless alloys.
15-5PH Stainless Steel H1100 is a martensitic precipitation-hardening stainless steel (15% Cr, 5% Ni, 3.1% Cu) in the high-strength H1100 condition, providing yield strengths around 1310 MPa with moderate elongation (~8%), used in aerospace fasteners, turbine components, and high-strength applications requiring corrosion resistance to 300°C. The H1100 condition represents full hardening and aging, delivering maximum strength with good fatigue and stress-corrosion cracking resistance compared to lower tempers.
15-5PH is a chromium-nickel precipitation-hardened martensitic stainless steel (containing ~15% Cr, ~5% Ni, plus copper and niobium) used in aerospace fasteners, springs, and high-strength structural components requiring corrosion resistance to 600°F. The H1150 condition is solution heat-treated and aged to provide tensile strength around 190 ksi with good ductility and toughness for demanding service environments.
15-5PH is a precipitation-hardening stainless steel containing chromium, nickel, and copper that achieves high strength through aging treatment, commonly used in aerospace applications requiring corrosion resistance to approximately 600°F. The H900 condition represents peak hardness achieved through solution treatment followed by controlled precipitation hardening, providing yield strength around 200 ksi with good fatigue resistance and dimensional stability in critical fasteners and structural components.
15-5PH H925 is a precipitation-hardened martensitic stainless steel (15% Cr, 5% Ni) in the H925 condition—solution heat-treated, cold-worked, and aged at 925°F—providing yield strength of approximately 170 ksi with good corrosion resistance and fracture toughness for aerospace fasteners and structural components operating to moderate temperatures. This condition balances high strength with ductility suitable for applications requiring reliable fatigue performance in saltwater and mildly corrosive environments.
15-5PH stainless steel is a precipitation-hardened martensitic stainless steel containing 15% chromium and 5% nickel, used primarily in aerospace applications requiring high strength and corrosion resistance at elevated temperatures. The H935 condition provides a nominal yield strength of 1,310 MPa (190 ksi) through precipitation hardening, offering excellent fatigue resistance and dimensional stability in critical structural and rotating components.
17-4PH is a precipitation-hardening stainless steel optimized for additive manufacturing via selective laser melting (SLM), with H900 heat treatment applied post-build to achieve peak strength and hardness. This material combines corrosion resistance typical of stainless steels with the high strength-to-weight ratio needed for aerospace and defense applications where complex geometries and minimal material waste are critical; engineers select it when traditional wrought 17-4PH cannot economically produce the required part geometry or when the design benefits from direct AM fabrication.
17-4 PH is a precipitation-hardening martensitic stainless steel that combines high strength with corrosion resistance through controlled heat treatment (H900 condition represents the fully hardened state). It is widely used in aerospace, defense, and oil & gas industries where components must withstand demanding mechanical loads in corrosive or marine environments while maintaining dimensional stability. Engineers select 17-4 PH when they need a good balance of strength, toughness, and corrosion resistance in fasteners, pump shafts, valve bodies, and structural components—offering superior performance to standard austenitic stainless steels in applications requiring higher hardness and fatigue resistance.
17-4PH stainless steel (Fe-Cr-Ni-Cu precipitation-hardening alloy) in H1000 condition is an investment casting used in aerospace applications requiring high strength and corrosion resistance at elevated temperatures; the H1000 temper provides yield strength around 1310 MPa (190 ksi) with moderate ductility through precipitation hardening at 482°C (900°F).
17-4PH (UNS S17400) is a precipitation-hardening martensitic stainless steel containing chromium, nickel, and copper that achieves high strength through heat treatment, commonly used in aerospace fasteners, pump shafts, and turbine components requiring corrosion resistance to 600°F. The H1025 condition provides a tensile yield strength of approximately 180 ksi after aging, offering excellent bearing and fatigue strength with moderate elongation suitable for highly stressed structural applications in jet engines and pressure vessels.
17-4PH (precipitation-hardened stainless steel) in H1100 condition is a martensitic stainless steel strengthened by copper and niobium precipitation, offering yield strength around 1,310 MPa with good corrosion resistance and toughness, used extensively in aerospace applications including fasteners, shafts, and structural components. The H1100 temper provides a balance of high strength and ductility through controlled aging after solution treatment and cold work.
17-4PH H1150 is a precipitation-hardened martensitic stainless steel (17% Cr, 4% Ni, Cu-strengthened) designed for high-strength aerospace and defense applications requiring corrosion resistance up to ~300°C. The H1150 condition (solution-treated and aged at 1150°F) provides ultrahigh yield strength (typically 1310 MPa) with moderate elongation, making it suitable for critical fasteners, shafts, and structural components in gas turbines and aircraft engines.
17-4PH stainless steel is a precipitation-hardening martensitic stainless steel (Fe-Cr-Ni-Cu-Nb) used extensively in aerospace and high-performance applications for components requiring high strength, corrosion resistance, and thermal stability to approximately 600°C. The H900 condition, achieved through solution annealing followed by precipitation hardening at 480°C, delivers yield strengths around 1,310 MPa and ultimate tensile strengths near 1,450 MPa with moderate ductility, making it suitable for critical fasteners, pump shafts, compressor components, and bearing races.
17-7PH is a precipitation-hardening stainless steel containing 17% chromium and 7% nickel, designed for high-strength aerospace applications requiring excellent corrosion resistance and elevated-temperature capability. The H1050 condition provides maximum strength through controlled precipitation hardening, suitable for critical fasteners, springs, and structural components in aircraft and engines operating up to approximately 600°C.
**2014 Aluminum** 2014 is a copper-alloyed aluminum alloy used primarily in aircraft fuselage and structural applications where moderate-to-high strength and good machinability are required. The alloy offers strength comparable to 2024 with superior machinability, typical yield strengths of 60–70 ksi depending on temper, and moderate corrosion resistance requiring protective cladding or coatings in service.
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.