214 materials
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.
7475 Aluminum T761 is a high-strength aluminum-zinc-magnesium-copper alloy in a stretched temper condition providing excellent fracture toughness and stress-corrosion cracking resistance for critical aerospace structural applications. The T761 temper achieves superior damage tolerance through controlled overaging after solution treatment and controlled stretching, making it suitable for highly loaded aircraft components requiring reliable performance in sustained-stress environments.
7475 aluminum is a zinc-copper-magnesium Al-Zn-Cu-Mg alloy used in high-strength aerospace applications requiring excellent damage tolerance and fatigue resistance. The T7651 temper (solution heat-treated, stress-relieved, and overaged) provides yield strength in the 350–420 MPa range with improved stress-corrosion cracking resistance compared to T6 conditions, making it suitable for critical structural components in aircraft wings and fuselages.
A201.0 is a copper-modified aluminum casting alloy designed for aerospace applications requiring moderate strength and improved castability. The T7 temper provides stress-relief heat treatment following solution heat treatment and artificial aging, delivering dimensional stability and reduced residual stress for precision cast components operating at elevated temperatures.
A201.0 is an aluminum-copper casting alloy with controlled impurities used primarily in aerospace engine components and high-temperature structural applications, offering superior strength retention to approximately 300°C. The T7 condition (solution heat-treated and artificially aged) provides peak hardness and yield strength with controlled ductility, balancing high-temperature capability with casting integrity for critical bearing and structural loads.
A357.0 is an aluminum-silicon casting alloy (7% Si) with enhanced strength and soundness characteristics, used primarily in aerospace applications requiring high-integrity castings. The T6 temper (solution heat-treated and artificially aged) provides superior tensile strength, yield strength, and bearing strength suitable for critical structural and engine components operating at moderate temperatures.
AerMet 100 is a high-strength martensitic steel alloyed with cobalt, nickel, molybdenum, and chromium, designed for critical aerospace structural and fastener applications requiring exceptional strength-to-weight ratios at service temperatures to 350°F. The STA condition (solution treated and aged) achieves ultimate tensile strengths of ~280 ksi with good fracture toughness and fatigue resistance, making it suitable for landing gear, airframe fittings, and high-performance fasteners in military aircraft.
AF1410 is a low-alloy steel containing chromium and molybdenum, designed for high-strength aerospace and structural applications requiring excellent fatigue resistance and fracture toughness. Condition A represents the annealed state, providing optimal machinability and ductility prior to final heat treatment for service conditions.
AISI 1025 is a low-carbon steel (0.22–0.28% C) used in structural and mechanical applications requiring moderate strength and good machinability. Annealed and normalized conditions provide different strength levels and ductility characteristics, with the material offering adequate toughness for general engineering applications below 400°C.
AISI 4340 is an ultra-high-strength low-alloy steel with excellent hardenability. Widely used for aircraft landing gear, shafts, and gears where very high strength-to-weight ratio is needed.
Aluminum 2024-T3 is a heat-treatable aluminum-copper alloy in the precipitation-hardened T3 condition, combining aluminum with 3.8–4.9% copper and 1.2–1.8% magnesium to achieve high strength-to-weight performance. It is widely used in aerospace structures, military aircraft fuselages and wings, and high-stress mechanical components where weight reduction and strength are critical. Engineers select 2024-T3 over softer aluminum alloys when superior strength is needed, though it offers lower corrosion resistance than some alternatives and is typically clad or painted for protection in service environments.
Aluminum 6061-T6 is a precipitation-hardened aluminum alloy strengthened through heat treatment, widely recognized as one of the most versatile medium-strength aluminum grades in structural and semi-structural applications. It is extensively used in aerospace components, automotive parts, marine structures, and general industrial fabrication where a balance of strength, corrosion resistance, and machinability is required. Engineers select 6061-T6 over other aluminum alloys for its excellent weldability, good resistance to seawater and atmospheric corrosion, and ease of machining, making it ideal for applications where both performance and manufacturability are critical constraints.
Aluminum 7075-T6 is a precipitation-hardened aluminum alloy strengthened by copper, magnesium, and zinc additions, representing the highest-strength aluminum alloy commonly available in industry. It is the workhorse material for weight-critical, high-performance structures where exceptional strength-to-weight ratio is essential—notably in aircraft fuselage and wing components, aerospace fasteners, and defense systems. Engineers select 7075-T6 when competing materials like 6061 or 2024 cannot meet load requirements without excessive weight penalty, though careful design is needed because its lower fracture toughness makes it more sensitive to fatigue and stress concentration than some alternatives.
AM-350 is a precipitation-hardening martensitic stainless steel (17Cr-4.3Ni-2.6Mo-1.3Ti) designed for aerospace applications requiring high strength at elevated temperatures up to approximately 600°C with good corrosion resistance. The SCT 850 and stabilized (sta) tempers provide controlled hardness and dimensional stability through specific heat treatment cycles, making it suitable for jet engine compressor components and high-strength fasteners.
AM-355 is a precipitation-hardening stainless steel (Fe-Cr-Ni-Mo-Al) engineered for high-strength aerospace applications requiring excellent corrosion resistance and strength retention to moderate temperatures. Available in multiple heat-treated conditions (SCT 1000, STA, T1000, T850), it provides yield strengths ranging from approximately 140 to 180 ksi depending on temper, with typical operating capability to 600°F.
AM-355 stainless steel is a martensitic stainless alloy (13% Cr, 4.7% Ni, 2.7% Mo) used in aerospace applications requiring high strength and corrosion resistance at elevated temperatures. The T850 temper (solution heat-treated and age-hardened) provides yield strengths in the 1380–1520 MPa range with good bearing strength and moderate ductility, suitable for critical fasteners, compressor components, and high-stress structural applications to approximately 315°C.
ASTM A36 is a mild carbon steel specified by the American Society for Testing and Materials, characterized by low carbon content and straightforward iron-manganese chemistry that prioritizes weldability and formability over high strength. It is the most widely used structural steel in North America, serving as the baseline material for bridges, buildings, towers, and machinery frames where moderate strength and excellent ductility are required. Engineers select A36 for its proven performance in welded construction, cost-effectiveness, ready availability, and reliable behavior under static loads; it remains the default choice for structural applications unless higher strength grades or corrosion resistance are specifically needed.
ASTM A992 is a high-strength structural steel specification commonly used in welded and bolted construction, designed to balance strength with weldability and toughness for demanding structural applications. It is the modern standard replacement for ASTM A36 in building and bridge construction, offering superior performance in seismic-prone regions and heavy-load scenarios where engineers need predictable strength without sacrificing ductility or fatigue resistance. Engineers select A992 over older grades when cost-effectiveness must be balanced against improved safety margins and code compliance in modern construction standards.
AZ31B is a wrought magnesium alloy containing aluminum and zinc, widely used in aerospace, automotive, and defense applications where weight reduction is critical. It offers moderate strength with good corrosion resistance and machinability, with strength and ductility varying significantly by temper condition from annealed (O) to strain-hardened (H24, H26) states.
AZ61A magnesium is a wrought alloy containing aluminum and zinc for improved strength and creep resistance, suitable for aerospace forgings and extruded components requiring moderate strength at elevated temperatures. The F (as-fabricated) temper provides baseline mechanical properties without heat treatment, offering yield strengths around 160 MPa with good formability for complex geometries in aircraft engine mounts and structural applications.
AZ91C is a magnesium alloy containing aluminum and zinc additions, widely used in aerospace and automotive applications where lightweight structural components are required. The T6 temper (solution heat-treated and artificially aged) provides improved strength and dimensional stability at moderate temperatures, with typical operating limits around 150°C and good castability characteristics for complex geometries.
AZ92A is a magnesium alloy containing aluminum and zinc, used primarily in aerospace and defense applications where lightweight structural components are required. The T6 temper (solution heat-treated and artificially aged) provides enhanced strength and hardness suitable for moderate-temperature service, with typical applications including aircraft engine housings and transmission cases.
Beryllium is a lightweight refractory metal with exceptional stiffness-to-weight ratio and thermal stability, used primarily in aerospace and defense applications requiring high-performance structural and thermal components. Both hot-pressed conditions offer near-identical elastic properties with ground and etched surfaces, with stress-relieved material providing residual stress mitigation for dimensional stability in critical applications.
Hot-pressed beryllium in ground and etched condition offers high strength-to-weight ratio with excellent thermal conductivity and dimensional stability, used primarily in aerospace and defense applications requiring lightweight structural components and precision instruments. This condition provides controlled grain structure and improved machinability compared to as-cast beryllium, with tensile strengths typically ranging 300–450 MPa depending on processing parameters, governed by AMS 7906 specification.
CoCrMo is a wrought cobalt-chromium-molybdenum alloy (ASTM F1537) designed for high-strength, corrosion-resistant applications requiring excellent biocompatibility and fatigue durability. It is the workhorse material for load-bearing orthopedic implants—hip and knee replacements, spinal fusion devices—and cardiac applications like stents and heart valve components, where it must withstand years of cyclic loading in the corrosive physiological environment. Engineers select this alloy over titanium or stainless steel alternatives when implants must tolerate high contact stresses, when manufacturing via wrought processing (forging, rolling) is economical, and when the material's proven long-term clinical track record is essential for regulatory approval.
CoCrMo (cobalt-chromium-molybdenum) cast alloy per ASTM F75 is a cobalt-based superalloy designed for extreme corrosion resistance and biocompatibility, with chromium and molybdenum additions providing oxidation resistance and solid-solution strengthening. This material is the workhorse for load-bearing orthopedic implants and dental prosthetics where long-term implantation demands both mechanical reliability and absence of toxic leaching. Engineers select cast CoCrMo over alternatives (stainless steel, titanium alloys) primarily for superior corrosion resistance in physiological environments and proven decades-long clinical track record, though its lower machinability and higher density compared to Ti alloys make it less preferred for weight-critical aerospace applications.
Commercially pure titanium (CP-Ti) in annealed condition is an unalloyed titanium grade offering excellent corrosion resistance and biocompatibility with moderate strength suitable for applications requiring ductility and formability. Primary uses include aerospace components, chemical processing equipment, and medical implants; the annealed condition provides optimal ductility and fracture toughness with yield strengths typically 25–50 ksi and elongation exceeding 20% across available forms (bar, sheet, plate, and extruded shapes).
Copper C110 is a commercially pure, oxygen-free copper grade (>99.9% Cu) widely used where electrical conductivity and thermal performance are critical. It is the standard choice for electrical wiring, busbars, transformers, and heat exchangers because of its excellent electrical and thermal transport properties combined with good workability. Engineers select C110 over lower-purity copper grades when oxygen contamination must be minimized to avoid brittleness in welded or cold-worked components, and over specialty alloys when the application does not require strength at elevated temperature or corrosion resistance beyond what pure copper naturally provides.
CP Titanium Grade 2 is a commercially pure (unalloyed) titanium metal offering an excellent balance of corrosion resistance, biocompatibility, and weldability at moderate strength levels. It is widely used in chemical processing equipment, seawater-handling systems, medical implants, and aerospace applications where corrosion immunity and weight savings outweigh the need for very high strength, making it a preferred choice over stainless steels in aggressive environments and biomedical contexts.
Cu-Al-Ni is a copper-based shape memory alloy (SMA) that exhibits both the one-way shape memory effect and superelastic behavior, allowing it to recover large deformations upon heating or unloading. It is used in actuators, sealing devices, and vibration dampers where its ability to transform between crystalline phases at relatively moderate temperatures provides reliable, reversible motion without external power. Engineers select this alloy over NiTi alternatives when lower cost, higher thermal conductivity, or operation in the 150–200 °C range is required, though it offers narrower temperature windows and greater thermal hysteresis than nickel-titanium counterparts.
Custom 450 stainless steel is a precipitation-hardened martensitic stainless steel (17% Cr, 4% Ni, 1% Mo) designed for high-strength aerospace applications requiring corrosion resistance and elevated temperature capability to approximately 600°F. The H1050 condition (solution heat-treated and aged) delivers tensile strength around 180 ksi with moderate ductility, suitable for bearing races, fasteners, and structural components in gas turbine engines and airframes per AMS 5763/5773 specifications.
Custom 450 is a martensitic stainless steel precipitation-hardened to the H900 condition, delivering very high strength (typically 1450+ MPa yield) with good corrosion resistance and fatigue performance for aerospace bearing and structural applications. The H900 temper provides optimized strength-toughness balance through controlled heat treatment, suitable for highly-stressed rotating components and fasteners per AMS 5763/5773 specifications.
Custom 450 stainless steel is a martensitic stainless steel with approximately 13% chromium and 1.0% molybdenum, designed for high-strength aerospace and gas turbine applications requiring superior corrosion resistance and elevated temperature capability. Solution-treated condition provides optimized balance of strength and toughness through austenitic conditioning and controlled cooling, meeting AMS 5763/5773 specifications for bar stock in critical rotating components.
Custom 455 is a precipitation-hardening martensitic stainless steel (Fe-Ni-Cr-Mo-Ti base) used primarily in aerospace applications requiring high strength at elevated temperatures up to 1000°F. The H1000 condition provides peak hardness and strength through aging treatment, delivering ultimate tensile strength around 180–200 ksi with good fatigue and bearing load characteristics, making it suitable for critical rotating components and fasteners in gas turbine engines and launch vehicle structures.
Custom 455 is a martensitic precipitation-hardening stainless steel with high strength and corrosion resistance, used in aerospace applications including fasteners, bearings, and structural components. The H950 temper provides approximately 1450 MPa yield strength through precipitation hardening, offering excellent fatigue performance and stress-corrosion cracking resistance suitable for demanding high-strength applications up to moderate temperatures.
Custom 465 stainless steel is a precipitation-hardened martensitic stainless steel containing cobalt and molybdenum, designed for high-strength aerospace applications requiring exceptional fatigue resistance and bearing performance. The H1000 condition provides maximum hardness and strength through precipitation hardening, delivering ultimate tensile strengths in the 1900+ MPa range with good corrosion resistance and dimensional stability at elevated temperatures.
Custom 465 is a precipitation-hardened martensitic stainless steel containing cobalt and molybdenum, designed for high-strength aerospace and bearing applications requiring superior fatigue resistance and dimensional stability at elevated temperatures up to ~480°C. The H950 condition (950°F aged) provides ultimate tensile strength exceeding 1700 MPa with good bearing fatigue strength and controlled toughness, suitable for highly-stressed rotating components and precision bearing races per AMS 5936.
Cu-Zn-Al is a copper-based shape memory alloy (SMA) that exhibits superelastic and shape-recovery behavior through reversible phase transformations between austenite and martensite crystal structures. This alloy family is valued in applications requiring actuation, vibration damping, and precise mechanical recovery at moderate temperatures, with Cu-Zn-Al offering lower cost and better machinability than Ni-Ti alternatives while accepting trade-offs in repeatability and thermal cycling stability. It operates in a narrow temperature window around room temperature, making it suited to ambient-condition devices but limiting use in high-temperature environments compared to competing SMAs.
D357.0 T6 is a high-strength aluminum casting alloy (Al-Si-Cu-Mg) in solution heat-treated and artificially aged condition, used primarily in aerospace applications requiring excellent castability and elevated-temperature strength up to approximately 300°F. The T6 temper delivers high yield and tensile strength with good bearing strength characteristics, making it suitable for critical structural and load-bearing cast components where dimensional precision and strength consistency are required.
Duplex stainless steel 2205 is a two-phase ferritic-austenitic stainless steel combining the corrosion resistance of austenitic grades with the strength and stress-corrosion cracking resistance of ferritic alloys. It is widely employed in offshore oil and gas infrastructure, chemical processing plants, and desalination systems where aggressive chloride environments and high pressures demand superior pitting and crevice corrosion resistance. Engineers select duplex 2205 over single-phase austenitic or ferritic stainless steels when both mechanical robustness and extended service life in seawater or acidic chloride solutions are critical cost drivers.
EZ33A is a magnesium-rare earth alloy (containing zirconium and yttrium) designed for elevated-temperature aerospace applications requiring creep resistance and dimensional stability. The T5 temper (artificially aged) provides moderate strength and creep resistance up to approximately 250–300°C, making it suitable for engine casings, transmission housings, and other high-temperature structural components.
Fe-Mn-Si shape memory alloy is an iron-based intermetallic compound that exhibits reversible martensitic phase transformation, enabling controlled recovery of pre-set shapes when heated above its transition temperature. This alloy system is valued in engineering applications requiring low-cost alternatives to nickel-titanium (NiTi) SMAs, with particular strength in seismic damping, pipeline couplings, and thermal actuators where moderate recovery strain and reliable cycling performance are acceptable trade-offs for reduced material cost and improved corrosion resistance. Unlike NiTi, Fe-Mn-Si alloys tolerate larger thermal hysteresis windows and perform well in iron-rich industrial environments, making them especially competitive in civil infrastructure, automotive safety systems, and geothermal applications.
Hastelloy X is a nickel-cobalt-chromium-molybdenum superalloy designed for high-temperature applications requiring excellent creep resistance and oxidation resistance up to 2200°F. Primary applications include jet engine components, gas turbine blades, and aerospace exhaust systems where sustained elevated-temperature strength and resistance to thermal fatigue are critical.
Hastelloy X is a nickel-chromium-molybdenum-cobalt superalloy designed for high-temperature applications requiring excellent corrosion and oxidation resistance up to 2200°F (1204°C); the solution-treated condition provides optimal ductility and toughness for sheet and plate forms used in aerospace engines, heat exchangers, and thermal processing equipment, with typical yield strengths in the 40-50 ksi range and elongations exceeding 30%.
HAYNES 230 is a nickel-chromium-tungsten superalloy designed for high-temperature structural applications requiring excellent creep resistance and oxidation resistance up to 1150°C (2100°F). The 2200 Anneal condition provides stress relief and recrystallization, delivering optimal combination of tensile strength and ductility for gas turbine engines, aerospace fasteners, and chemical processing equipment operating in oxidizing environments at elevated temperatures.