24,657 materials
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.
AZ92A is a magnesium alloy containing aluminum and zinc that is precipitation hardened in the T6 condition to provide high strength and improved creep resistance for elevated-temperature applications in aerospace castings. T6 temper offers solution heat treatment followed by artificial aging, delivering tensile yield strengths in the 160–180 MPa range with moderate elongation suitable for investment, permanent mold, and sand casting processes per AMS specifications.
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.
Beryllium stress-relieved material, specified per AMS 7902, exhibits low density (1.85 g/cm³) with high specific stiffness and thermal conductivity, suited for aerospace and defense structural and thermal applications requiring weight minimization. The stress-relieved condition (achieved through controlled heating and surface finishing via grinding and etching) reduces residual stresses from prior processing while maintaining strength, providing improved dimensional stability and fracture toughness compared to as-worked conditions.
C17200 copper-beryllium is a precipitation-hardenable copper alloy containing 1.6-2.0% beryllium, used in aerospace and defense applications requiring high strength-to-weight ratio, excellent fatigue resistance, and superior electrical and thermal conductivity. The alloy exhibits yield strengths up to 180 ksi in hardened conditions with operating capability to ~400°C, making it suitable for springs, connectors, and structural fasteners in demanding environments.
C17200 Copper Beryllium H04 is a precipitation-hardenable copper-beryllium alloy in the half-hard temper condition, offering high strength (approximately 1,310 MPa tensile), excellent fatigue and bearing performance, and superior electrical conductivity retention compared to other high-strength copper alloys; used in aerospace electrical contacts, switch components, and precision bearings where strength, wear resistance, and electrical properties are simultaneously required.
C17200 copper-beryllium alloy in TF00 condition (solution heat-treated and precipitation-hardened) is a high-strength, non-magnetic beryllium copper used in aerospace bearing and structural applications requiring exceptional strength-to-weight ratio and fatigue resistance. The TF00 temper provides yield strength approximately 150–180 ksi with controlled elongation, excellent fatigue performance, and good electrical conductivity while maintaining beryllium's characteristic hardness and wear resistance.
C355.0 is a copper-containing aluminum casting alloy (Al-Si-Cu-Mg system) used primarily in aerospace and automotive applications requiring moderate strength and good castability. The T6 temper (solution heat-treated and artificially aged) provides enhanced mechanical properties suitable for structural components operating at elevated temperatures with improved dimensional stability and corrosion resistance compared to as-cast conditions.
C355.0 is an aluminum-copper-magnesium casting alloy with silicon modification, used primarily in aerospace and high-performance applications requiring elevated temperature strength and dimensional stability. The T6 temper (solution heat-treated and artificially aged) provides tensile strengths of approximately 35–40 ksi with good bearing strength and moderate ductility, making it suitable for complex cast aerospace components operating at intermediate temperatures.
C86300 is a copper-manganese-tin-iron alloy (manganese bronze) used in marine hardware, valves, and pump components requiring moderate strength and excellent corrosion resistance in seawater environments. The as-cast condition provides nominal tensile strength around 60-70 ksi with good castability and wear resistance, though lower ductility than wrought variants.
C86300 manganese bronze is a copper-tin-zinc alloy (containing approximately 60% copper, 30% zinc, and 10% tin) used for marine and heavy-duty industrial castings requiring moderate strength and excellent corrosion resistance in seawater environments. The as-cast condition provides as-solidified properties with tensile strength around 45–55 ksi and moderate elongation, suitable for propellers, pump housings, and valve bodies where castability and seawater corrosion resistance are prioritized over maximum strength.
C86500 manganese bronze is a copper-based alloy (Cu-Mn-Fe-Zn system) used in marine propellers, valve bodies, and other seawater-service components due to excellent corrosion resistance and moderate strength. The as-cast condition provides good castability and seawater corrosion resistance, with density approximately 8.5 g/cm³ and Young's modulus around 100 GPa, making it suitable for cast marine hardware operating in aggressive aqueous environments.
C86500 Manganese Bronze is a copper-zinc-manganese-iron alloy cast in as-cast condition, providing moderate strength (typically 40-50 ksi UTS) with good corrosion resistance and machinability for marine hardware, valve bodies, and pump impellers. The as-cast condition exhibits lower strength and ductility compared to heat-treated variants but offers improved castability and dimensional stability for complex geometries per AMS 4860.
Clad 7475 is a high-strength aluminum-zinc-magnesium alloy with copper alloying used primarily in aircraft structures and aerospace applications requiring damage-tolerance and fatigue resistance. The material is clad with pure aluminum for enhanced corrosion resistance and offers yield strengths ranging from approximately 380–505 MPa depending on temper, with excellent fracture toughness characteristics across multiple overaged and retrogressed-and-reaged temper conditions.
Clad 7475 aluminum alloy in T61 temper is a high-strength aerospace aluminum with zinc, magnesium, and copper alloying elements, featuring a protective pure aluminum cladding layer that provides superior corrosion resistance while maintaining exceptional bearing strength and fatigue resistance for critical airframe components. T61 condition achieves its properties through solution heat treatment and controlled aging, delivering yield strengths in the 435–460 MPa range with good damage tolerance suitable for aircraft wing and fuselage structure applications per AMS 4207 specification.
Clad 7475 aluminum is a high-strength 7xxx-series alloy (Zn-Mg-Cu system) with a thin pure aluminum cladding layer for enhanced corrosion resistance, used primarily in aerospace structural applications requiring exceptional strength-to-weight ratios and fatigue performance. The T761 temper (overaged condition) provides reduced quench sensitivity and improved stress-corrosion cracking resistance compared to peak-aged conditions, with yield strengths approximately 440–480 MPa and ultimate tensile strengths of 500–550 MPa in sheet form.
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) is an unalloyed titanium grade used in aerospace, chemical processing, and biomedical applications where corrosion resistance and moderate strength are required at temperatures up to ~300°C. The annealed condition provides optimal ductility and fracture toughness with approximately 40% lower strength compared to higher-strength titanium alloys, making it suitable for applications prioritizing corrosion resistance and formability over maximum strength.
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 beryllium is a precipitation-hardenable copper alloy (typically 2% beryllium by weight) offering exceptional strength-to-weight ratio, high electrical and thermal conductivity, and excellent fatigue resistance, used primarily in aerospace, defense, and high-reliability electronics applications. The H-series tempers (H01, H02, H04) represent increasing levels of cold work hardening for enhanced strength, while TF00 is the annealed condition providing maximum ductility and machinability.
Copper-beryllium alloy in H01 (hard/strain-hardened) condition, a precipitation-hardenable copper alloy containing 1.6-2.0% beryllium used in aerospace and defense applications requiring high strength-to-weight ratio, excellent electrical and thermal conductivity, and non-magnetic properties. The H01 temper provides maximum strength through strain hardening with controlled elongation, suitable for demanding applications including springs, connectors, and precision components operating at elevated temperatures.
Copper beryllium (CuBe) H02 is a precipitation-hardenable copper alloy in half-hard temper condition, offering high strength and excellent electrical and thermal conductivity for aerospace and defense applications requiring beryllium's unique combination of properties. The H02 temper provides intermediate strength levels between annealed and fully hard conditions, making it suitable for strip applications where moderate strength, ductility, and workability must be balanced in components such as electrical contacts, springs, and precision fasteners.
Copper Beryllium H04 is a precipitation-hardenable copper-beryllium alloy in a strain-hardened condition offering high strength and excellent electrical and thermal conductivity for critical aerospace and defense applications. The H04 temper (half-hard) provides intermediate strength levels with controlled elongation suitable for strip applications requiring moderate forming capability while maintaining superior fatigue resistance and non-magnetic properties.
Copper-beryllium alloy (typically 1.6-2.0% Be) used in aerospace and defense applications requiring high strength-to-weight ratio and excellent electrical conductivity; TF00 temper is the fully annealed condition providing maximum ductility and workability with yield strength around 70-90 MPa and elongation typically exceeding 40%, suitable for forming operations before final hardening.
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 martensitic precipitation-hardening stainless steel strengthened by copper and aluminum additions, providing high yield strength (typically 1310–1655 MPa depending on temper) and good corrosion resistance for aerospace fasteners, turbine components, and structural applications requiring elevated temperature performance to approximately 480°C. The H-series tempers (H900–H1150) represent increasing strength levels achieved through controlled aging, with H1150 offering maximum hardness and strength at the cost of reduced ductility, while Solution Treated condition provides baseline ductility for forming operations.
Custom 450 Stainless Steel is a precipitation-hardening martensitic stainless steel (chromium-based with copper and niobium alloying) designed for high-strength aerospace applications requiring corrosion resistance and elevated temperature capability. The H1000 condition represents the highest strength level achievable through precipitation hardening, delivering yield strengths approximately 1700+ MPa with controlled elongation, suitable for critical fasteners and structural components in military and commercial aircraft.
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 stainless steel is a martensitic stainless steel with approximately 13% chromium and 1% molybdenum, designed for high-strength aerospace and turbine engine applications requiring elevated temperature strength and corrosion resistance. The H1100 condition (hardened and tempered to approximately 1100°F) provides tensile strengths typically in the 180–200 ksi range with moderate elongation, balancing hardness and fracture toughness for critical rotating components.
Custom 450 stainless steel is a martensitic stainless steel (chromium-based with controlled carbon and molybdenum additions) used primarily in aerospace applications requiring high strength and corrosion resistance at elevated temperatures. The H1150 condition is a hardened and tempered state providing ultimate tensile strength approximately 1,150 ksi (7,930 MPa) with moderate ductility, suitable for critical fasteners and structural components in gas turbine engines and high-performance aircraft systems.
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 precipitation-hardened to high strength levels, offering excellent corrosion resistance in moderately aggressive environments and suitability for aerospace structural components and fasteners. The H950 condition provides maximum strength through precipitation hardening, delivering yield strength in the 1,520–1,655 MPa range with controlled elongation for critical applications requiring high strength-to-weight ratios and fatigue resistance.
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-hardened martensitic stainless steel (17-4 PH derivative) designed for high-strength aerospace and defense applications requiring excellent corrosion resistance combined with tensile strengths exceeding 1,400 MPa. The H1000 and H950 conditions represent peak-aged tempers providing optimal strength and elastic property stability at operating temperatures up to approximately 480°C.
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 is a precipitation-hardenable martensitic stainless steel (13% Cr, 8% Ni, 2% Mo, 1% Al, Ti) designed for high-strength aerospace applications requiring excellent fatigue resistance and corrosion resistance in moderately aggressive environments. The H1000 and H950 conditions achieve yield strengths of 1380 MPa and 1310 MPa respectively through controlled precipitation hardening, with maintained toughness at cryogenic temperatures suitable for rocket motor casings and fasteners.
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 is a sand-cast aluminum-copper alloy (2xx series) designed for high-strength aerospace applications requiring good castability and moderate elevated-temperature performance. The T6 temper (solution heat-treated and artificially aged) provides tensile strengths in the 240–280 MPa range with improved dimensional stability compared to as-cast condition, making it suitable for engine blocks, compressor housings, and structural castings in aircraft powerplants.
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.
EZ33A is a magnesium casting alloy containing zinc and rare-earth elements (primarily cerium) that provides elevated-temperature strength and creep resistance for aerospace engine components; the T5 temper (artificially aged after casting) delivers improved yield and tensile strength while maintaining reasonable ductility for applications up to approximately 300°C.
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-based superalloy containing cobalt, chromium, and tungsten, designed for high-temperature applications requiring excellent creep resistance and oxidation resistance up to approximately 2100°F (1149°C). Primary applications include gas turbine engines, combustors, and aerospace heat exchangers; the material offers superior strength retention and fatigue performance in oxidizing environments at elevated temperatures.
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.
HAYNES®230 is a nickel-chromium-tungsten superalloy designed for high-temperature structural applications requiring oxidation resistance and creep strength to approximately 2250°F (1230°C). The 2250 Anneal condition provides stress-relieved properties suitable for aerospace applications including turbine shrouds, combustor liners, and other elevated-temperature engine components where moderate strength and excellent corrosion/oxidation resistance are required.
HAYNES HR-120 is a nickel-based superalloy with cobalt and chromium additions designed for high-temperature structural applications in aerospace engines and gas turbines. The annealed condition provides optimal ductility and machinability while maintaining excellent creep resistance and oxidation protection up to approximately 1200°C.
HAYNES HR-120 is a nickel-iron-chromium superalloy designed for high-temperature structural applications requiring intermediate strength and excellent oxidation resistance up to approximately 1200°F (649°C). The annealed condition provides optimized ductility and toughness for forming and fabrication while maintaining adequate yield strength, making it suitable for aerospace engine components, ducting, and thermal protection systems per AMS 5916.
HS 188 is a cobalt-based superalloy containing tungsten, chromium, and nickel, designed for high-temperature structural applications in gas turbines, aerospace engines, and industrial furnaces where service temperatures exceed 1000°C. The alloy offers excellent creep resistance, oxidation resistance, and thermal fatigue performance, with the Solution Treated condition providing optimal balance of strength and ductility for elevated-temperature service.
HS 188 is a cobalt-based superalloy with tungsten and chromium additions, designed for high-temperature structural applications in gas turbines and aerospace engines requiring sustained performance above 1000°C. Solution-treated condition provides optimal balance of strength and ductility through controlled heat treatment, suitable for sheet applications where creep resistance and thermal fatigue resistance are critical performance requirements.
Inconel 600 is a nickel-chromium austenitic superalloy containing iron, molybdenum, and titanium, designed for high-temperature applications in aerospace, chemical processing, and nuclear industries up to 1200°C. The alloy provides excellent corrosion and oxidation resistance, high strength retention at elevated temperatures, and superior fatigue performance, with strength levels varying by temper condition from annealed (lowest strength, highest ductility) through cold-worked variants (progressively higher strength via strain-hardening).