103,183 materials
A357.0 is a cast aluminum-silicon alloy (Al-7Si-0.6Mg) designed for aerospace and high-performance applications requiring good castability and elevated temperature strength. The T6 temper (solution heat-treated and artificially aged) provides enhanced mechanical properties with improved strength retention at service temperatures up to approximately 150°C.
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.
ABS is a tough, amorphous thermoplastic copolymer combining acrylonitrile, butadiene, and styrene monomers, known for its balance of rigidity, impact resistance, and processability. It is widely used in consumer products, automotive components, and industrial housings where good dimensional stability, chemical resistance, and aesthetic finish are required. Engineers select ABS over more brittle plastics (like HIPS) when impact toughness is critical, and over engineering thermoplastics (like polycarbonate or nylon) when cost and ease of injection molding are priorities.
AerMet 100 is a high-strength, low-alloy steel (Fe-Ni-Co-Mo-Cr) used in aerospace landing gear, fasteners, and structural components requiring ultrahigh strength with good fracture toughness at ambient and cryogenic temperatures. The STA (Solution Treated and Aged) condition provides yield strengths exceeding 1700 MPa with enhanced toughness through controlled precipitation hardening, making it suitable for damage-tolerant design in critical aerospace applications.
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.
AF1410 steel is a low-alloy, case-hardening steel containing nickel, chromium, and molybdenum, specified under AMS 6527 for aerospace bearing and structural applications requiring high compressive strength and fatigue resistance. Condition "a" represents the normalized and tempered state, providing balanced yield and ultimate strengths suitable for bearing races and highly stressed components in aircraft landing gear and power transmission systems.
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 1025 is a low-carbon steel (0.22–0.28% C) with manganese content, used in structural applications, fasteners, and automotive components requiring moderate strength and good machinability. The annealed condition provides maximum ductility and minimum hardness (approximately 135–180 HV), making it suitable for cold-forming operations while sacrificing strength compared to work-hardened or normalized conditions.
AISI 1025 is a plain carbon steel (0.22-0.28% C) normalized to provide uniform microstructure and improved machinability through stress relief heat treatment. This condition offers moderate strength with good ductility and toughness, suitable for structural components and tubing applications requiring consistent properties without high hardness.
AISI 301 is an austenitic chromium-nickel stainless steel (17-18% Cr, 6-8% Ni) with high work-hardening capacity, used for springs, fasteners, and aerospace components requiring excellent corrosion resistance and moderate strength. Cold-working tempers (1/4 Hard through Full Hard) provide yield strengths from ~200 to 1,200 MPa with retained ductility, while Annealed condition offers lower strength for formability and subsequent hardening.
AISI 301 is an austenitic chromium-nickel stainless steel (17-18% Cr, 6-8% Ni) widely used in aerospace fasteners, springs, and high-strength sheet applications requiring excellent corrosion resistance and work-hardening capability. The 1/2 Hard temper condition provides intermediate strength through controlled cold-working, balancing formability with yield strength (0.2% offset) suitable for applications requiring both processing flexibility and structural performance at cryogenic through moderate elevated temperatures.
AISI 301 is an austenitic chromium-nickel stainless steel (17-18% Cr, 6-8% Ni) with excellent corrosion resistance and work-hardening characteristics, used extensively in aerospace fasteners, springs, and vibration-damping applications. The 1/4 hard condition provides intermediate strength through controlled cold-working, balancing improved yield strength and fatigue performance with retained formability for sheet and strip forms per AMS 5517.
AISI 301 is an austenitic stainless steel (Fe-Cr-Ni) with moderate chromium and nickel content that provides good corrosion resistance and work-hardenability; the 3/4 Hard temper condition delivers intermediate strength through cold-working, suitable for spring applications, fasteners, and structural components in aerospace and industrial environments requiring corrosion resistance with enhanced yield and tensile strength.
AISI 301 is an austenitic chromium-nickel stainless steel (17-18% Cr, 6-8% Ni) widely used in aerospace, automotive, and industrial applications requiring moderate strength with excellent corrosion resistance and formability. The annealed condition provides maximum ductility and workability with yield strength around 170-210 MPa, making it suitable for complex formed components and applications requiring cold-working capability.
AISI 301 full hard is a chromium-nickel austenitic stainless steel (17-18% Cr, 6-8% Ni) in a heavily cold-worked condition that achieves tensile strengths of approximately 185-205 ksi, providing high strength and moderate corrosion resistance for spring applications, fasteners, and structural components in aerospace and industrial environments. Full hard condition offers maximum strength through strain hardening with reduced ductility, suitable for applications requiring high yield and ultimate strength rather than formability.
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.
Alclad 2524-T3 is a clad aluminum-copper-magnesium alloy in solution heat-treated and cold-worked condition, providing high strength with improved fatigue resistance and corrosion protection via the pure aluminum cladding layer. Primary applications include aircraft fuselage skin and pressurized structures requiring damage tolerance and sustained stress capability at moderate temperatures.
Alclad 2524-T3 is a copper-aluminum-magnesium alloy with a pure aluminum corrosion-protective cladding, used primarily in aircraft fuselage and wing structures requiring high fatigue resistance and damage tolerance. The T3 temper (solution heat-treated and cold-worked) provides yield strength around 41 ksi with excellent fatigue performance and moderate corrosion resistance, suitable for high-cycle applications in the -55°C to 120°C temperature range.
Alumina (Al₂O₃) is a polycrystalline ceramic composed of aluminum and oxygen, widely recognized as one of the most versatile and commercially mature advanced ceramics. It is extensively used in applications ranging from refractory linings in high-temperature furnaces and electrical insulators to precision cutting tools, grinding media, and biomedical implants, where its combination of hardness, thermal stability, and chemical inertness provides significant advantages over metals and polymers. Engineers select alumina when they need a material that maintains strength at elevated temperatures, resists corrosion and wear, provides electrical insulation, or requires biocompatibility—making it a go-to choice across thermal processing, electronics, aerospace, and medical device industries.
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 is a precipitation-hardenable aluminum alloy containing magnesium and silicon as primary strengthening elements, with minor copper addition for further hardening. It is one of the most widely used structural aluminum alloys in industry, valued for its excellent combination of formability, weldability, and corrosion resistance—making it the preferred choice over higher-strength but less weldable alloys (like 7075) when joint integrity and ease of fabrication are critical. Applications range from structural frames and pressure vessels to marine components and consumer products, where moderate strength, good machinability, and reliable performance in outdoor environments justify its selection.
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.
Aluminum Nitride (AlN) is a wide-bandgap semiconductor ceramic compound combining aluminum and nitrogen in a 1:1 stoichiometry, belonging to the III-V nitride family alongside GaN and InN. It is primarily used in high-power electronics and optoelectronics where excellent thermal conductivity combined with electrical insulation is critical—such as in LED substrates, power device packaging, and RF/microwave components for telecommunications and defense applications. Engineers select AlN over alternatives like alumina when thermal management of semiconductor junctions is paramount, and over GaN when electrical isolation rather than conductivity is required.
AM100A is a magnesium-aluminum alloy (Mg-10Al-0.1Mn) used in aerospace applications requiring moderate strength and good castability, with T6 heat treatment (solution treated and artificially aged) providing improved strength and hardness suitable for elevated temperature service up to approximately 150°C.
AM100A T6 is a magnesium casting alloy (Mg-Al-rare earth) in the T6 heat-treated condition (solution treated and artificially aged) offering high strength and elevated-temperature capability up to ~150°C, used primarily in aerospace engine components and transmission housings. The T6 temper provides improved yield strength and tensile properties compared to as-cast condition while maintaining castability in investment and permanent mold processes.
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-350 is a precipitation-hardened martensitic stainless steel (17% Cr, 4.7% Ni, 2.7% Mo, with aluminum and titanium for strengthening) used in aerospace fasteners, bearings, and high-strength structural components requiring corrosion resistance up to approximately 600°F. The SCT 850 condition (solution heat-treated and aged at 850°F) provides yield strengths around 200 ksi with good toughness and fatigue resistance, balancing strength with ductility for critical bearing and fastening applications.
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 is a martensitic stainless steel (17Cr-4.3Ni-2.8Mo-1.3Ti) used in aerospace applications requiring high strength and corrosion resistance at elevated temperatures, with SCT 1000 condition (solution heat-treated and aged at 1000°F) providing yield strengths in the 170–180 ksi range with moderate ductility for demanding structural and fastener applications.
AM-355 stainless steel is a precipitation-hardenable martensitic stainless steel (17% Cr, 4.3% Ni, 2.6% Mo) used in aerospace fasteners and structural components requiring high strength and corrosion resistance at elevated temperatures. The T1000 condition is aged to approximately 1000°F (538°C), providing ultimate tensile strengths in the range of 180–210 ksi with good fracture toughness and fatigue resistance for service to 600°F (316°C).
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.
AZ31B is a wrought magnesium alloy containing aluminum and zinc, commonly used in aerospace structural components, automotive parts, and portable equipment where light weight is critical. The O (annealed) temper provides optimal ductility and formability with reduced strength compared to work-hardened conditions, making it suitable for applications requiring complex forming operations and moderate loads at temperatures up to approximately 150°C.
AZ31B-H24 is a wrought magnesium alloy containing aluminum and zinc, strain-hardened to provide improved strength and rigidity for structural applications in aerospace and automotive industries. The H24 temper delivers moderate strength with adequate ductility and formability, making it suitable for sheet and plate applications requiring balanced mechanical properties and corrosion resistance in non-severe environments.
AZ31B is a wrought magnesium alloy containing aluminum and zinc, widely used in aerospace and automotive applications where light weight and moderate strength are required. The H26 temper (strain-hardened and partially annealed) provides intermediate strength and ductility suitable for sheet and plate applications, with good formability and improved corrosion resistance compared to softer tempers.
AZ31B is a wrought magnesium alloy containing aluminum and zinc, widely used in aerospace, automotive, and defense applications where lightweight structures are required. The alloy offers moderate strength (yield ~160-275 MPa depending on temper), good corrosion resistance, and low density (~1.8 g/cm³), with F (as-fabricated), O (annealed), and H24 (strain-hardened) tempers providing increasingly higher strength at the expense of ductility.
AZ31B is a wrought magnesium alloy containing aluminum and zinc providing moderate strength with good corrosion resistance, widely used in aerospace and automotive applications where weight reduction is critical. The F (as-fabricated) temper represents the material in its as-extruded or as-forged condition without heat treatment, offering consistent properties suitable for structural components requiring ductility and formability over peak strength.
AZ61A is a magnesium alloy containing aluminum and zinc alloying elements, used primarily in aerospace and structural applications requiring lightweight components with moderate strength. The F temper represents the as-fabricated condition without heat treatment, providing baseline mechanical properties suitable for forging and casting operations.
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.
AZ91C is a magnesium-aluminum-zinc casting alloy heat-treated to T6 condition (solution heat-treated and artificially aged), providing improved strength and creep resistance for aerospace and structural applications requiring lightweight castings. T6 temper delivers typical yield strengths of 160–170 MPa with moderate elongation (3–5%), suitable for service up to approximately 150°C, commonly produced via investment and sand casting per AMS 4437 and AMS 4452.
AZ91E is a high-strength magnesium alloy containing aluminum and zinc alloying elements, widely used in aerospace and automotive applications where weight reduction is critical. The T6 temper (solution heat-treated and artificially aged) provides improved strength and dimensional stability, with typical density around 1.81 g/cm³ and Young's modulus approximately 45 GPa, making it suitable for moderate-temperature structural components operating up to approximately 150°C.
AZ91E is a cast magnesium alloy containing aluminum and zinc that is solution heat-treated and artificially aged to the T6 condition, providing improved strength and hardness compared to as-cast material. This alloy is used primarily in aerospace and automotive applications where lightweight castings with moderate strength and acceptable corrosion resistance are required, with typical service limited to temperatures below 120°C.
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.
Beta-tricalcium phosphate (β-TCP) is a calcium phosphate ceramic composed of calcium, phosphorus, and oxygen in a 3:2 stoichiometric ratio; it is the thermodynamically stable form of tricalcium phosphate at physiological temperatures. It is widely used in orthopedic and dental applications as a biocompatible bone substitute and scaffold material, where it provides osteoconductive properties and gradually resorbs as new bone forms, making it preferable to non-resorbable ceramics for applications requiring tissue integration. β-TCP is also employed in maxillofacial reconstruction, periodontal treatments, and as a component in composite bone cements; its combination of bioactivity and resorption kinetics offers distinct advantages over hydroxyapatite (which resorbs too slowly) and α-TCP (which sets too rapidly for clinical handling).
Bioglass 45S5 is a silicate-based bioactive ceramic composed of silica, sodium oxide, calcium oxide, and phosphorus oxide that bonds directly to living bone and soft tissue through formation of a hydroxyapatite layer when in contact with biological fluids. It is widely used in orthopedic and dental applications—including bone void fillers, dental implants, periodontal regeneration, and maxillofacial reconstruction—because it promotes osteogenic (bone-forming) response and integrates with native tissue rather than remaining inert like traditional ceramics. Engineers select Bioglass 45S5 when biological integration and resorption are design goals, distinguishing it from inert alumina or zirconia ceramics that encapsulate rather than bond with bone.
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.