10,375 materials
7475 aluminum is a high-strength Al-Zn-Mg-Cu alloy designed for critical aerospace structural applications requiring superior fatigue resistance and stress-corrosion cracking resistance compared to 7075. This alloy operates effectively up to ~150°C and is specified for highly stressed aircraft fuselage and wing components where damage tolerance and long-term durability in service are paramount.
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.
7475-T761 is a high-strength aluminum-zinc-magnesium-copper alloy reinforced with aramid fibers in sheet laminate form, delivering enhanced damage tolerance and fatigue resistance for aerospace structural applications. The T761 temper (overaged condition) provides controlled strength levels with improved fracture toughness relative to peak-hardness tempers, making it suitable for damage-critical aircraft components operating at intermediate temperatures.
9Ni-4Co-0.20C is a high-strength, low-alloy steel designed for cryogenic applications, combining nickel and cobalt additions to maintain toughness at extremely low temperatures while the moderate carbon content provides strength. The Q&T (quenched and tempered) condition delivers yield strengths typically 1,380–1,550 MPa with excellent fracture toughness and impact resistance down to liquid helium temperatures, making it suitable for aerospace propellant tankage and cryogenic pressure vessels.
9Ni-4Co-0.20C steel is a high-strength, low-alloy steel containing 9% nickel and 4% cobalt designed for cryogenic and ultra-high-strength aerospace applications, with the Q&T (quenched and tempered) condition providing yield strengths in the 1,400–1,650 MPa range and excellent toughness at temperatures down to -196°C. Specified per AMS 6523 for use in missile motor cases, rocket bodies, and other critical structural components requiring superior strength-to-weight ratios and fracture toughness in extreme environments.
# 9Ni-4Co-0.30C Steel Ultra-high-strength nickel-cobalt maraging steel used in aerospace applications requiring exceptional yield strengths (typically 1,379–1,586 MPa) and fracture toughness at cryogenic temperatures. Q&T (quenched and tempered) condition provides controlled hardness and ductility balance suitable for critical load-bearing components in rocket motors, pressure vessels, and landing gear systems.
9Ni-4Co-0.30C steel in Q&T (quenched and tempered) condition is a high-strength, low-alloy steel designed for aerospace structural applications requiring yield strengths in the 1,380–1,720 MPa range with good fracture toughness and fatigue resistance. This nickel-cobalt-carbon composition is specified in AMS 6524a and AMS 6526 for critical fasteners, forgings, and structural components where a combination of high bearing strength, compressive yield strength, and controlled ductility is essential for damage-tolerant design.
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.
A-286 is an austenitic iron-nickel-cobalt superalloy strengthened by precipitation hardening, designed for jet engine components and high-temperature structural applications requiring sustained service to 1300°F (704°C). The alloy combines excellent creep resistance, fatigue strength, and corrosion resistance with moderate density, making it suitable for turbine discs, fasteners, and casings in aerospace propulsion systems.
A-286 is an iron-nickel-cobalt superalloy (Fe-Ni-Co base with Ti, Al, Mo, V, Cr) solution heat-treated and aged (STA) to provide sustained strength up to ~700°C, offering yield strengths of 170–200 ksi with good fatigue resistance and oxidation protection for jet engine components, fasteners, and high-temperature structural applications. The STA condition delivers optimal tensile properties and bearing strength characteristics while maintaining ductility suitable for aerospace fastening and engine hardware applications.
A356.0 is an aluminum-silicon casting alloy (Al-7Si-0.3Mg) used primarily in aerospace and automotive applications requiring good castability and moderate strength at elevated temperatures. T6 and T6P tempers provide solution heat treatment and artificial aging, with T6P offering improved properties through controlled precipitation hardening, suitable for components operating up to approximately 250°C.
A356.0 is an aluminum-silicon casting alloy (7–8% Si) commonly used in aerospace and automotive applications where lightweight components with good castability and moderate strength are required. The T6 temper (solution heat-treated and artificially aged) provides enhanced strength and hardness suitable for structural and engine components operating at elevated temperatures up to approximately 150°C.
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.
Aramid fiber-reinforced plastic (AFRP) combining DuPont Kevlar 49 aramid fibers in a unidirectional 0° orientation with epoxy matrix, processed as prepreg and cured at 120°C. This material is engineered for applications demanding high specific strength, excellent impact resistance, and low density in a fiber-dominated, load-aligned configuration. Industries rely on it for ballistic protection, aerospace structures, and high-performance sporting goods where weight savings and damage tolerance outweigh the cost premium relative to glass or carbon fiber composites.
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-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.
AS4/3501-6 is a unidirectional carbon fiber reinforced epoxy prepreg system combining Hexcel's AS4 carbon fibers (12K tow) with 3501-6 epoxy matrix, designed for autoclave processing at 175°C. This material is a industry-standard choice for aerospace primary structures, defense applications, and high-performance composite parts where fiber alignment in a single direction is critical for load-bearing efficiency. Engineers select it over multi-directional laminates when maximum stiffness and strength along the primary load axis outweigh omnidirectional property needs, and its well-documented MIL-HDBK-17 qualification makes it a preferred baseline for structural certification and damage-tolerance analysis.
AS4/3502 is a carbon fiber reinforced epoxy composite in plain weave fabric form, combining Hexcel's AS4 carbon fiber (3K tow) with 3502 epoxy matrix, cured via autoclave prepreg processing. This material is a workhorse in aerospace and defense, selected for primary and secondary structures where balanced in-plane properties, damage tolerance, and manufacturing repeatability are required. The plain weave architecture (versus unidirectional or twill) provides good transverse strength and impact resistance with acceptable longitudinal performance, making it ideal when loads aren't purely directional or when lay-up flexibility and ease of handling outweigh ultimate performance density.
AS4 is a continuous carbon fiber produced by Hexcel, widely recognized as an industry-standard intermediate-modulus fiber for polymer matrix composites. It is the workhorse reinforcement in aerospace structures, wind turbine blades, and high-performance sporting goods, chosen for its balance of stiffness, strength, and cost-effectiveness compared to higher-modulus alternatives like IM7 or HS40. Engineers select AS4 when moderate-to-high structural performance is required without the weight or cost penalty of premium fibers, making it the most common choice for primary aircraft structures and demanding composite applications.
AS4/PEEK (APC-2) is a thermoplastic composite combining AS4 carbon fibers with polyetheretherketone (PEEK) resin, engineered for high-performance applications requiring both strength and thermal stability. This material is widely used in aerospace, automotive, and industrial sectors where components must withstand elevated temperatures, aggressive chemical environments, and demanding mechanical loads while maintaining processability through heat forming. AS4/PEEK is valued over traditional thermoset composites for its ability to be re-melted and reshaped, faster manufacturing cycles, and superior impact tolerance, making it particularly attractive for cost-sensitive production and repair scenarios.
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.