10,375 materials
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.
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.
Cadmium Telluride (CdTe) is a binary II-VI semiconductor compound with a direct bandgap in the near-infrared region, making it a primary material for optoelectronic and radiation detection applications. The material is most widely deployed in thin-film photovoltaic (solar cell) technology, where it offers high theoretical conversion efficiency and manufactures at lower cost than silicon alternatives; CdTe is also valued in gamma-ray and X-ray detectors for medical imaging, security screening, and nuclear monitoring due to its strong photon absorption and good charge transport properties. Engineers select CdTe when bandgap energy (~1.44 eV) and radiation stopping power are critical, though environmental and health regulations around cadmium toxicity constrain its adoption in some markets and drive ongoing development of cadmium-free alternatives.
AS4/3501-6 quasi-isotropic CFRP is a carbon fiber reinforced epoxy composite with balanced fiber orientation (0°, ±45°, and 90°) designed to provide uniform stiffness and strength in multiple load directions. The layup consists of eight plies of Hexcel AS4 carbon fiber in a 3501-6 epoxy matrix, processed via autoclave prepreg curing, creating a material suitable for applications requiring multidirectional load resistance without a dominant stress direction. This quasi-isotropic architecture makes it a go-to choice over unidirectional or angle-ply laminates when loading conditions are complex or unpredictable, though engineers sacrifice peak performance in any single direction compared to tailored layups.
CFRP IM7/8552 is an autoclave-processed carbon fiber reinforced polymer composite combining Hexcel's high-strength IM7 carbon fibers with a toughened 8552 epoxy matrix, engineered as a unidirectional lamina for primary load-bearing applications. This material system is widely specified in aerospace structures—including aircraft fuselages, wings, and control surfaces—and increasingly adopted in high-performance sporting goods and industrial equipment where weight reduction, damage tolerance, and thermal stability are critical. The IM7/8552 combination is valued over competing systems for its balance of fiber stiffness, matrix fracture resistance, and processing robustness in demanding environments.
IM7/977-3 is a high-performance carbon fiber reinforced polymer (CFRP) composite featuring IM7 intermediate-modulus carbon fibers in a 977-3 toughened epoxy matrix, engineered for unidirectional fiber alignment to maximize strength and stiffness along the fiber direction. This system is widely used in aerospace primary structures, wind turbine blades, and high-performance sporting equipment where the combination of low weight, high fiber-direction strength, and superior matrix toughness (977-3 is Hexcel's damage-resistant formulation) provides advantages over brittle conventional epoxy systems. Engineers select IM7/977-3 when damage tolerance, impact resistance, and hot-wet performance are critical alongside weight savings—particularly in military aircraft, commercial jetliners, and harsh operating environments where intermediate fiber modulus balances stiffness gains with superior fiber toughness compared to high-modulus alternatives.
CFRP M55J/RS-3C is an ultra-high modulus carbon fiber reinforced polymer combining Toray's M55J carbon fiber with TenCate's cyanate ester matrix, processed via autoclave prepreg for 0° unidirectional layup. This material targets aerospace and space structures where exceptional stiffness-to-weight ratio and dimensional stability under thermal cycling are critical performance drivers. The combination of ultra-high modulus fiber with a high-temperature thermoset matrix makes it suitable for demanding applications that require minimal deflection, superior creep resistance, and reliable performance in extended temperature environments—distinguishing it from general-purpose epoxy composites used in less stringent load cases.
T300/934 is a unidirectional carbon fiber composite combining Toray's widely-used T300 carbon fibers with Fiberite's 934 epoxy matrix, produced via autoclave prepreg processing. This material is a workhorse in aerospace and defense applications where moderate-temperature performance, reliable processability, and cost-effectiveness matter more than cutting-edge performance—it remains a baseline choice for primary structures, control surfaces, and components where damage tolerance and manufacturing repeatability are critical. Engineers typically select T300/934 over newer fiber systems when specifications allow, because the extensive historical data, mature supply chain, and well-understood failure modes reduce design risk and certification burden.
CFRP T700/2510 is a unidirectional carbon fiber reinforced polymer composite combining Toray's T700S carbon fibers with a 2510 epoxy matrix, processed as an out-of-autoclave (OOA) prepreg system that cures at moderate temperature without requiring autoclave equipment. This material is widely used in aerospace, defense, and performance-critical structures where weight savings, stiffness, and damage tolerance are essential—particularly in secondary structures, control surfaces, and components where the out-of-autoclave processing reduces manufacturing cost and facility overhead compared to autoclave-dependent systems. The unidirectional fiber orientation makes it ideal for applications requiring directional strength optimization, and the 2510 epoxy matrix offers good toughness and environmental resistance, making it a practical choice for engineers balancing performance demands with manufacturing simplicity.
CFRP T800H/3900-2 is a high-performance unidirectional carbon fiber reinforced polymer combining Toray's T800H intermediate-modulus carbon fiber with a toughened epoxy matrix, processed via autoclave prepreg for consistent fiber alignment and minimal voids. It is used in aerospace primary structures (wings, fuselages), high-speed rotorcraft, and demanding defense applications where the combination of stiffness, strength, and impact resistance enables weight reduction without sacrificing damage tolerance. Engineers select this material over standard T700 or IM7 systems when the superior fiber properties and toughened matrix justify the cost—particularly in load-critical components that experience transverse loads, vibration, or require excellent fatigue performance.
AS4/PEEK (APC-2) is a carbon-fiber-reinforced thermoplastic composite combining Hexcel AS4 carbon fibers with Victrex PEEK matrix resin, processed via thermoplastic stamp forming or automated fiber placement (AFP) at 390°C. This material class bridges aerospace-grade performance with manufacturing flexibility: unlike thermoset composites, it can be melted and reformed, enabling rapid consolidation, rework, and complex near-net-shape production without lengthy cure cycles. Industries from commercial aerospace (fuselage components, interior panels) to high-performance automotive and oil & gas drilling applications adopt it when damage tolerance, temperature resistance, and production speed outweigh the cost premium of thermoset alternatives.
Carbon fiber-reinforced thermoplastic composite with a polyphenylene sulfide (PPS) matrix, manufactured via press consolidation at 320°C. This unidirectional 0° layup combines T300 carbon fibers at 50% volume fraction with an inherently flame-resistant, chemical-stable thermoplastic resin. CFRTP/PPS is chosen for demanding aerospace and automotive applications where high stiffness, low density, chemical resistance, and elevated temperature performance are required without the processing constraints of thermoset epoxies—the thermoplastic matrix enables rapid consolidation, potential re-molding, and improved impact tolerance compared to brittle thermoset alternatives.
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.
Nextel 720/Aluminosilicate is a ceramic matrix composite (CMC) combining alumina-silica fibers in an aluminosilicate matrix, processed via slurry infiltration and high-temperature sintering. This oxide/oxide system is used in aerospace thermal protection, industrial furnace components, and high-temperature engine applications where oxidation resistance and damage tolerance are critical. Unlike brittle monolithic ceramics, this CMC retains some load-carrying capacity after matrix cracking, making it suitable for cyclic thermal and mechanical loading in extreme environments.
SiC/SiC ceramic matrix composite (CMC) reinforced with Hi-Nicalon S silicon carbide fibers in a dense SiC matrix, produced via chemical vapor infiltration (CVI) combined with polymer infiltration and pyrolysis (PIP). This cross-ply laminate architecture ([0/90]₂) delivers excellent damage tolerance and thermal stability compared to monolithic ceramics. Used in extreme-temperature structural applications where thermal shock resistance, light weight, and retention of strength at elevated temperatures are critical, particularly in aerospace propulsion (engine hot sections) and next-generation power generation systems; offers a significant advantage over superalloy alternatives by operating at higher temperatures while maintaining lower density.
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.