214 materials
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-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.
Inconel 600 is a nickel-chromium austenitic superalloy with excellent oxidation and corrosion resistance up to 1100°C, used in aerospace, chemical processing, and nuclear applications. The annealed condition provides optimal ductility and corrosion resistance with reduced yield strength compared to cold-worked tempers, making it suitable for applications requiring high toughness and resistance to intergranular corrosion in service temperatures up to approximately 900°C.
Inconel 625 offers outstanding corrosion and oxidation resistance, with excellent weldability. Used in marine, chemical, and aerospace applications where extreme corrosion resistance at elevated temperatures is needed.
Inconel 718 is the dominant nickel superalloy for gas turbine engine disks and casings, accounting for over 50% of all superalloy production. Excellent high-temperature strength up to ~650°C and good weldability.
Inconel 718 produced via selective laser melting (SLM) is a nickel-based superalloy manufactured through additive manufacturing, combining the exceptional high-temperature strength and corrosion resistance of conventional Inconel 718 with the design freedom and complexity capabilities of metal 3D printing. This material is increasingly adopted in aerospace, power generation, and oil & gas industries where engineers need intricate cooling channels, lightweight geometries, or rapid prototyping of high-performance components that would be difficult or impossible to machine from wrought stock. SLM Inconel 718 is valued for its ability to maintain structural integrity in aggressive thermal and corrosive environments while enabling near-net-shape manufacturing, though careful process control and post-processing (such as heat treatment) are critical to achieve consistent mechanical properties and eliminate porosity inherent to the additive process.
Inconel 718 is a nickel-based superalloy in wrought form that has been precipitation-hardened through aging heat treatment to achieve high strength at elevated temperatures. It is widely used in aerospace, power generation, and oil & gas industries where components must withstand extreme thermal and mechanical stresses while maintaining structural integrity. Engineers select this alloy for critical applications requiring excellent creep resistance, fatigue strength, and corrosion resistance in operating environments that would cause conventional steels and aluminum alloys to fail.
Inconel X-750 is a nickel-based superalloy strengthened by gamma-prime precipitation, designed for high-temperature aerospace applications requiring sustained strength to approximately 1300°F (704°C). The alloy exhibits excellent creep resistance, fatigue strength, and corrosion resistance in jet engine components, gas turbine blades, and fasteners, with the Equalized and Aged temper providing optimal strength development through controlled solution treatment and precipitation hardening.
MP159 is a cobalt-based superalloy containing nickel, chromium, and molybdenum, designed for high-temperature aerospace applications requiring excellent fatigue strength and corrosion resistance up to approximately 700°C. The STA (solution-treated and aged) cold-drawn condition provides enhanced tensile strength and fatigue performance through precipitation hardening, making it suitable for engine components, fasteners, and structural elements in military aircraft and gas turbine applications.
MP159 is a nickel-cobalt-base superalloy containing chromium, molybdenum, and tungsten, designed for high-strength fastener and spring applications in aerospace engines and structures. The STA (Solution Treated and Aged) cold-drawn condition provides superior tensile strength and yield strength with controlled ductility, maintaining excellent fatigue resistance and stress-rupture performance at elevated temperatures up to approximately 700°C.
MP35N is a cobalt-nickel-chromium-molybdenum superalloy designed for high-strength, corrosion-resistant applications requiring excellent fatigue resistance and performance in cryogenic to moderate elevated temperatures. Primarily used in aerospace fasteners, springs, and medical implants, MP35N offers yield strengths exceeding 1,000 MPa with superior resistance to stress-corrosion cracking and seawater corrosion compared to conventional stainless steels.
MP35N STA Cold Drawn is a cobalt-nickel-chromium-molybdenum superalloy in solution-treated and aged condition with cold-drawing, used primarily in high-temperature aerospace fasteners and springs requiring exceptional strength retention to 600°C and excellent corrosion resistance in oxidizing and seawater environments. The cold-drawn condition provides increased yield and tensile strength with controlled ductility, making it suitable for applications demanding both mechanical performance and fatigue resistance at elevated temperatures.
Ni-Mn-Ga is a ferromagnetic shape memory alloy (FSMA) that combines magnetic properties with the ability to recover large strains when heated or exposed to magnetic fields, enabling actuation without traditional electrical current. The alloy is employed in niche applications requiring compact, silent, responsive actuators—particularly in aerospace, automotive adaptive systems, and biomedical devices where conventional electromagnetic or piezoelectric solutions are impractical. Engineers choose this material when shape recovery must be triggered magnetically, when noise and power efficiency are critical, or when space constraints demand high strain output from minimal volume, though availability, cost, and brittleness relative to conventional shape memory alloys (like NiTi) currently limit adoption to specialized, performance-critical roles.
NiTiCu is a copper-modified nickel-titanium shape memory alloy that combines the reversible phase transformation behavior of NiTi with improved thermal stability from copper alloying. The addition of copper narrows the thermal hysteresis and raises transition temperatures, making this alloy useful for applications requiring precise actuation within constrained temperature windows or where repeatability across thermal cycles is critical. Unlike binary NiTi, the ternary composition offers better control over the austenite-finish and martensite-start temperatures, reducing energy losses and improving cycling durability in temperature-sensitive systems.
NiTiHf is a ternary shape memory alloy combining nickel, titanium, and hafnium, engineered to extend the operating temperature range beyond conventional NiTi by raising transformation temperatures while maintaining superelastic and shape-memory functionality. It is used in aerospace propulsion systems, high-temperature actuators, and thermal-cycling-resistant seals where traditional NiTi becomes unreliable; the hafnium addition is critical for applications demanding performance above 100°C where shape recovery and damping are essential design features. Compared to NiTi, NiTiHf trades some strain capacity and thermal stability window for significantly higher service temperatures, making it the material of choice when heating rules out conventional shape memory alloys but full-ceramic or superalloy rigidity is undesirable.
NiTiNb is a ternary nickel-titanium-niobium shape memory alloy engineered to exhibit wide thermal hysteresis, enabling large temperature differentials between the martensite and austenite phases during thermomechanical cycling. This composition is used in applications requiring high actuation temperatures, damping over broad temperature ranges, or robust recovery behavior under cyclic loading, particularly in aerospace sealing systems, precision actuators, and vibration isolation devices where conventional NiTi alloys lack sufficient thermal span or functional stability.
Nitinol (NiTi) is a near-equiatomic nickel-titanium intermetallic alloy that exhibits shape memory and superelastic behavior, allowing it to recover large deformations upon heating or unloading without permanent plastic strain. This unique metallurgical behavior—driven by reversible martensitic phase transformations—makes it invaluable in applications requiring actuators, dampers, or components that must return to a programmed geometry after deformation. Engineers select Nitinol over conventional metals when design space is constrained and active or passive motion control is needed, or when the ability to absorb large strains without failure is critical to device function.
Nitinol (NiTi) is a nickel-titanium shape-memory and superelastic alloy that exhibits remarkable strain recovery—when deformed, it returns to its original shape upon unloading or heating, depending on the alloy's thermal state. This property stems from a reversible phase transformation between austenite and martensite crystal structures, making it fundamentally different from conventional metals. In superelastic form (used at room temperature above the austenite finish temperature), Nitinol absorbs and releases large elastic deformations repeatedly without permanent set, enabling designs where flexibility and damage tolerance are critical. The alloy is widely deployed in medical devices—stents, guidewires, orthodontic wires, and surgical instruments—where its biocompatibility, fatigue resistance, and ability to conform to complex geometries while maintaining structural integrity are essential; it is also found in aerospace actuators, seismic dampers, and precision mechanical switches where its unique combination of elasticity and hysteretic energy absorption outperforms conventional springs or elastic materials.
Oxidized Zr-2.5Nb (marketed as Oxinium) is a surface-hardened zirconium alloy created by controlled oxidation of a zirconium-niobium base metal, producing a ceramic oxide layer bonded to a ductile metallic substrate. This material is engineered specifically for bearing and articulating surfaces in orthopedic implants, where the hard oxide exterior minimizes wear and the tough underlying alloy provides damage tolerance. Compared to conventional cobalt-chromium or alumina-on-plastic combinations, Oxinium offers reduced wear rates and improved scratch resistance while maintaining the fracture toughness advantage of metallic substrates, making it particularly valuable in hip and knee replacements where long-term durability and low particulate generation are critical.
PH13-8Mo is a martensitic precipitation-hardening stainless steel (13% Cr, 8% Ni, Mo, Al) that achieves ultra-high strength in the H1000 condition through age hardening, providing yield strengths around 1310 MPa with good corrosion resistance and fatigue performance for aerospace fasteners, bearings, and critical structural components. The H1000 temper represents maximum strength conditioning and maintains useful strength to approximately 300°C with excellent bearing fatigue and fatigue crack growth resistance, making it suitable for demanding load-bearing applications where both strength and corrosion resistance are required.
PH13-8Mo is a martensitic precipitation-hardening stainless steel (13% Cr, 8% Ni, Mo, Al additions) used in aerospace applications requiring high strength and corrosion resistance to approximately 600°C; the H1050 condition provides a yield strength around 1,050 ksi through precipitation hardening, with excellent fatigue performance and stress-corrosion cracking resistance in chloride environments.
PH13-8Mo H1100 is a precipitation-hardened martensitic stainless steel (13% Cr, 8% Mo, 2.5% Ni) that achieves high strength (typically 1310 MPa yield) through H1100 heat treatment (1100°F aging), providing excellent corrosion resistance and fatigue performance for aerospace fasteners, landing gear components, and other critical applications requiring high strength-to-weight ratio at elevated temperatures up to ~315°C. Available in forged, ring, and extruded bar forms, this alloy offers good ductility and toughness balanced with superior tensile strength suitable for demanding structural and fastening applications per AMS 5629.
PH13-8Mo stainless steel is a precipitation-hardening martensitic stainless steel containing molybdenum and copper that delivers high strength (typically 1,310 MPa yield) with good corrosion resistance, suited for aircraft engine components and fasteners. The H950 condition is aged to provide peak hardness and tensile properties while maintaining adequate ductility and fracture toughness for critical aerospace applications per AMS 5629.
PH15-7Mo is a precipitation-hardening stainless steel with molybdenum strengthening providing yield strengths around 1,380 MPa (200 ksi) in the H1050 condition, suitable for aerospace fasteners, springs, and high-strength structural components requiring corrosion resistance at elevated temperatures. The H1050 temper delivers optimized strength through controlled aging while maintaining toughness for critical bearing and fastening applications in aircraft engines and airframes.
Porous tantalum, also known by the trade name Trabecular Metal, is a highly biocompatible pure tantalum foam structure engineered with interconnected porosity to mimic cancellous bone architecture. Its combination of biological integration capability, corrosion resistance, and radiopacity makes it the preferred choice for orthopedic and spinal implants where bone on-growth and long-term fixation are critical; it outperforms alternatives like titanium alloys in applications requiring rapid osseointegration and can eliminate the need for bone cement or supplemental fixation screws.
QE22A is a magnesium alloy containing rare earth elements (primarily cerium and lanthanum) designed for elevated-temperature aerospace applications, offering superior creep resistance and strength retention up to approximately 300°C. The T6 temper (solution heat-treated and artificially aged) provides optimal mechanical properties and dimensional stability for sand-cast components in engines and structural applications operating under thermal stress.
René 41 is a cobalt-based superalloy containing nickel, chromium, molybdenum, and aluminum alloying elements, designed for high-temperature structural applications in gas turbines and jet engines. The STA (solution-treated and aged) condition provides elevated-temperature strength retention and creep resistance up to approximately 1200°F (650°C), with excellent fatigue performance and oxidation resistance for demanding aerospace propulsion environments.
René 41 STA is a nickel-base superalloy (Ni-Co-Cr-Mo-W-Al-Ti) in solution heat-treated and aged condition, designed for high-temperature structural applications in jet engines and gas turbines operating up to 1100°F (593°C). The STA condition provides optimized strength and creep resistance through controlled grain structure and precipitation hardening, with excellent bearing strength and fatigue performance in bar, forging, plate, and sheet forms.
René 88DT is a nickel-based superalloy designed for high-temperature structural applications requiring exceptional strength and creep resistance at elevated temperatures. It is used primarily in aerospace propulsion systems—particularly in turbine engine components such as blades, vanes, and casings—where sustained thermal and mechanical loads demand reliable performance in extreme environments. Engineers select this alloy when superior high-temperature capability and fatigue resistance are critical, making it preferable to conventional nickel superalloys in next-generation engine designs and demanding industrial gas turbine applications.
Unalloyed tantalum (ASTM F560) is a highly pure refractory metal (≥99.5% Ta) prized for its exceptional corrosion resistance, biocompatibility, and ability to withstand extreme temperatures without degradation. It is widely used in chemical processing equipment, medical implants, and aerospace/defense applications where exposure to aggressive corrosive environments or physiological fluids demands a material that remains stable and inert over extended service life. Engineers select tantalum when stainless steels and nickel alloys prove insufficient due to chloride pitting, sulfuric acid attack, or when direct contact with living tissue requires proven biocompatibility without elution of harmful ions.
Ti-13Nb-13Zr is a near-beta titanium alloy composed primarily of titanium with balanced additions of niobium and zirconium, designed to achieve low elastic modulus while maintaining strength and biocompatibility. It is primarily used in orthopedic implants and dental applications where reducing the stiffness mismatch between implant and bone is critical to prevent stress shielding and promote long-term integration. This alloy is notable for combining β-stabilizing elements (Nb, Zr) that lower the Young's modulus compared to conventional titanium alloys, making it attractive for load-bearing implants that require both mechanical reliability and biological acceptance without the cytotoxicity concerns of vanadium-containing alternatives.
Ti-13V-11Cr-3Al is a metastable beta titanium alloy containing vanadium and chromium additions for enhanced strength and hardenability, primarily used in aerospace fasteners, springs, and bearing applications. The annealed condition provides moderate strength levels (approximately 130–150 ksi yield) with improved ductility and fracture toughness compared to aged conditions, suitable for applications requiring good fatigue resistance and damage tolerance.
Ti-13V-11Cr-3Al is a metastable beta titanium alloy containing 13% vanadium, 11% chromium, and 3% aluminum, designed for high-strength aerospace fastener and structural applications requiring superior bearing strength and fatigue resistance. The STA (solution-treated and aged) condition provides yield strengths in the 1,200–1,400 MPa range with excellent compressive properties and damage tolerance, making it suitable for critical bearing surfaces and highly stressed mechanical components in aircraft structures and engines.
Ti-15Mo is a metastable beta-phase titanium alloy containing 15 wt% molybdenum, designed to combine the corrosion resistance and biocompatibility of titanium with the strength and lower modulus benefits of beta-stabilized microstructures. It is used in biomedical implants (orthopedic and dental), aerospace components, and chemical processing equipment where corrosion resistance, biocompatibility, and moderate strength are prioritized; compared to α+β titanium alloys like Ti-6Al-4V, Ti-15Mo offers improved corrosion resistance and lower stiffness while maintaining good strength, making it particularly valuable in load-bearing implants where modulus matching to bone or tissue is beneficial.
Alpha titanium alloy with excellent weldability and cryogenic toughness. 795 MPa yield. Used in cryogenic applications (liquid hydrogen/oxygen), high-pressure gas bottles, and airframe forgings. One of the oldest aerospace titanium alloys.
Ti-5Al-2.5Sn is a near-alpha titanium alloy used primarily in aircraft engines and high-temperature aerospace applications, offering good creep resistance and tensile strength up to approximately 600°F. The annealed condition provides optimal ductility and dimensional stability after hot forming operations, with yield strength around 70-90 ksi and excellent damage tolerance characteristics.
Ti-6Al-2Sn-4Zr-2Mo is a near-alpha titanium alloy strengthened by aluminum and molybdenum additions, designed for elevated-temperature applications requiring moderate strength and creep resistance up to approximately 600°C in aerospace gas turbine engines and compressor casings. Duplex annealed condition provides optimal combination of strength and fracture toughness through controlled recrystallization and alpha-phase stabilization, with yield strengths typically 800–1000 MPa and good ductility (8–15% elongation) across bar, forging, and sheet product forms.
Ti-6242 is a near-alpha titanium alloy combining aluminum, tin, zirconium, and molybdenum additions to create a material with excellent creep resistance and thermal stability at intermediate temperatures. It is used primarily in gas turbine engines, compressor casings, and other high-temperature structural applications where sustained performance in the 300–500 °C range is critical. Engineers select Ti-6242 over conventional Ti-6Al-4V when creep resistance and extended service life at elevated temperatures are priorities, making it particularly valuable in military and commercial aerospace propulsion systems where weight savings and durability directly impact performance.
Ti-6Al-4V is the most widely used titanium alloy, offering an excellent strength-to-weight ratio, good corrosion resistance, and biocompatibility. Standard workhorse alloy for aerospace, biomedical, and high-performance applications.
Ti-6Al-4V annealed is a two-phase titanium alloy (6% aluminum, 4% vanadium) in a stress-relieved condition offering moderate strength with improved ductility and fracture toughness compared to higher-strength tempers. Widely used in aerospace engine casings, compressor blades, and airframe components where operating temperatures to 300°C and damage tolerance are critical; available in forgings, extrusions, castings, and wrought forms per MIL specifications.
Ti-6Al-4V ELI (Extra Low Interstitial) is an extra-pure variant of the industry-standard Ti-6Al-4V titanium alloy, with tightly controlled oxygen and other interstitial elements to maximize ductility and fracture toughness. This material is the preferred choice in biomedical implants, aerospace components, and other applications where reliability and tissue compatibility are critical, as the reduced interstitial content enhances both mechanical reliability and biocompatibility compared to standard Ti-6Al-4V. Engineers select Grade 23 ELI when implant longevity, crack resistance, and minimal inflammatory response are non-negotiable—making it the de facto standard for orthopedic and cardiovascular devices despite higher material cost.
Ti-6Al-4V Grade 5 is a two-phase titanium alloy containing aluminum and vanadium alloying elements, representing the most widely used titanium alloy in industry due to its excellent balance of strength, weight, and corrosion resistance. It is the workhorse material for aerospace structures, medical implants, and chemical processing equipment, chosen by engineers specifically for applications requiring high strength-to-weight ratio, superior biocompatibility, and reliable performance in demanding thermal and corrosive environments where conventional steels or aluminum alloys fall short.
Ti-6Al-4V produced via laser powder bed fusion (L-PBF) in the as-built condition is a titanium alloy renowned for its strength-to-weight ratio and biocompatibility, commonly used in aerospace, medical device, and high-performance industrial applications. The as-built microstructure—characterized by rapid solidification from the additive manufacturing process—exhibits high strength but lower ductility compared to wrought or heat-treated variants, making it suitable for load-bearing components where weight reduction and design complexity are critical. Engineers select this material when the ability to fabricate near-net-shape geometries, integrate functional features, and avoid traditional machining waste outweighs the need for maximum elongation or when post-process heat treatment is planned.
Ti-6Al-4V (titanium–6% aluminum–4% vanadium) is a two-phase alpha-beta titanium alloy manufactured via laser powder bed fusion (L-PBF) and stress-relieved to reduce residual stresses from the additive manufacturing process. This material combines the lightweight, corrosion-resistant properties of titanium with excellent strength-to-weight ratio, making it a preferred choice for aerospace, medical device, and demanding industrial applications where weight savings and durability are critical. The L-PBF processing route enables complex near-net-shape geometries and reduced material waste compared to wrought forms, though the stress-relieved condition represents an intermediate heat treatment state positioned between as-built and fully annealed material.
Ti-6Al-4V STA is a solution heat-treated and aged (STA) condition of the titanium alloy Ti-6Al-4V, providing improved strength and creep resistance compared to annealed conditions through precipitation hardening, with typical yield strengths in the 140–160 ksi range. This condition is widely used in aerospace applications including jet engine compressor blades, landing gear, and airframe components requiring high specific strength, fatigue resistance, and reliable performance up to approximately 300°C.
Ti-6Al-6V-2Sn is a near-alpha titanium alloy containing 6% aluminum, 6% vanadium, and 2% tin, designed for elevated-temperature aerospace applications requiring moderate strength and creep resistance up to approximately 600°C. The alloy offers good fatigue performance and weldability with moderate density, making it suitable for jet engine components, airframes, and other high-temperature structural applications.
Ti-6Al-6V-2Sn is a near-alpha titanium alloy combining aluminum and vanadium for strength with tin for elevated-temperature stability, commonly used in gas turbine engines and airframes requiring sustained performance to approximately 600°C. The annealed condition provides a stable microstructure with moderate strength and good ductility, suitable for components requiring damage tolerance and fracture toughness over maximum strength.
Ti-6Al-6V-2Sn is a near-alpha titanium alloy containing 6% aluminum, 6% vanadium, and 2% tin, designed for elevated-temperature aerospace applications requiring high strength retention to approximately 600°C. The STA (solution-treated and aged) condition provides a controlled microstructure with excellent creep resistance, high yield and tensile strength, and good fracture toughness, making it suitable for compressor blades, casings, and other critical jet engine and airframe components.
Ti-6Al-7Nb is a near-alpha titanium alloy that substitutes niobium for vanadium in the classic Ti-6Al-4V formulation, eliminating concerns about vanadium cytotoxicity in biomedical applications. It is widely used in orthopedic and dental implants, cardiovascular devices, and surgical instruments where biocompatibility, corrosion resistance, and load-bearing reliability are critical. Engineers select this alloy over Ti-6Al-4V specifically for long-term implantable devices where material-body interaction must be minimized, while maintaining comparable mechanical performance and superior fatigue resistance in cyclic loading environments.
Ti-8Al-1Mo-1V is a near-alpha titanium alloy with moderate strength and superior creep resistance, designed for elevated-temperature aerospace applications requiring service to approximately 1200°F. The alloy combines aluminum for strength and low density with molybdenum and vanadium for creep and heat-resistance properties, with Duplex Annealed condition providing optimized toughness and Solution Treated condition delivering maximum strength.
Ti-8Al-1Mo-1V is a near-alpha titanium alloy with moderate strength and excellent creep resistance, designed for elevated-temperature applications in jet engines and gas turbines. Duplex Annealed condition provides balanced strength and ductility through dual-phase heat treatment, yielding tensile strengths in the 140–160 ksi range with good elongation for damage-tolerant design in aircraft powerplant components operating to approximately 600°C.
Udimet 720 is a nickel-based superalloy designed for high-temperature structural applications requiring exceptional strength retention at elevated temperatures. It is widely used in jet engine components—particularly turbine blades, vanes, and casings—where it must withstand sustained thermal cycling and mechanical stress in the 700–800 °C operating range. Engineers select Udimet 720 over conventional superalloys when creep resistance, fatigue life, and damage tolerance are critical in demanding aerospace and power-generation environments.
Nickel-based superalloy (Ni-19.5Cr-13.5Co-4.3Mo-3Al-1.4Ti). 795 MPa yield, 1275 MPa UTS. Workhorse disc alloy for intermediate-temperature turbine stages (up to ~700°C). Good forgeability and weldability for a superalloy.
Waspaloy is a nickel-based superalloy containing cobalt, chromium, molybdenum, and tungsten alloying elements, designed for high-temperature structural applications in gas turbine engines and other demanding aerospace environments. The solution, stabilization, and precipitation heat-treated condition provides optimized strength and creep resistance through controlled gamma-prime precipitation, with tensile properties (yield strength, ultimate tensile strength, elongation, and reduction of area) suitable for elevated-temperature service up to approximately 1200°F (650°C).
ZE41A is a magnesium alloy containing zinc, rare earth elements, and zirconium, designed for elevated-temperature aerospace castings requiring moderate strength and creep resistance up to approximately 150°C. The T5 temper (artificially aged) provides improved yield and bearing strength characteristics in sand-cast form per AMS 4439, suitable for engine components and structural aircraft parts operating under sustained thermal loads.
ZK60A is a high-strength magnesium alloy containing zinc and zirconium, used in aerospace and defense applications requiring excellent strength-to-weight ratio and moderate elevated-temperature capability. The alloy provides superior creep resistance compared to other magnesium alloys, with T5 temper offering improved mechanical properties through controlled heat treatment and natural aging.
2014 Aluminum T651 is a copper-alloyed aerospace aluminum with solution heat treatment, stress relief, and artificial aging, delivering tensile strength of approximately 70–75 ksi with enhanced fatigue resistance and dimensional stability for structural aircraft components. The T651 temper provides improved crack resistance compared to T4 while maintaining good machinability, making it suitable for forged and machined airframe fittings, wings, and fuselage sections where fatigue and sustained loads are critical.
2014 aluminum (T651X) is a copper-alloyed wrought aluminum alloy in an artificial age-hardened condition with controlled stretching, providing high strength (ultimate tensile strength ~70 ksi / 485 MPa) and improved stress-relief characteristics suitable for aerospace structural applications. The T651X temper delivers enhanced fracture toughness and reduced quench sensitivity compared to unstretched T651, making it preferred for thick-section forgings and extrusions in critical load-bearing components where damage tolerance is required.
2024 Aluminum T351 is a solution heat-treated and stress-relieved aluminum-copper alloy (nominally 4.4% Cu, 1.5% Mg, 0.6% Mn) used in high-strength aerospace and defense structures. The T351 temper provides excellent fatigue resistance and fracture toughness through controlled stress relief, making it the preferred condition for aircraft wing skins, fuselage components, and highly stressed fasteners operating in service environments.
2024 Aluminum T351X is a copper-aluminum alloy in an artificially aged condition following solution heat treatment and stress relief stretching, providing high strength-to-weight ratio (ultimate tensile strength ~70 ksi) with improved stress-corrosion cracking resistance compared to T4 temper. Primary applications include aircraft fuselage skin, wing components, and fasteners requiring sustained strength at elevated temperatures up to ~300°F with controlled residual stress levels.