2219 Aluminum Alloy Bar


2219 Aluminum is a precipitation/age hardening alloy with excellent strength and mechanical properties. This copper-containing alloy features extreme toughness and excellent stress corrosion resistance when treated making it an excellent metal for use in supersonic aircraft component manufacture and high temperature structural applications. AL 2219 is mainly aluminum based, with copper being the other major chemical property. Standard specifications for 2219 include ASTM 4066, ASTM B209 and more.


Aluminium Alloy 2219 is with high strength alloy which combines good machinability and good mechanical properties. 2219 is useful over a temperature range of -452°F to 600°F, is readily weldable and has good fracture toughness. In the T8 condition it is resistant to stress corrosion cracking.


2219 aluminium alloy is an alloy in the wrought aluminium-copper family (2000 or 2xxx series). It can be heat-treated to produce tempers with higher strength but lower ductility. The aluminium-copper alloys have high strength, but are generally less corrosion resistant and harder to weld than other types of aluminium alloys. To compensate for the lower corrosion resistance, 2219 aluminium can be clad in a commercially pure alloy such as 1050 or painted. This alloy is commonly formed by both extrusion and forging, but is not used in casting.


The 2219 aluminium alloy in particular has high fracture toughness, is weldable and resistant to stress corrosion cracking, therefore it is widely used in supersonic aircraft skin and structural members. The Space Shuttle Standard Weight Tank was also fabricated from the 2219 alloy. The Columbus module on the International Space Station also used 2219 aluminium alloy with a cylinder thickness of 4 mm, which was increased to 7 mm for the end cones.


Chemical Composition:


Balance0.20 max0.30 max5.80-6.800.20-0.400.02 max0.10 max0.02-0.100.05-0.150.10-0.25


Mechanical Properties:


Hardness, Brinell115115
Hardness, Knoop145145
Hardness, Rockwell A45.545.5
Hardness, Rockwell B7272
Hardness, Vickers130130
Ultimate Tensile Strength414 MPa60000 psi
Tensile Yield Strength290 MPa42000 psi
Elongation at Break10%10%
Modulus of Elasticity73.1 GPa10600 ksi
Poisson’s Ratio0.330.33
Fatigue Strength103 MPa15000 psi
Shear Modulus27 GPa3920 ksi
Shear Strength255 MPa37000 psi



Physical Properties at different states:


Aluminium Alloy 2219 - Bar / Extrusions

MaterialTemperDirectionTensile Strength ksiYield Strength ksiElongation in 2" (%)
Alloy 2219 (AMS 4162)T8511L58426
Alloy 2219 (AMS 4162)T8511LT56394


Aluminium 2219 - Sheet / Plater (Bare)

MaterialTemperThicknessTensile Strength ksiYield Strength ksiElongation in 2" (%)
Alloy 2219 (QQ-A-250/30)00.020"-2.0032 max16 max12
Alloy 2219 (QQ-A-250/30)T3510.250" - 2.00"462810
Alloy 2219 (QQ-A-250/30)T8510.250" - 2.00"62467-8


Aluminium 2219 - Sheet / Plater (Clad) Temper T81 / T851

MaterialTemperThicknessTensile Strength ksiYield Strength ksiElongation in 2" (%)
Alloy 2219 (AMS 4094)T81/ T8510.020"-0.039"49376
Alloy 2219 (AMS 4094)T81/ T8510.039"-0.099"55417
Alloy 2219 (AMS 4094)T81/ T8510.099"-0.249"58437
2219 (AMS 4094)T81/ T8510.245"-0.499"58428


Thermal Properties:


CTE, linear 68°F22.3 µm/m-°C12.4 µin/in-°F
CTE, linear 250°C24.1 µm/m-°C13.4 µin/in-°F
Specific Heat Capacity0.864 J/g-°C0.207 BTU/lb-°F
Thermal Conductivity120 W/m-K833 BTU-in/hr-ft²-°F
Liquids643 °C1190 °F



  • Supersonic aircraft skin
  • Structural members
  • High strength weldments
  • Space booster
  • Fuel tanks
  • Aircraft parts


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