Aluminium alloy 2014 2014

Al-Cu-Mg-Si wrought alloy (AlCu₄SiMg). Composition limits for 2014A in wt% (BS EN 573-3, as printed on Aalco): Cu 3.90 to 5.00, Mn 0.40 to 1.20, Mg 0.20 to 0.80, Si 0.50 to 0.90, Fe max 0.50, Zn max 0.25, Ti max 0.15, Cr max 0.10, Al balance. Smiths gives the same Cu, Mn and Mg ranges.

Also known as UNS A92014, EN 3.1255, EN name EN AW-2014, EN name AlCu4SiMg, AFNOR A-U4SG, BS H15 · 4 more

2014 (also sold as 2014A; UNS A92014, EN AW-2014, W.Nr.

9 sources · Updated 2026-10-26 · CC BY 4.0

Evidence level

2 of 5

Lab-measured

Carry load

460 MPa minimum tensile

Carry heat

138 W/(m·K)

Weight

2.82 g/cm3

Melting

535 °C

Sheet strength by temper

440 MPa T651 against 400 MPa T4

Recipe, share of the weight

Al balanceAluminium
Cu 3.9 to 5%Copper
Mn 0.4 to 1.2%Manganese
Mg 0.2 to 0.8%Magnesium
Si 0.5 to 0.9%Silicon

Best for

High-strength structural parts for aerospace and defence, where a 460 MPa minimum tensile strength in T651 plate is needed and the part is clad or painted against corrosion

Weakest at

Corrosion resistance (poor in water and salt, with pitting and galvanic attack in sea water), and welding, which is difficult and prone to cracking

Risk at a glance

People Low. Low in solid form
If it fails Severe. Pitting and galvanic attack in chloride or sea water
Corrosion Severe. Corrosion resistance is poor, so unclad 2014 needs paint or cladding.

Quick facts: 2014

Key properties of 2014
Property	Value	Basis
Density	2.82 g/cm³	1 sourced value
Yield strength	at least 225 MPa	5 sourced values across conditions
Tensile strength	at least 400 MPa	5 sourced values across conditions
Young's modulus	71 GPa	1 sourced value
Hardness (Brinell)	138 HB	1 sourced value
Thermal conductivity	138 W/(m·K)	1 sourced value
Thermal expansion (CTE)	23 ppm/K	1 sourced value
Melting point	510 to 638 °C	2 sourced values across conditions
Electrical resistivity	4.5e-8 Ω·m	1 sourced value

What is the density of Aluminium alloy 2014?

Aluminium alloy 2014 has a density of 2.82 g/cm³. The source and test conditions are listed in the properties table on this page.

What is the thermal conductivity of Aluminium alloy 2014?

Aluminium alloy 2014 has a thermal conductivity of 138 W/(m·K). The source and test conditions are listed in the properties table on this page.

What is the coefficient of thermal expansion of Aluminium alloy 2014?

Aluminium alloy 2014 has a coefficient of thermal expansion of 23 ppm/K. The source and test conditions are listed in the properties table on this page.

What is the melting point of Aluminium alloy 2014?

Aluminium alloy 2014 has a melting point of 510 to 638 °C. The range covers 2 sourced values across the tempers, forms and test conditions the sources report; room-temperature values are used where a source states a temperature.

What is the yield strength of Aluminium alloy 2014?

Aluminium alloy 2014 has a yield strength of at least 225 MPa. The range covers 5 sourced values across the tempers, forms and test conditions the sources report; room-temperature values are used where a source states a temperature.

What are the other names and codes for Aluminium alloy 2014?

Aluminium alloy 2014 is also written as UNS A92014, EN 3.1255, EN name EN AW-2014, EN name AlCu4SiMg, AFNOR A-U4SG, BS H15. Each code is printed in the source listed beside it in the designations table.

What is Aluminium alloy 2014 used for?

Uses recorded in the sources include Aircraft structural parts; Saturn cryogenic propellant tanks; Motorsport uprights, hydraulic parts and fasteners.

Why it exists

2014 is a copper-bearing aluminium alloy chosen for high strength and fatigue resistance. The Aalco 2014A datasheet in the T651 temper gives a minimum tensile strength of 460 MPa for 12.5 to 40 mm plate, a density of 2.82 g/cm3 and a thermal conductivity of 138 W/(m·K). Its weak point is corrosion: Aalco rates its resistance to atmospheric attack as poor, especially in water or salt, so it is often clad or painted. A presentation in the UAH archive says the Saturn cryogenic tanks were made of 2014-T6.

Where it's used

Aerospace structures

Aircraft Materials describes 2014 as commonly used in many aerospace structural applications. Smiths lists motorsport uprights, hydraulic parts and fasteners among its typical uses.

Launch vehicle tanks

A presentation in the UAH archive says the Saturn tanks for cryogenic fuels were fabricated of 2014-T6 aluminium alloy, and that many of their structural features were first developed for the Thor booster.

Recipe

Wrought Al-Cu-Mg-Si alloy (AlCu4SiMg). Composition limits from the BS EN 573-3 table on the Aalco 2014A datasheet: copper 3.90 to 5.00 wt%, manganese 0.40 to 1.20, magnesium 0.20 to 0.80, silicon 0.50 to 0.90, with iron, zinc, titanium and chromium at their maxima and aluminium the balance. It is supplied in the fully heat-treated condition, solution heat-treated and artificially aged (Aalco), and is extruded and forged in practice (Wikipedia).

What 2014 is made of
Ingredient	Share of the weight	What it does
Aluminium Al	balance	Matrix of the alloy.
Copper Cu	3.9 to 5%	Main alloying element, which gives the alloy its precipitation-hardening strength.
Manganese Mn	0.4 to 1.2%	Alloying element.
Magnesium Mg	0.2 to 0.8%	Alloying element.
Silicon Si	0.5 to 0.9%	Alloying element, 2014A has slightly less iron and silicon than 2014 (Smiths).

Weight shares are as printed in the sources.

What it can do

Carry load

460 MPa minimum tensile

The 2014A T651 plate from 12.5 to 40 mm has a minimum tensile strength of 460 MPa, a minimum proof stress of 400 MPa and a minimum elongation of 6 %.

Carry heat

138 W/(m·K)

measured

Thermal conductivity is 138 W/(m·K) on the Aalco datasheet. NASA says the room-temperature conductivity of 2014 can be up to 30 percent lower than that of electrical-conductor-grade aluminium.

Weight

2.82 g/cm3

measured

Density is 2.82 g/cm3 on the Aalco datasheet, and the Smiths datasheet prints the same figure.

Melting

535 °C

measured

The datasheet gives a melting point of 535 °C. NASA gives a melting range of 510 to 638 °C for the alloy.

Sheet strength by temper

440 MPa T651 against 400 MPa T4

A T651 sheet from 0.4 to 6 mm has a minimum tensile strength of 440 MPa. The T4 bare sheet from 0.2 to 6.0 mm has a minimum of 400 MPa and a minimum yield strength of 225 MPa.

How it compares

The Smiths datasheet gives the same 460 MPa minimum tensile class for bar in T6, T6510 and T6511 from 25 to 75 mm, and Aircraft Materials gives 480 MPa for T6510 bar from 20 to 75 mm. Temper changes strength a lot: T4 sheet is 400 MPa and T6 sheet is 440 MPa minimum. The figures come from different datasheets and product forms, so read the rows as examples, not as a ranking against other aluminium profiles.

The same measurements for each material, so you can compare them. Each row names the key condition under the value; the full conditions and methods are in the numbered notes under Technical details. Other materials are shown beside it; each was measured under its own conditions, so open its page before comparing closely. Compare every grade in the family.

Benchmarks
Measurement	2014	6061	7075-T6	2024	5052	5XXX	2195 (Al-Cu-Li)	Al	1050	2011	2017	2017A	2219	2319	2618A	3003	3103	4047	5019	5056	5083	AlMg2	AlMg3	6013	6063	6082	6101	AA7050	AA8011	Au-Al IMCs	Al master alloys
Thermal behavior and safety
Thermal conductivity, 2014A datasheetValue printed in a stockist datasheet	138 W/(m·K)²	167 W/(m·K)	130 W/m·K	121 W/m-K	138 W/m-K	138 W/(m·K)	no data	220 W/(m·K)	229 W/m.K	140 W/m.K	140 W/m.K	140 W/m.K	130 W.m/m2.°C	no data	147 W/m.K	190 W/m.K	160 W/m.K	no data	110 to 140 W/(m·K)	109 to 117 W/(m·K)	121 W/(m·K)	138 W/(m·K)	140 to 160 W/(m·K)	164 W/(m·K)	200 W/(m·K)	180 W/(m·K)	no data	154 W/(m·K)	210 to 220 W/(m·K)	no data	no data
Melting point, 2014A datasheetSingle value printed in a stockist datasheet	535 °C⁴	no data	532 °C	no data	607.2 to 649 °C	no data	1020 degF	660 °C	645 to 657 °C	540 °C	510 °C	510 °C	543 °C	543 to 643 °C	549 °C	655 °C	655 °C	1068 to 1080 °F	575 to 630 °C	565 to 640 °C	570 °C	605 to 650 °C	590 to 645 °C	579 °C	600 °C	575 °C	1090 °F	490 °C	640 to 655 °C	no data	880 °C
Melting range (lower to upper), alloy 2014	510 to 638 °C⁵	no data	532 °C	no data	607.2 to 649 °C	no data	1020 degF	660 °C	645 to 657 °C	540 °C	510 °C	510 °C	543 °C	543 to 643 °C	549 °C	655 °C	655 °C	1068 to 1080 °F	575 to 630 °C	565 to 640 °C	570 °C	605 to 650 °C	590 to 645 °C	579 °C	600 °C	575 °C	1090 °F	490 °C	640 to 655 °C	no data	880 °C
Physical and electrical
Density, 2014A datasheetValue printed in a stockist datasheet	2.82 g/cm³	2.7 g/cm³	2.8 Mg/m3	2.78 g/cc	2.68 g/cc	2.68 g/cm³	0.096 lb/in3	2.7 g/cm³	2.71 g/cm³	2.82 g/cm³	2.79 g/cm³	2.79 g/cm³	2.84 g/cm³	2.84 g/cm³	2.76 g/cm³	2.73 g/cm³	2.73 g/cm³	2.65 g/cm³	2.64 g/cm³	2.64 g/cm³	2.65 g/cm³	2.69 g/cm³	2.67 g/cm³	2.71 g/cm³	2700 kg/m3	2.7 g/cm³	0.097 lb/cu.in	2.83 g/cm³	2.71 g/cm³	no data	no data
Electrical resistivity, 2014A datasheet	0.045 µΩ·m⁶	4 µΩ·cm	5.2 µΩ·cm	5.82 µΩ·cm	no data	5.8 µΩ·cm	no data	2.646 µΩ·cm	no data	no data	no data	no data	5.7 μΩ.cm²/cm	no data	no data	no data	no data	no data	0.0526 to 0.0667 Ω·mm²/m	5.88×10^-8 to 6.25×10^-8 Ω·m	0.058 µΩ·m	50 nΩ·m	no data	no data	0.35 µΩ·m	0.038 µΩ·m	no data	no data	2.86×10^-8 to 2.94×10^-8 Ω·m	no data	no data
Brinell hardness, plate 12.5 to 40 mm, T651Value printed in a stockist datasheet	138 HB⁷	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	no data	75 HB	no data	52 HB	130 HB	no data	91 HB	no data	no data	no data	no data	no data
Other measurements
Modulus of elasticity, 2014A datasheetValue printed in a stockist datasheet	71 GPa¹	68.9 GPa	71 GPa	73.1 GPa	70.3 GPa	70.3 GPa	11 MSI	69 GPa	69000 MPa	70 GPa	72 GPa	72 GPa	73.8 x10^3 N/mm2	no data	71 GPa	69.5 GPa	69.5 GPa	no data	70 GPa	71 GPa	72 GPa	70 GPa	70 GPa	71 GPa	69.5 GPa	70 GPa	no data	71.5 GPa	70 GPa	no data	no data
Coefficient of thermal expansion, 2014A datasheetValue printed in a stockist datasheet	23 ppm/K³	23.6 ppm/K	23.4 µm/m·K	23.2 ppm/K	24.8 µm/m-°C	24 ppm/K	no data	22.5 ppm/K	23.5 x10-6/K	21.4 µm/m.°C	22.9 µm/(m·°C)	22.9 µm/m.°C	22.5 x10^-6 m/m.°C	no data	21.6 µm/m°C	23.1 ppm/K	23.1 x10-6/K	no data	no data	2.41×10^-5 1/K	25 ppm/K	23.8 µm/m/°C	23.9 ppm/K	21.7 µm/m°C	23.5 ppm/K	23.1 ppm/K	no data	23.5 ppm/K	2.35×10^-5 1/K	no data	no data
Tensile strength, minimum, plate 12.5 to 40 mm, T651Minimum value printed in a stockist datasheet	> 460 MPa⁸	310 MPa	572 MPa	469 MPa	28 ksi	228 MPa	80 ksi	88 MPa	105 to 145 MPa	300 MPa	427 MPa	427 MPa	> 62 ksi	160 MPa	420 MPa	110 MPa	> 140 MPa	124 MPa	270 to 350 MPa	300 MPa	275 to 350 MPa	190 to 230 MPa	190 to 260 MPa	410 MPa	27 ksi	> 300 MPa	32000 psi	> 483 MPa	180 to 195 MPa	no data	no data
Proof stress, minimum, plate 12.5 to 40 mm, T651Minimum value printed in a stockist datasheet	> 400 MPa⁹	276 MPa	503 MPa	324 MPa	13 ksi	193 MPa	74 ksi	29 MPa	> 85 MPa	140 MPa	276 MPa	276 MPa	> 50 ksi	70 MPa	350 MPa	50 MPa	> 110 MPa	55 MPa	no data	no data	> 125 MPa	> 120 MPa	> 80 MPa	350 MPa	21 ksi	> 255 MPa	28000 psi	> 414 MPa	no data	no data	no data
Elongation A, minimum, plate 12.5 to 40 mm, T651Minimum value printed in a stockist datasheet	> 6 %¹⁰	17 %	11 %	19 %	25 %	12 %	8 %	50 to 65 %	4 to 8 %	16 %	18 %	18 %	> 6 %	12 %	> 5 %	25 %	> 8 %	12 %	> 2 %	20 %	> 12 %	4 to 12 %	> 12 %	4 %	8 %	> 9 %	> 8 %	> 7 %	> 1 %	no data	no data
Tensile strength, minimum, sheet 0.4 to 6 mm, T651Minimum value printed in a stockist datasheet	> 440 MPa¹¹	310 MPa	572 MPa	469 MPa	28 ksi	228 MPa	80 ksi	88 MPa	105 to 145 MPa	300 MPa	427 MPa	427 MPa	> 62 ksi	160 MPa	420 MPa	110 MPa	> 140 MPa	124 MPa	270 to 350 MPa	300 MPa	275 to 350 MPa	190 to 230 MPa	190 to 260 MPa	410 MPa	27 ksi	> 300 MPa	32000 psi	> 483 MPa	180 to 195 MPa	no data	no data
Proof stress, minimum, sheet 0.4 to 6 mm, T651Minimum value printed in a stockist datasheet	> 390 MPa¹²	276 MPa	503 MPa	324 MPa	13 ksi	193 MPa	74 ksi	29 MPa	> 85 MPa	140 MPa	276 MPa	276 MPa	> 50 ksi	70 MPa	350 MPa	50 MPa	> 110 MPa	55 MPa	no data	no data	> 125 MPa	> 120 MPa	> 80 MPa	350 MPa	21 ksi	> 255 MPa	28000 psi	> 414 MPa	no data	no data	no data
Tensile strength, minimum, bar T6510 20 to 75 mm	> 480 MPa¹³	310 MPa	572 MPa	469 MPa	28 ksi	228 MPa	80 ksi	88 MPa	105 to 145 MPa	300 MPa	427 MPa	427 MPa	> 62 ksi	160 MPa	420 MPa	110 MPa	> 140 MPa	124 MPa	270 to 350 MPa	300 MPa	275 to 350 MPa	190 to 230 MPa	190 to 260 MPa	410 MPa	27 ksi	> 300 MPa	32000 psi	> 483 MPa	180 to 195 MPa	no data	no data
Yield strength, minimum, bar T6510 20 to 75 mm	> 435 MPa¹⁴	276 MPa	503 MPa	324 MPa	13 ksi	193 MPa	74 ksi	29 MPa	> 85 MPa	140 MPa	276 MPa	276 MPa	> 50 ksi	70 MPa	350 MPa	50 MPa	> 110 MPa	55 MPa	no data	no data	> 125 MPa	> 120 MPa	> 80 MPa	350 MPa	21 ksi	> 255 MPa	28000 psi	> 414 MPa	no data	no data	no data
Elongation, minimum, bar T6510 20 to 75 mm	> 7 %¹⁵	17 %	11 %	19 %	25 %	12 %	8 %	50 to 65 %	4 to 8 %	16 %	18 %	18 %	> 6 %	12 %	> 5 %	25 %	> 8 %	12 %	> 2 %	20 %	> 12 %	4 to 12 %	> 12 %	4 %	8 %	> 9 %	> 8 %	> 7 %	> 1 %	no data	no data
Tensile strength, minimum, bar T6/T6510/T6511 25 to 75 mmMinimum value printed in a stockist datasheet	> 460 MPa¹⁶	310 MPa	572 MPa	469 MPa	28 ksi	228 MPa	80 ksi	88 MPa	105 to 145 MPa	300 MPa	427 MPa	427 MPa	> 62 ksi	160 MPa	420 MPa	110 MPa	> 140 MPa	124 MPa	270 to 350 MPa	300 MPa	275 to 350 MPa	190 to 230 MPa	190 to 260 MPa	410 MPa	27 ksi	> 300 MPa	32000 psi	> 483 MPa	180 to 195 MPa	no data	no data
Proof stress, minimum, bar T6/T6510/T6511 25 to 75 mmMinimum value printed in a stockist datasheet	> 420 MPa¹⁷	276 MPa	503 MPa	324 MPa	13 ksi	193 MPa	74 ksi	29 MPa	> 85 MPa	140 MPa	276 MPa	276 MPa	> 50 ksi	70 MPa	350 MPa	50 MPa	> 110 MPa	55 MPa	no data	no data	> 125 MPa	> 120 MPa	> 80 MPa	350 MPa	21 ksi	> 255 MPa	28000 psi	> 414 MPa	no data	no data	no data
Elongation, minimum, bar T6/T6510/T6511 25 to 75 mmMinimum value printed in a stockist datasheet	> 7 %¹⁸	17 %	11 %	19 %	25 %	12 %	8 %	50 to 65 %	4 to 8 %	16 %	18 %	18 %	> 6 %	12 %	> 5 %	25 %	> 8 %	12 %	> 2 %	20 %	> 12 %	4 to 12 %	> 12 %	4 %	8 %	> 9 %	> 8 %	> 7 %	> 1 %	no data	no data
Tensile strength, minimum, sheet T4 bare 0.2 to 6.0 mm	> 400 MPa¹⁹	310 MPa	572 MPa	469 MPa	28 ksi	228 MPa	80 ksi	88 MPa	105 to 145 MPa	300 MPa	427 MPa	427 MPa	> 62 ksi	160 MPa	420 MPa	110 MPa	> 140 MPa	124 MPa	270 to 350 MPa	300 MPa	275 to 350 MPa	190 to 230 MPa	190 to 260 MPa	410 MPa	27 ksi	> 300 MPa	32000 psi	> 483 MPa	180 to 195 MPa	no data	no data
Yield strength, minimum, sheet T4 bare 0.2 to 6.0 mm	> 225 MPa²⁰	276 MPa	503 MPa	324 MPa	13 ksi	193 MPa	74 ksi	29 MPa	> 85 MPa	140 MPa	276 MPa	276 MPa	> 50 ksi	70 MPa	350 MPa	50 MPa	> 110 MPa	55 MPa	no data	no data	> 125 MPa	> 120 MPa	> 80 MPa	350 MPa	21 ksi	> 255 MPa	28000 psi	> 414 MPa	no data	no data	no data

Why choose it, and why not

Good for

High-strength machined parts: 460 MPa minimum tensile strength in 12.5 to 40 mm T651 plate.
Aerospace structures and cryogenic propellant tanks, according to the sources cited.
Machining: Smiths calls machinability excellent and Aalco calls it very good.

Watch out for

Corrosion: poor resistance in water and salt, with pitting and galvanic attack, so clad or paint the alloy.
Welding: difficult and prone to cracking. Aalco rates resistance spot and beam welding as excellent, and does not recommend oxygen or inert-gas welding.
Hot forming without artificial ageing lowers corrosion resistance.
The datasheets disagree on corrosion grade: Aalco says poor, Smiths says average.
No 2014 flight outgassing, erosion or cold-welding data were read in this run.

2014 is a high-strength copper-bearing aluminium alloy, with a 460 MPa minimum tensile strength in T651 plate, and it was used for Saturn cryogenic tanks according to the UAH archive. It corrodes readily in water and salt and is difficult to weld, so it needs cladding or paint. This profile has no 2014 flight-exposure data, fatigue values or toughness values.

Technical details

For scientists and researchers. Everything above comes from the record below: every number with its method, its conditions and its source.

Other names and standards

The same grade under other systems, as datasheets and standards print them. Each code was checked against the page it comes from.

Other names and standards
System	Codes
UNS	A92014
EN	3.1255
EN name	EN AW-2014, AlCu4SiMg
AFNOR	A-U4SG
BS	H15
AMS	4029 (sheet and plate, T651), 4121 (bars, rods and wire, T6)
ASTM	B 209 (sheet and plate)
Trade name	14S (pre-1954 industry designation)

Notes

The method, full conditions and any caveat for the numbered rows above.

Notes for the numbered rows
#	Measurement	Method	Conditions	Caveat
1	Modulus of elasticity, 2014A datasheet	—	grade 2014A (datasheet)temperature not stated	Smiths prints the same 71 GPa. Wikipedia gives 73 GPa as a typical value for 2014, so the figure depends on the source.
2	Thermal conductivity, 2014A datasheet	—	grade 2014A (datasheet)temperature not stated	Smiths prints the same 138 W/m.K. NASA says the room-temperature thermal conductivity of 2014 is up to 30 percent lower than that of electrical-conductor-grade aluminium.
3	Coefficient of thermal expansion, 2014A datasheet	—	grade 2014A (datasheet)temperature not statedunit in source 23 x10^-6 /K	—
4	Melting point, 2014A datasheet	—	grade 2014A (datasheet)pressure not stated	NASA gives a melting range of 510 to 638 °C for the same alloy, which contains this value.
5	Melting range (lower to upper), alloy 2014	Range printed in a NASA materials handbook, critical temperatures section	grade 2014 (NASA handbook)	—
6	Electrical resistivity, 2014A datasheet	Value printed in a stockist datasheet; µΩ·m is the same unit as x10^-6 Ω·m	grade 2014A (datasheet)temperature not statedunit in source x10^-6 Ω.m (printed as 0.045 x10^-6 Ω.m)	—
7	Brinell hardness, plate 12.5 to 40 mm, T651	—	grade 2014Atemper T651form plate, 12.5 to 40 mmstandard BS EN 485-2:2008	—
8	Tensile strength, minimum, plate 12.5 to 40 mm, T651	—	grade 2014Atemper T651form plate, 12.5 to 40 mmstandard BS EN 485-2:2008	—
9	Proof stress, minimum, plate 12.5 to 40 mm, T651	—	grade 2014Atemper T651form plate, 12.5 to 40 mmmeasure proof stress as printed; the page does not name the offset	—
10	Elongation A, minimum, plate 12.5 to 40 mm, T651	—	grade 2014Atemper T651form plate, 12.5 to 40 mmgauge length printed as Elongation A; gauge length not stated	—
11	Tensile strength, minimum, sheet 0.4 to 6 mm, T651	—	grade 2014Atemper T651form sheet, 0.4 to 6 mmstandard BS EN 485-2:2008	—
12	Proof stress, minimum, sheet 0.4 to 6 mm, T651	—	grade 2014Atemper T651form sheet, 0.4 to 6 mmmeasure proof stress as printed; the page does not name the offset	—
13	Tensile strength, minimum, bar T6510 20 to 75 mm	Minimum value printed in a materials datasheet (typical mechanical properties table)	grade alloy 2014 bartemper T6510form bar, 20 to 75 mm diameterunit in source N/mm²	—
14	Yield strength, minimum, bar T6510 20 to 75 mm	Minimum value printed in a materials datasheet (typical mechanical properties table)	grade alloy 2014 bartemper T6510form bar, 20 to 75 mm diameterunit in source N/mm²	—
15	Elongation, minimum, bar T6510 20 to 75 mm	Minimum value printed in a materials datasheet (typical mechanical properties table)	grade alloy 2014 bartemper T6510form bar, 20 to 75 mm diametergauge length 5.65 square root of area, as printed	—
16	Tensile strength, minimum, bar T6/T6510/T6511 25 to 75 mm	—	grade 2014 / 2014Atemper T6, T6510 or T6511form bar, 25 to 75 mm diameterstandard BS EN 755-2	—
17	Proof stress, minimum, bar T6/T6510/T6511 25 to 75 mm	—	grade 2014 / 2014Atemper T6, T6510 or T6511form bar, 25 to 75 mm diameterstandard BS EN 755-2measure proof stress as printed; the page does not name the offset	—
18	Elongation, minimum, bar T6/T6510/T6511 25 to 75 mm	—	grade 2014 / 2014Atemper T6, T6510 or T6511form bar, 25 to 75 mm diameterstandard BS EN 755-2	—
19	Tensile strength, minimum, sheet T4 bare 0.2 to 6.0 mm	Minimum value printed in a materials datasheet (typical mechanical properties table)	grade alloy 2014 sheettemper T4 bareform sheet, 0.2 to 6.0 mmunit in source N/mm²	—
20	Yield strength, minimum, sheet T4 bare 0.2 to 6.0 mm	Minimum value printed in a materials datasheet (typical mechanical properties table)	grade alloy 2014 sheettemper T4 bareform sheet, 0.2 to 6.0 mmunit in source N/mm²	—

Corrosion and compatibility

What happens when it meets other materials and environments.

Corrosion and compatibility
Environment	Concern	What happens
Atmosphere, water and salt	severe	Corrosion resistance is poor, so unclad 2014 needs paint or cladding.¹
Chloride water and sea water	severe	Pitting in chloride water, and severe galvanic attack in sea water.²
Hot forming of 2014-T6	moderate	Hot forming without artificial ageing lowers corrosion resistance.³
Space environment (launch vehicles and spacecraft)	low	NASA says aluminium alloys are relatively insensitive to space-environment degradation.⁴

Corrosion details
#	Environment	Details	Test conditions
1	Atmosphere, water and salt	Aalco rates resistance to atmospheric attack as poor, especially when exposed to water or salt, and advises a lanolin-based protective oil in storage. Wikipedia says the corrosion resistance is particularly poor and that the alloy is often clad with pure aluminium. Smiths calls corrosion resistance average and says the material is often hard anodised, so the datasheets do not agree on the grade of resistance.	basis datasheet and encyclopaedia statements; no exposure test with a corrosion rate was read
2	Chloride water and sea water	NASA's handbook says pitting attack occurs in waters containing chloride or other halogen ions, especially at crevices or stagnant areas. It also says that galvanic coupling with more noble metals generally produces severe attack on aluminium, especially in sea water, and that traces of copper, iron and mercury ions promote localised attack.	basis general statement for aluminium alloys in the NASA handbook; no 2014-specific rate was quoted
3	Hot forming of 2014-T6	NASA says hot forming generally reduces the corrosion resistance of 2014-T6, but artificial ageing after hot forming prevents the susceptibility. Under controlled conditions, strength loss from reheating seldom exceeds 5 percent.	temper 2014-T6process hot forming
4	Space environment (launch vehicles and spacecraft)	The NASA handbook states that aluminium alloys have been used in structural and nonstructural applications in launch vehicles and spacecraft with excellent success, because they are relatively insensitive to degradation in typical space environments. This is a general statement for the alloy family, not a 2014 exposure result.	basis general statement; no 2014 flight exposure or mass-loss data were read in this run

Risks and side effects

Hazards to people, what happens when a cell overheats, and how the material is handled and stored.

For people

The sources give hazard information for processing this alloy, not for the solid metal.

Solid metal: The Russel Metals SDS says aluminium alloys are an article and not hazardous in solid form. Dust and fumes from cutting, grinding, melting and welding are the hazard.
Dust: The same SDS gives an exposure limit of 1 mg/m3 (ACGIH TWA) for aluminium alloy dust.

If it fails

The failure routes in the sources are corrosion in water, cracking in welds, and lost corrosion resistance after hot forming.

Water and salt: NASA describes pitting in chloride water and severe galvanic attack in sea water. The sources give no corrosion rate for 2014 in those conditions.
Welds: Wikipedia says the alloy is difficult to weld because it is subject to cracking.
Hot forming: NASA says hot forming of 2014-T6 lowers corrosion resistance unless the part is artificially aged afterwards.

Handling and storage

Storage: Aalco advises a lanolin-based protective oil in storage.
Fires: Dust and chips can burn. The SDS says to use Class D extinguishing agents or sand on those fires.

Test details
The original wording and numbers from the sources, for readers who want them.

Failure risks

Failure risks
Failure	Trigger and consequence
Pitting and galvanic attack in chloride or sea watercritical severity	Water containing chloride or other halogen ions, crevices or stagnant areas, or contact with more noble metalsNASA says these conditions cause pitting and severe galvanic attack on aluminium, especially in sea water. The sources give no corrosion rate for 2014 in these conditions.
Cracking during weldingmoderate severity	Fusion welding of 2014Wikipedia says the alloy is difficult to weld because it is subject to cracking.
Loss of corrosion resistance after hot forming without ageingmoderate severity	Hot forming of 2014-T6 with no artificial ageing afterwardsNASA says artificial ageing after hot forming prevents the corrosion susceptibility. Strength loss from controlled reheating seldom exceeds 5 percent.

Side effects on surrounding parts

Side effects on surrounding parts
Affects	Effect
Heat spreading and thermal control	NASA says the room-temperature thermal conductivity of 2014 can be up to 30 percent lower than that of electrical-conductor-grade aluminium, so heat transfer depends on temper and composition.

Handling and storage

Aalco advises a lanolin-based protective oil against atmospheric corrosion in storage. It rates brazing and soldering as not recommended, and resistance spot and beam welding as excellent.
Dusts, chips and fines can burn. Aluminium chips, dust and fines in contact with water can generate flammable hydrogen gas. The SDS says to use Class D extinguishing agents or sand on fires involving dusts or chips.

Mitigations

Clad the alloy with pure aluminium, or paint unclad material that is exposed to the elements.

Supply and geography

How common the raw materials are and where they come from.

Aluminium, primary smelter production

Top producers (2025): China 60.8%, India 5.7%, Russia 5.3%, Canada 4.5%, United Arab Emirates 3.6%
Recycling: USGS: in 2025 about 3.6 million tons of aluminum were recovered from purchased scrap in the United States, about 56 % from new scrap and 44 % from old scrap. Old scrap was equivalent to about 28 % of apparent consumption.
Substitutes: USGS: composites can substitute for aluminum in aircraft fuselages and wings.

Documents

Datasheets, safety data sheets, papers and standards you can open.

Documents
Document	Type	Year
Aalco Metals: Aluminium Alloy Commercial Alloy 2014A T651 Sheet and Plate datasheet	datasheet
Smiths High Performance: 2014 / 2014A Aluminium technical datasheet (revision 11.02.2025)	datasheet	2025
Aircraft Materials: Aluminium Alloy 2014 / 2014A technical data sheet	datasheet
Wikipedia: 2014 aluminium alloy	report	2026
BIKAR: EN AW-2014 round bar product page (designation table)	report
NASA MSFC Materials Data Handbook: Aluminum Alloy 2014, 2nd edition (NTRS 19720023885)	report	1972
University of Alabama in Huntsville archive: The production of large tanks for cryogenic fuels (Harpoothian)	report
USGS Mineral Commodity Summaries 2026: Aluminum	report	2026
Russel Metals GHS safety data sheet: Aluminum alloys (April 15, 2019)	sds	2019

Full record

The complete spore, as stored. Free to reuse under CC-BY-4.0. Images keep the licence shown with each one.

Show the full YAML

spore: profile
id: aluminium-2014
spore_version: 0.2
family: aluminium-alloys
name: Aluminium alloy 2014
abbreviation: '2014'
role: high-strength aerospace structural alloy
category: metals
type: aluminium
summary: |
  2014 (also sold as 2014A; UNS A92014, EN AW-2014, W.Nr. 3.1255) is a wrought copper-bearing aluminium alloy (Al-Cu-Mg-Si) used where high strength matters. The Aalco datasheet for 2014A in the T651 temper gives a density of 2.82 g/cm3, a minimum tensile strength of 460 MPa for 12.5 to 40 mm plate, and a thermal conductivity of 138 W/(m·K). Its corrosion resistance is poor: Aalco rates resistance to atmospheric attack as poor, especially in water or salt, and Wikipedia calls it particularly poor, so it is often clad with pure aluminium. A 1960s presentation in the UAH archive says the Saturn cryogenic tanks were fabricated of 2014-T6.
best_for: High-strength structural parts for aerospace and defence, where a 460 MPa minimum tensile strength in T651 plate is needed and the part is clad or painted against corrosion
weakest_at: Corrosion resistance (poor in water and salt, with pitting and galvanic attack in sea water), and welding, which is difficult and prone to cracking
identity:
  formula: 'Al-Cu-Mg-Si wrought alloy (AlCu4SiMg). Composition limits for 2014A in wt% (BS EN 573-3, as printed on Aalco): Cu 3.90 to 5.00, Mn 0.40 to 1.20, Mg 0.20 to 0.80, Si 0.50 to 0.90, Fe max 0.50, Zn max 0.25, Ti max 0.15, Cr max 0.10, Al balance. Smiths gives the same Cu, Mn and Mg ranges.'
  source: aalco-plate
  where: Chemical Composition table, Spec BS EN 573-3:2009, alloy 2014, on the Aalco 2014A T651 sheet and plate datasheet
  designations:
    - system: UNS
      code: A92014
      source: aircraft-2014
      where: UNS line under the alloy 2014 specifications
    - system: EN
      code: '3.1255'
      source: aircraft-2014
      where: Werkstoff Nr. 3.1255 line
    - system: EN name
      code: EN AW-2014
      source: bikar-2014
      where: Material row on the EN AW-2014 round bar product page
    - system: EN name
      code: AlCu4SiMg
      source: aircraft-2014
      where: Chemical name line in the specifications list
    - system: AFNOR
      code: A-U4SG
      source: aircraft-2014
      where: A-U4SG line in the specifications list
    - system: BS
      code: H15
      source: aircraft-2014
      where: BS H15 line in the specifications list
    - system: AMS
      code: '4029'
      note: sheet and plate, T651
      source: aircraft-2014
      where: AMS 4029 line in the specifications list
    - system: AMS
      code: '4121'
      note: bars, rods and wire, T6
      source: aircraft-2014
      where: AMS 4121 line in the specifications list
    - system: ASTM
      code: B 209
      note: sheet and plate
      source: wiki-2014
      where: Standards list, ASTM B 209
    - system: Trade name
      code: 14S
      note: pre-1954 industry designation
      source: wiki-2014
      where: Lead paragraph, sentence on the conventional designation 14S
tags:
  environments:
    - launch
  stresses:
    - extreme-cold
  applications:
    - structures
    - propulsion-and-tanks
    - cryogenic-fuel
properties:
  - benchmark: density
    label: Density, 2014A datasheet
    value: 2.82
    unit: g/cm3
    scope: material
    conditions:
      grade: 2014A (datasheet title; BS EN 573-3 alloy 2014)
      temperature: not stated
    method: Value printed in a stockist datasheet
    status: ground
    source: aalco-plate
    where: Physical Property table, row Density
  - benchmark: elastic_modulus
    label: Modulus of elasticity, 2014A datasheet
    value: 71
    unit: GPa
    scope: material
    conditions:
      grade: 2014A (datasheet)
      temperature: not stated
    method: Value printed in a stockist datasheet
    status: ground
    note: Smiths prints the same 71 GPa. Wikipedia gives 73 GPa as a typical value for 2014, so the figure depends on the source.
    source: aalco-plate
    where: Physical Property table, row Modulus of Elasticity
  - benchmark: thermal_conductivity
    label: Thermal conductivity, 2014A datasheet
    value: 138
    unit: W/(m·K)
    scope: material
    conditions:
      grade: 2014A (datasheet)
      temperature: not stated
    method: Value printed in a stockist datasheet
    status: ground
    note: Smiths prints the same 138 W/m.K. NASA says the room-temperature thermal conductivity of 2014 is up to 30 percent lower than that of electrical-conductor-grade aluminium.
    source: aalco-plate
    where: Physical Property table, row Thermal Conductivity
  - benchmark: cte
    label: Coefficient of thermal expansion, 2014A datasheet
    value: 23
    unit: ppm/K
    scope: material
    conditions:
      grade: 2014A (datasheet)
      temperature: not stated
      unit_in_source: 23 x10^-6 /K
    method: Value printed in a stockist datasheet
    status: ground
    source: aalco-plate
    where: Physical Property table, row Thermal Expansion
  - benchmark: melting_point
    label: Melting point, 2014A datasheet
    value: 535
    unit: °C
    scope: material
    conditions:
      grade: 2014A (datasheet)
      pressure: not stated
    method: Single value printed in a stockist datasheet
    status: ground
    note: NASA gives a melting range of 510 to 638 °C for the same alloy, which contains this value.
    source: aalco-plate
    where: Physical Property table, row Melting Point
  - benchmark: melting_point
    label: Melting range (lower to upper), alloy 2014
    value: 510
    value_high: 638
    bound: range
    unit: °C
    scope: material
    conditions:
      grade: 2014 (NASA handbook)
    method: Range printed in a NASA materials handbook, critical temperatures section
    status: ground
    source: nasa-2014
    where: Section 3.3 Critical Temperatures
  - benchmark: electrical_resistivity
    label: Electrical resistivity, 2014A datasheet
    value: 0.045
    unit: µΩ·m
    scope: material
    conditions:
      grade: 2014A (datasheet)
      temperature: not stated
      unit_in_source: x10^-6 Ω.m (printed as 0.045 x10^-6 Ω.m)
    method: Value printed in a stockist datasheet; µΩ·m is the same unit as x10^-6 Ω·m
    status: ground
    source: aalco-plate
    where: Physical Property table, row Electrical Resistivity
  - benchmark: hardness_brinell
    label: Brinell hardness, plate 12.5 to 40 mm, T651
    value: 138
    unit: HB
    scope: material
    conditions:
      grade: 2014A
      temper: T651
      form: plate, 12.5 to 40 mm
      standard: BS EN 485-2:2008
    method: Value printed in a stockist datasheet
    status: ground
    source: aalco-plate
    where: Mechanical table, Plate 12.5mm to 40mm, row Hardness Brinell
  - benchmark: ultimate_tensile_strength
    label: Tensile strength, minimum, plate 12.5 to 40 mm, T651
    value: 460
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: 2014A
      temper: T651
      form: plate, 12.5 to 40 mm
      standard: BS EN 485-2:2008
    method: Minimum value printed in a stockist datasheet
    status: ground
    source: aalco-plate
    where: Mechanical table, Plate 12.5mm to 40mm, row Tensile Strength
  - benchmark: yield_strength
    label: Proof stress, minimum, plate 12.5 to 40 mm, T651
    value: 400
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: 2014A
      temper: T651
      form: plate, 12.5 to 40 mm
      measure: proof stress as printed; the page does not name the offset
    method: Minimum value printed in a stockist datasheet
    status: ground
    source: aalco-plate
    where: Mechanical table, Plate 12.5mm to 40mm, row Proof Stress
  - benchmark: elongation
    label: Elongation A, minimum, plate 12.5 to 40 mm, T651
    value: 6
    bound: lower
    unit: '%'
    scope: material
    conditions:
      grade: 2014A
      temper: T651
      form: plate, 12.5 to 40 mm
      gauge_length: printed as Elongation A; gauge length not stated
    method: Minimum value printed in a stockist datasheet
    status: ground
    source: aalco-plate
    where: Mechanical table, Plate 12.5mm to 40mm, row Elongation A
  - benchmark: ultimate_tensile_strength
    label: Tensile strength, minimum, sheet 0.4 to 6 mm, T651
    value: 440
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: 2014A
      temper: T651
      form: sheet, 0.4 to 6 mm
      standard: BS EN 485-2:2008
    method: Minimum value printed in a stockist datasheet
    status: ground
    source: aalco-plate
    where: Mechanical table, Sheet 0.4mm to 6mm, row Tensile Strength
  - benchmark: yield_strength
    label: Proof stress, minimum, sheet 0.4 to 6 mm, T651
    value: 390
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: 2014A
      temper: T651
      form: sheet, 0.4 to 6 mm
      measure: proof stress as printed; the page does not name the offset
    method: Minimum value printed in a stockist datasheet
    status: ground
    source: aalco-plate
    where: Mechanical table, Sheet 0.4mm to 6mm, row Proof Stress
  - benchmark: ultimate_tensile_strength
    label: Tensile strength, minimum, bar T6510 20 to 75 mm
    value: 480
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: alloy 2014 bar
      temper: T6510
      form: bar, 20 to 75 mm diameter
      unit_in_source: N/mm²
    method: Minimum value printed in a materials datasheet (typical mechanical properties table)
    status: ground
    source: aircraft-2014
    where: Typical Mechanical Properties table, Alloy 2014 Bar, T6510, diameter 20-75 mm, Tensile Strength min
  - benchmark: yield_strength
    label: Yield strength, minimum, bar T6510 20 to 75 mm
    value: 435
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: alloy 2014 bar
      temper: T6510
      form: bar, 20 to 75 mm diameter
      unit_in_source: N/mm²
    method: Minimum value printed in a materials datasheet (typical mechanical properties table)
    status: ground
    source: aircraft-2014
    where: Typical Mechanical Properties table, Alloy 2014 Bar, T6510, diameter 20-75 mm, Yield Strength min
  - benchmark: elongation
    label: Elongation, minimum, bar T6510 20 to 75 mm
    value: 7
    bound: lower
    unit: '%'
    scope: material
    conditions:
      grade: alloy 2014 bar
      temper: T6510
      form: bar, 20 to 75 mm diameter
      gauge_length: 5.65 square root of area, as printed
    method: Minimum value printed in a materials datasheet (typical mechanical properties table)
    status: ground
    source: aircraft-2014
    where: Typical Mechanical Properties table, Alloy 2014 Bar, T6510, diameter 20-75 mm, Elongation on 5.65 min
  - benchmark: ultimate_tensile_strength
    label: Tensile strength, minimum, bar T6/T6510/T6511 25 to 75 mm
    value: 460
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: 2014 / 2014A
      temper: T6, T6510 or T6511
      form: bar, 25 to 75 mm diameter
      standard: BS EN 755-2
    method: Minimum value printed in a stockist datasheet
    status: ground
    source: smiths-2014
    where: Mechanical Properties box, page 2, row Tensile Strength
  - benchmark: yield_strength
    label: Proof stress, minimum, bar T6/T6510/T6511 25 to 75 mm
    value: 420
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: 2014 / 2014A
      temper: T6, T6510 or T6511
      form: bar, 25 to 75 mm diameter
      standard: BS EN 755-2
      measure: proof stress as printed; the page does not name the offset
    method: Minimum value printed in a stockist datasheet
    status: ground
    source: smiths-2014
    where: Mechanical Properties box, page 2, row Proof Stress
  - benchmark: elongation
    label: Elongation, minimum, bar T6/T6510/T6511 25 to 75 mm
    value: 7
    bound: lower
    unit: '%'
    scope: material
    conditions:
      grade: 2014 / 2014A
      temper: T6, T6510 or T6511
      form: bar, 25 to 75 mm diameter
      standard: BS EN 755-2
    method: Minimum value printed in a stockist datasheet
    status: ground
    source: smiths-2014
    where: Mechanical Properties box, page 2, row Elongation
  - benchmark: ultimate_tensile_strength
    label: Tensile strength, minimum, sheet T4 bare 0.2 to 6.0 mm
    value: 400
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: alloy 2014 sheet
      temper: T4 bare
      form: sheet, 0.2 to 6.0 mm
      unit_in_source: N/mm²
    method: Minimum value printed in a materials datasheet (typical mechanical properties table)
    status: ground
    source: aircraft-2014
    where: Typical Mechanical Properties table, Alloy 2014 Sheet, T4 Bare, 0.2-6.0 mm, Tensile Strength min
  - benchmark: yield_strength
    label: Yield strength, minimum, sheet T4 bare 0.2 to 6.0 mm
    value: 225
    bound: lower
    unit: MPa
    scope: material
    conditions:
      grade: alloy 2014 sheet
      temper: T4 bare
      form: sheet, 0.2 to 6.0 mm
      unit_in_source: N/mm²
    method: Minimum value printed in a materials datasheet (typical mechanical properties table)
    status: ground
    source: aircraft-2014
    where: Typical Mechanical Properties table, Alloy 2014 Sheet, T4 Bare, 0.2-6.0 mm, Yield Strength min
corrosion:
  - environment: Atmosphere, water and salt
    headline: Corrosion resistance is poor, so unclad 2014 needs paint or cladding.
    effect: Aalco rates resistance to atmospheric attack as poor, especially when exposed to water or salt, and advises a lanolin-based protective oil in storage. Wikipedia says the corrosion resistance is particularly poor and that the alloy is often clad with pure aluminium. Smiths calls corrosion resistance average and says the material is often hard anodised, so the datasheets do not agree on the grade of resistance.
    rating: severe
    conditions:
      basis: datasheet and encyclopaedia statements; no exposure test with a corrosion rate was read
    source: aalco-plate
    where: Corrosion Resistance section (Aalco); Wikipedia lead paragraph read for the cladding statement
  - environment: Chloride water and sea water
    headline: Pitting in chloride water, and severe galvanic attack in sea water.
    effect: NASA's handbook says pitting attack occurs in waters containing chloride or other halogen ions, especially at crevices or stagnant areas. It also says that galvanic coupling with more noble metals generally produces severe attack on aluminium, especially in sea water, and that traces of copper, iron and mercury ions promote localised attack.
    rating: severe
    conditions:
      basis: general statement for aluminium alloys in the NASA handbook; no 2014-specific rate was quoted
    source: nasa-2014
    where: Section 10.1 General, Corrosion Resistance and Protection
  - environment: Hot forming of 2014-T6
    headline: Hot forming without artificial ageing lowers corrosion resistance.
    effect: NASA says hot forming generally reduces the corrosion resistance of 2014-T6, but artificial ageing after hot forming prevents the susceptibility. Under controlled conditions, strength loss from reheating seldom exceeds 5 percent.
    rating: moderate
    conditions:
      temper: 2014-T6
      process: hot forming
    source: nasa-2014
    where: Section 5.212 Hot Forming
  - environment: Space environment (launch vehicles and spacecraft)
    headline: NASA says aluminium alloys are relatively insensitive to space-environment degradation.
    effect: The NASA handbook states that aluminium alloys have been used in structural and nonstructural applications in launch vehicles and spacecraft with excellent success, because they are relatively insensitive to degradation in typical space environments. This is a general statement for the alloy family, not a 2014 exposure result.
    rating: low
    conditions:
      basis: general statement; no 2014 flight exposure or mass-loss data were read in this run
    source: nasa-2014
    where: Section 6.1 General, Space Environment Effects
risks:
  hazards:
    - text: The Russel Metals SDS for aluminium alloys (a generic sheet, not specific to 2014, dated April 15, 2019) says aluminium and its alloys are an article and not hazardous in solid form. Cutting, milling, grinding, melting and welding can emit hazardous materials. For those emitted products the sheet lists flammable solid category 1 (chips or powder form), carcinogenicity category 2 and respiratory sensitiser category 1.
      ghs: []
      source: russel-sds
      where: Section 2 Hazardous Ingredients, classification and GHS table
    - text: The same SDS gives an exposure limit of 1 mg/m3 (ACGIH TWA) for aluminium and aluminium alloy dusts.
      ghs: []
      source: russel-sds
      where: Exposure controls, control parameters
  failure_risks:
    - mode: Pitting and galvanic attack in chloride or sea water
      trigger: Water containing chloride or other halogen ions, crevices or stagnant areas, or contact with more noble metals
      consequence: NASA says these conditions cause pitting and severe galvanic attack on aluminium, especially in sea water. The sources give no corrosion rate for 2014 in these conditions.
      severity: critical
      source: nasa-2014
      where: Section 10.1 General
    - mode: Cracking during welding
      trigger: Fusion welding of 2014
      consequence: Wikipedia says the alloy is difficult to weld because it is subject to cracking.
      severity: moderate
      source: wiki-2014
      where: Lead paragraph
    - mode: Loss of corrosion resistance after hot forming without ageing
      trigger: Hot forming of 2014-T6 with no artificial ageing afterwards
      consequence: NASA says artificial ageing after hot forming prevents the corrosion susceptibility. Strength loss from controlled reheating seldom exceeds 5 percent.
      severity: moderate
      source: nasa-2014
      where: Section 5.212 Hot Forming
  side_effects:
    - text: NASA says the room-temperature thermal conductivity of 2014 can be up to 30 percent lower than that of electrical-conductor-grade aluminium, so heat transfer depends on temper and composition.
      affects: Heat spreading and thermal control
      source: nasa-2014
      where: Section 9.212 Thermal conductivity
  handling:
    - text: Aalco advises a lanolin-based protective oil against atmospheric corrosion in storage. It rates brazing and soldering as not recommended, and resistance spot and beam welding as excellent.
      source: aalco-plate
      where: Corrosion Resistance and Weldability sections
    - text: Dusts, chips and fines can burn. Aluminium chips, dust and fines in contact with water can generate flammable hydrogen gas. The SDS says to use Class D extinguishing agents or sand on fires involving dusts or chips.
      source: russel-sds
      where: Fire-fighting measures, suitable extinguishing media and specific hazards
  mitigations:
    - text: Clad the alloy with pure aluminium, or paint unclad material that is exposed to the elements.
      source: wiki-2014
      where: Lead paragraph, corrosion sentence
uses:
  - application: structures
    device: Aircraft structural parts
    example: Aircraft Materials says alloy 2014 is commonly used in many aerospace structural applications because of its high strength, and also lists military vehicles, bridges and weapons. Aalco describes it as a high-strength component alloy for aerospace and defence.
    source: aircraft-2014
    where: Introduction paragraph; Aalco use statement is on the aalco-plate datasheet (Machinability and typical applications)
  - application: propulsion-and-tanks
    device: Saturn cryogenic propellant tanks
    example: A presentation by a Douglas engineer, held in the University of Alabama in Huntsville archive, says the NASA/Douglas Saturn tanks for cryogenic fuels were fabricated of 2014-T6 aluminium alloy, and that many of their structural features were first developed for the Thor booster.
    source: uah-harpoothian
    where: Archive description (item 10274), abstract paragraph
  - application: structures
    device: Motorsport uprights, hydraulic parts and fasteners
    example: Smiths High Performance lists motorsport uprights, hydraulics, fasteners and aircraft fuselages among typical applications, and says the alloy is highly suitable where high strength and fatigue resistance are required.
    source: smiths-2014
    where: Applications box, page 1
supply:
  - subject: Aluminium, primary smelter production
    producers:
      - country: China
        share_percent: 60.8
        year: 2025
      - country: India
        share_percent: 5.7
        year: 2025
      - country: Russia
        share_percent: 5.3
        year: 2025
      - country: Canada
        share_percent: 4.5
        year: 2025
      - country: United Arab Emirates
        share_percent: 3.6
        year: 2025
    critical_lists: []
    recycling: 'USGS: in 2025 about 3.6 million tons of aluminum were recovered from purchased scrap in the United States, about 56 % from new scrap and 44 % from old scrap. Old scrap was equivalent to about 28 % of apparent consumption.'
    substitutes:
      - 'USGS: composites can substitute for aluminum in aircraft fuselages and wings.'
    source: usgs-aluminum
    where: World Smelter Production and Capacity table, 2025e column (China 45,000; India 4,200; Russia 3,900; Canada 3,300; UAE 2,700; world total 74,000, thousand t). Shares were calculated by Space Mushroom from those tonnes and rounded to 0.1 %. Recycling and Substitutes sections.
documents:
  - title: 'Aalco Metals: Aluminium Alloy Commercial Alloy 2014A T651 Sheet and Plate datasheet'
    type: datasheet
    url: https://www.aalco.co.uk/datasheets/Aluminium-Alloy-2014A-T651-Sheet-and-Plate_295.ashx
  - title: 'Smiths High Performance: 2014 / 2014A Aluminium technical datasheet (revision 11.02.2025)'
    type: datasheet
    url: https://www.smithshp.com/assets/pdf/aluminium/commercial-aluminium/2014-aluminium-english.pdf
    year: 2025
  - title: 'Aircraft Materials: Aluminium Alloy 2014 / 2014A technical data sheet'
    type: datasheet
    url: https://aircraftmaterials.com/data/aluminium/2014a.html
  - title: 'Wikipedia: 2014 aluminium alloy'
    type: report
    url: https://en.wikipedia.org/wiki/2014_aluminium_alloy
    year: 2026
  - title: 'BIKAR: EN AW-2014 round bar product page (designation table)'
    type: report
    url: https://my.bikar.com/en_US/products/329_003-329-003-2
  - title: 'NASA MSFC Materials Data Handbook: Aluminum Alloy 2014, 2nd edition (NTRS 19720023885)'
    type: report
    url: https://ntrs.nasa.gov/citations/19720023885
    year: 1972
  - title: 'University of Alabama in Huntsville archive: The production of large tanks for cryogenic fuels (Harpoothian)'
    type: report
    url: https://digitalprojects.uah.edu/items/show/10274
  - title: 'USGS Mineral Commodity Summaries 2026: Aluminum'
    type: report
    url: https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-aluminum.pdf
    year: 2026
  - title: 'Russel Metals GHS safety data sheet: Aluminum alloys (April 15, 2019)'
    type: sds
    url: https://www.russelmetals.com/wp-content/uploads/sds-aluminum-alloys.pdf
    year: 2019
gaps:
  - 'Critical-mineral listing for aluminium was not read in this run: the USGS aluminum summary did not print a critical-minerals entry, so critical_lists is empty.'
  - Stress-corrosion cracking, fatigue, fracture toughness and cryogenic strength of 2014 were not entered. The NASA 1972 handbook has these data, but its scanned text is too noisy to copy values from with confidence.
  - The ASM alloy digest for 2014 was blocked by a bot check and was not read. Its values are not used.
  - No 2014 flight outgassing, total-mass-loss, atomic-oxygen erosion or cold-welding result was found. No LDEF or space-exposure data were read for this alloy.
  - No flight or modern launch-vehicle record for 2014 was found. The only space use is the Saturn cryogenic tank statement in a 1960s-era archive presentation.
  - Electrical conductivity of 2014 (Wikipedia gives 34 to 50 % IACS, with no temper stated) and the Wikipedia ranges for tensile strength and thermal conductivity were not entered, because they are not tied to one temper or form.
  - The Russel Metals SDS is a generic aluminium-alloy sheet, not one for 2014. Its hazard text is used only as a general statement, and no GHS hazard codes are printed in it. No PubChem record was read (the page is client-rendered).
  - Radiation effects, emissivity and regolith abundance of aluminium were not looked up.
  - Hardness is recorded under the name hardness_brinell, which is not in the canonical property file.
  - Alclad 2014, which Wikipedia says is often used, is a different product and was not profiled.
sources:
  aalco-plate:
    title: 'Aalco Metals: Aluminium Alloy, Commercial Alloy 2014A T651 Sheet and Plate (datasheet)'
    url: https://www.aalco.co.uk/datasheets/Aluminium-Alloy-2014A-T651-Sheet-and-Plate_295.ashx
    kind: datasheet
    license: Stockist datasheet (cited, not reproduced); Aalco notes the data may not reflect the latest standards
  smiths-2014:
    title: Smiths High Performance, 2014 / 2014A Aluminium technical datasheet (revision 11.02.2025)
    url: https://www.smithshp.com/assets/pdf/aluminium/commercial-aluminium/2014-aluminium-english.pdf
    year: 2025
    kind: datasheet
    license: Stockist datasheet (cited, not reproduced)
  aircraft-2014:
    title: Aircraft Materials, Aluminium Alloy 2014 / 2014A technical data sheet
    url: https://aircraftmaterials.com/data/aluminium/2014a.html
    kind: datasheet
    license: Supplier web page (cited, not reproduced)
  wiki-2014:
    title: Wikipedia, 2014 aluminium alloy
    url: https://en.wikipedia.org/wiki/2014_aluminium_alloy
    year: 2026
    kind: web
    license: CC BY-SA 4.0 (cited, not reproduced)
  bikar-2014:
    title: BIKAR, EN AW-2014 round bar product page with material designation table
    url: https://my.bikar.com/en_US/products/329_003-329-003-2
    kind: web
    license: Supplier web page (cited, not reproduced)
  nasa-2014:
    title: 'NASA MSFC, Materials Data Handbook: Aluminum Alloy 2014 (2nd edition, May 1972), prepared under a NASA contract'
    id: NTRS 19720023885
    url: https://ntrs.nasa.gov/citations/19720023885
    year: 1972
    kind: report
    license: NASA public document (cited, not reproduced)
  uah-harpoothian:
    title: The production of large tanks for cryogenic fuels, Harpoothian, UAH Archives, Special Collections and Digital Initiatives (item 10274)
    url: https://digitalprojects.uah.edu/items/show/10274
    kind: report
    license: University archive description (cited, not reproduced)
  usgs-aluminum:
    title: 'USGS Mineral Commodity Summaries 2026: Aluminum'
    id: USGS MCS 2026
    url: https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-aluminum.pdf
    year: 2026
    kind: report
    license: public domain (USGS)
  russel-sds:
    title: Russel Metals GHS safety data sheet, Aluminum alloys (April 15, 2019)
    url: https://www.russelmetals.com/wp-content/uploads/sds-aluminum-alloys.pdf
    year: 2019
    kind: datasheet
    license: Manufacturer safety data sheet (cited, not reproduced)
license: CC-BY-4.0
updated: '2026-10-26'
review:
  status: draft
  method: assistant
  checked_values: 21
  unreachable: 2
  caveats: 5
  note: 'Values were read by an AI assistant on 2026-10-26 from the pages named in each entry. Two sources were unreachable: the ASM alloy digest (bot check) and PubChem (client-rendered page). Caveats: the 2014A datasheet values are for the T651 temper and BS EN 485-2 limits; the bar and sheet minimums from Aircraft Materials and Smiths are for other forms; the NASA handbook is from 1972 and its text was scanned, so only clearly printed values were used; the datasheets disagree on corrosion grade and Young''s modulus (71 against 73 GPa); the Russel SDS is generic for aluminium alloys.'
story:
  risk_groups:
    - title: For people
      lead: The sources give hazard information for processing this alloy, not for the solid metal.
      level: 1
      verdict: Low in solid form
      points:
        - label: Solid metal
          line: The Russel Metals SDS says aluminium alloys are an article and not hazardous in solid form. Dust and fumes from cutting, grinding, melting and welding are the hazard.
        - label: Dust
          line: The same SDS gives an exposure limit of 1 mg/m3 (ACGIH TWA) for aluminium alloy dust.
    - title: If it fails
      lead: The failure routes in the sources are corrosion in water, cracking in welds, and lost corrosion resistance after hot forming.
      points:
        - label: Water and salt
          line: NASA describes pitting in chloride water and severe galvanic attack in sea water. The sources give no corrosion rate for 2014 in those conditions.
        - label: Welds
          line: Wikipedia says the alloy is difficult to weld because it is subject to cracking.
        - label: Hot forming
          line: NASA says hot forming of 2014-T6 lowers corrosion resistance unless the part is artificially aged afterwards.
    - title: Handling and storage
      points:
        - label: Storage
          line: Aalco advises a lanolin-based protective oil in storage.
        - label: Fires
          line: Dust and chips can burn. The SDS says to use Class D extinguishing agents or sand on those fires.
  why: '2014 is a copper-bearing aluminium alloy chosen for high strength and fatigue resistance. The Aalco 2014A datasheet in the T651 temper gives a minimum tensile strength of 460 MPa for 12.5 to 40 mm plate, a density of 2.82 g/cm3 and a thermal conductivity of 138 W/(m·K). Its weak point is corrosion: Aalco rates its resistance to atmospheric attack as poor, especially in water or salt, so it is often clad or painted. A presentation in the UAH archive says the Saturn cryogenic tanks were made of 2014-T6.'
  uses:
    - where: Aerospace structures
      line: Aircraft Materials describes 2014 as commonly used in many aerospace structural applications. Smiths lists motorsport uprights, hydraulic parts and fasteners among its typical uses.
    - where: Launch vehicle tanks
      line: A presentation in the UAH archive says the Saturn tanks for cryogenic fuels were fabricated of 2014-T6 aluminium alloy, and that many of their structural features were first developed for the Thor booster.
  can_do:
    - label: Carry load
      value: 460 MPa minimum tensile
      line: The 2014A T651 plate from 12.5 to 40 mm has a minimum tensile strength of 460 MPa, a minimum proof stress of 400 MPa and a minimum elongation of 6 %.
    - label: Carry heat
      value: 138 W/(m·K)
      benchmark: thermal_conductivity
      line: Thermal conductivity is 138 W/(m·K) on the Aalco datasheet. NASA says the room-temperature conductivity of 2014 can be up to 30 percent lower than that of electrical-conductor-grade aluminium.
    - label: Weight
      value: 2.82 g/cm3
      benchmark: density
      line: Density is 2.82 g/cm3 on the Aalco datasheet, and the Smiths datasheet prints the same figure.
    - label: Melting
      value: 535 °C
      benchmark: melting_point
      line: The datasheet gives a melting point of 535 °C. NASA gives a melting range of 510 to 638 °C for the alloy.
    - label: Sheet strength by temper
      value: 440 MPa T651 against 400 MPa T4
      line: A T651 sheet from 0.4 to 6 mm has a minimum tensile strength of 440 MPa. The T4 bare sheet from 0.2 to 6.0 mm has a minimum of 400 MPa and a minimum yield strength of 225 MPa.
  compare: 'The Smiths datasheet gives the same 460 MPa minimum tensile class for bar in T6, T6510 and T6511 from 25 to 75 mm, and Aircraft Materials gives 480 MPa for T6510 bar from 20 to 75 mm. Temper changes strength a lot: T4 sheet is 400 MPa and T6 sheet is 440 MPa minimum. The figures come from different datasheets and product forms, so read the rows as examples, not as a ranking against other aluminium profiles.'
  compare_rows:
    - label: Density
      benchmark: density
    - label: Thermal conductivity
      benchmark: thermal_conductivity
    - label: Thermal expansion
      benchmark: cte
  handling:
    - Specify the temper and product form. Minimum strength depends on both, and the T4 sheet minimum is 400 MPa against 440 MPa for T651 sheet.
    - Protect unclad material with paint, cladding or lanolin-based oil in storage, because corrosion resistance is poor.
    - Do not fusion-weld without a specialist process. Wikipedia says the alloy is subject to cracking, and Aalco rates oxygen and inert-gas welding as not recommended.
    - Control dust and chips from grinding and machining. They can burn and, when wet, release hydrogen.
  good_for:
    - 'High-strength machined parts: 460 MPa minimum tensile strength in 12.5 to 40 mm T651 plate.'
    - Aerospace structures and cryogenic propellant tanks, according to the sources cited.
    - 'Machining: Smiths calls machinability excellent and Aalco calls it very good.'
  watch_out:
    - 'Corrosion: poor resistance in water and salt, with pitting and galvanic attack, so clad or paint the alloy.'
    - 'Welding: difficult and prone to cracking. Aalco rates resistance spot and beam welding as excellent, and does not recommend oxygen or inert-gas welding.'
    - Hot forming without artificial ageing lowers corrosion resistance.
    - 'The datasheets disagree on corrosion grade: Aalco says poor, Smiths says average.'
    - No 2014 flight outgassing, erosion or cold-welding data were read in this run.
  verdict: 2014 is a high-strength copper-bearing aluminium alloy, with a 460 MPa minimum tensile strength in T651 plate, and it was used for Saturn cryogenic tanks according to the UAH archive. It corrodes readily in water and salt and is difficult to weld, so it needs cladding or paint. This profile has no 2014 flight-exposure data, fatigue values or toughness values.
  recipe:
    line: 'Wrought Al-Cu-Mg-Si alloy (AlCu4SiMg). Composition limits from the BS EN 573-3 table on the Aalco 2014A datasheet: copper 3.90 to 5.00 wt%, manganese 0.40 to 1.20, magnesium 0.20 to 0.80, silicon 0.50 to 0.90, with iron, zinc, titanium and chromium at their maxima and aluminium the balance. It is supplied in the fully heat-treated condition, solution heat-treated and artificially aged (Aalco), and is extruded and forged in practice (Wikipedia).'
    parts:
      - name: Aluminium
        symbol: Al
        share_note: balance
        role: Matrix of the alloy.
      - name: Copper
        symbol: Cu
        share_percent: 3.9
        share_high: 5
        role: Main alloying element, which gives the alloy its precipitation-hardening strength.
      - name: Manganese
        symbol: Mn
        share_percent: 0.4
        share_high: 1.2
        role: Alloying element.
      - name: Magnesium
        symbol: Mg
        share_percent: 0.2
        share_high: 0.8
        role: Alloying element.
      - name: Silicon
        symbol: Si
        share_percent: 0.5
        share_high: 0.9
        role: Alloying element, 2014A has slightly less iron and silicon than 2014 (Smiths).

References

Every number above carries a reference number. Click one to see the source and where in it the value comes from.

References
Source	Type	Year	Used for
Aalco Metals: Aluminium Alloy, Commercial Alloy 2014A T651 Sheet and Plate (datasheet)	datasheet		15 values
Smiths High Performance, 2014 / 2014A Aluminium technical datasheet (revision 11.02.2025)	datasheet	2025	4 values
Aircraft Materials, Aluminium Alloy 2014 / 2014A technical data sheet	datasheet		6 values
Wikipedia, 2014 aluminium alloy	web	2026	2 values
BIKAR, EN AW-2014 round bar product page with material designation table	web		0 values
NASA MSFC, Materials Data Handbook: Aluminum Alloy 2014 (2nd edition, May 1972), prepared under a NASA contract	report	1972	7 values
The production of large tanks for cryogenic fuels, Harpoothian, UAH Archives, Special Collections and Digital Initiatives (item 10274)	report		1 value
USGS Mineral Commodity Summaries 2026: Aluminum	report	2026	1 value
Russel Metals GHS safety data sheet, Aluminum alloys (April 15, 2019)	datasheet	2019	3 values

References
Identity
Formula	Al-Cu-Mg-Si wrought alloy (AlCu4SiMg). Composition limits for 2014A in wt% (BS EN 573-3, as printed on Aalco): Cu 3.90 to 5.00, Mn 0.40 to 1.20, Mg 0.20 to 0.80, Si 0.50 to 0.90, Fe max 0.50, Zn max 0.25, Ti max 0.15, Cr max 0.10, Al balance. Smiths gives the same Cu, Mn and Mg ranges.
Role	high-strength aerospace structural alloy
Benchmarks	21

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