Aluminium-magnesium alloys (5XXX series) 5XXX

spore: profile
id: aluminium-5xxx
spore_version: 0.2
family: aluminium-alloys
name: Aluminium-magnesium alloys (5XXX series)
abbreviation: 5XXX
role: structural alloy
category: metals
type: aluminium
summary: >
  The 5XXX series are wrought aluminium alloys whose main addition is magnesium. They are not hardened by heat treatment but by the magnesium
  dissolved in the metal and by cold work. This profile keeps three alloys apart: 5052 (2.2 to 2.8 wt% Mg), 5083 (4.0 to 4.9 wt% Mg) and 5086
  (3.5 to 4.5 wt% Mg). NASA lists 5052-H32 among spacecraft structural aluminium alloys and 5052 foil is the usual honeycomb core of sandwich panels;
  an open recycling study found hard-drive platters made of 5XXX aluminium under a 10 micrometre nickel layer.
best_for: "Welded, corrosion-resistant sheet and plate at moderate strength (5083 is sold for ship building and pressure vessels)"
weakest_at: "Strength per alloy is modest next to heat-treated 6061, and 5083 is not recommended above 65 °C because of grain-boundary attack"
identity:
  formula: "Al-Mg alloys, wt% limits per alloy. 5052: Mg 2.20 to 2.80, Cr 0.15 to 0.35, Si max 0.25, Fe max 0.40, Cu max 0.10, Mn max 0.10, Zn max 0.10, Al 95.7 to 97.7 (remainder). 5083: Mg 4.0 to 4.9, Mn 0.4 to 1.0, Cr 0.050 to 0.25, Si 0 to 0.4, Fe 0 to 0.4, Zn 0 to 0.25, Ti 0 to 0.15, Cu 0 to 0.1, Al 92.4 to 95.6. 5086: Mg 3.5 to 4.5, Mn 0.2 to 0.7, Cr 0.050 to 0.25, Fe 0 to 0.5, Si 0 to 0.4, Zn 0 to 0.25, Ti 0 to 0.15, Cu 0 to 0.1, Al 93 to 96.3"
  source: clinton-5052h32
  where: "5052: Component Elements table of the 5052-H32 datasheet (Aluminum Association composition, not for design). 5083 and 5086: Alloy composition lists on the MakeItFrom 5083-O and 5086-H32 pages (permitted ranges under applicable standards); 5083 Mg range also on the Dinco H116 datasheet"
tags:
  environments: [launch]
  stresses: [extreme-cold]
  applications: [structures, propulsion-and-tanks]
properties:
  - benchmark: density
    label: Density, 5052-H32
    value: 2.68
    unit: g/cm3
    scope: material
    conditions: {alloy: "5052", temper: "H32", basis: "Aluminum Association typical value, marked NOT FOR DESIGN", temperature: "not stated"}
    method: Typical value listed in a datasheet (Clinton Aluminum copy of the ASM-style sheet)
    status: ground
    source: clinton-5052h32
    where: Physical Properties table, row Density
  - benchmark: yield_strength
    label: Tensile yield strength, 5052-H32
    value: 193
    unit: MPa
    scope: material
    conditions: {alloy: "5052", temper: "H32", basis: "Aluminum Association typical value, marked NOT FOR DESIGN", temperature: "not stated", product_form: "not stated"}
    method: Typical value listed in a datasheet
    status: ground
    source: clinton-5052h32
    where: Mechanical Properties table, row Tensile Strength, Yield
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, 5052-H32
    value: 228
    unit: MPa
    scope: material
    conditions: {alloy: "5052", temper: "H32", basis: "Aluminum Association typical value, marked NOT FOR DESIGN", temperature: "not stated"}
    method: Typical value listed in a datasheet
    status: ground
    source: clinton-5052h32
    where: Mechanical Properties table, row Tensile Strength, Ultimate
  - benchmark: elongation
    label: Elongation at break, 5052-H32, 1.59 mm thick
    value: 12
    unit: "%"
    scope: material
    conditions: {alloy: "5052", temper: "H32", specimen: "thickness 1.59 mm (0.0625 in)", basis: "Aluminum Association typical value", note: "the same table lists 18 % for a 12.7 mm (0.500 in) diameter specimen, so elongation depends on specimen size"}
    method: Typical value listed in a datasheet
    status: ground
    source: clinton-5052h32
    where: Mechanical Properties table, row Elongation at Break
  - benchmark: elastic_modulus
    label: Modulus of elasticity, 5052-H32
    value: 70.3
    unit: GPa
    scope: material
    conditions: {alloy: "5052", temper: "H32", basis: "average of tension and compression; compression modulus is about 2 % greater than tensile (datasheet comment)", type: "Aluminum Association typical value"}
    method: Typical value listed in a datasheet
    status: ground
    source: clinton-5052h32
    where: Mechanical Properties table, row Modulus of Elasticity
  - benchmark: fatigue_strength
    label: Fatigue strength at 500,000,000 cycles, 5052-H32
    value: 117
    unit: MPa
    scope: material
    conditions: {alloy: "5052", temper: "H32", loading: "completely reversed stress", test: "RR Moore machine and specimen", cycles: "5.00e+8"}
    method: Value listed in a datasheet
    status: ground
    source: clinton-5052h32
    where: Mechanical Properties table, row Fatigue Strength
  - benchmark: thermal_conductivity
    label: Thermal conductivity, 5052-H32
    value: 138
    unit: W/(m·K)
    scope: material
    conditions: {alloy: "5052", temper: "H32", temperature: "77 °F", basis: "Aluminum Association typical value"}
    method: Typical value listed in a datasheet
    status: ground
    source: clinton-5052h32
    where: Thermal Properties table, row Thermal Conductivity
  - benchmark: melting_range
    label: Melting range, 5052 (solidus to liquidus)
    value: 607.2
    value_high: 649
    bound: range
    unit: °C
    scope: material
    conditions: {alloy: "5052", basis: "typical range for the typical composition of wrought products 1/4 inch thickness or greater"}
    method: Typical range listed in a datasheet (solidus 607.2 °C, liquidus 649 °C)
    status: ground
    source: clinton-5052h32
    where: Thermal Properties table, rows Melting Point, Solidus and Liquidus
  - benchmark: yield_strength
    label: Tensile yield strength, 5052-O (annealed)
    value: 89.6
    unit: MPa
    scope: material
    conditions: {alloy: "5052", temper: "O (annealed)", unit_in_source: "13 ksi", conversion: "1 ksi = 6.8948 MPa, calculated by Space Mushroom", basis: "bulk-material datasheet values quoted by NASA from two supplier datasheets"}
    method: Table of datasheet values in a NASA technical memorandum
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, row O (annealed), column Yield
  - benchmark: yield_strength
    label: Tensile yield strength, 5052-H38
    value: 255
    unit: MPa
    scope: material
    conditions: {alloy: "5052", temper: "H38", unit_in_source: "37 ksi", conversion: "1 ksi = 6.8948 MPa, rounded to 255 MPa by Space Mushroom", basis: "bulk-material datasheet values quoted by NASA from two supplier datasheets"}
    method: Table of datasheet values in a NASA technical memorandum
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, row H38, column Yield
  - benchmark: elongation
    label: Elongation, 5052-O (annealed)
    value: 25
    unit: "%"
    scope: material
    conditions: {alloy: "5052", temper: "O (annealed)", basis: "bulk-material datasheet values quoted by NASA", specimen: "not stated"}
    method: Table of datasheet values in a NASA technical memorandum
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, row O (annealed), column Elongation
  - benchmark: elongation
    label: Elongation, 5052-H38
    value: 7
    unit: "%"
    scope: material
    conditions: {alloy: "5052", temper: "H38", basis: "bulk-material datasheet values quoted by NASA", specimen: "not stated"}
    method: Table of datasheet values in a NASA technical memorandum
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, row H38, column Elongation
  - benchmark: elastic_modulus
    label: Elastic modulus of 5052-H39 honeycomb foil
    value: 57.2
    unit: GPa
    scope: material
    conditions: {alloy: "5052", temper: "H39", form: "foil 0.0016 in thick, rolling and transverse samples", temperature: "room temperature", unit_in_source: "8.3 Msi, 1 Msi = 6.8948 GPa, converted by Space Mushroom", uncertainty_in_source: "plus or minus 0.3 Msi, pooled over all aged and unaged samples"}
    method: Tensile tests of foil with photogrammetry strain measurement, NASA Glenn
    status: ground
    note: NASA says datasheets usually cite 10 Msi for bulk 5052; the foil value is lower and may reflect the thin-foil sample size.
    source: nasa-tm-2018-219753
    where: Page 4 text and page 6 text (modulus 8.3±0.3 Msi)
  - benchmark: failure_strain
    label: Strain to failure of 5052-H39 honeycomb foil
    value: 1.6
    unit: "%"
    scope: material
    conditions: {alloy: "5052", temper: "H39", form: "foil 0.0016 in thick", temperature: "room temperature", range_in_source: "0.5 to 3.4 percent over the 14 tests"}
    method: Average of 14 tensile tests with photogrammetry, NASA Glenn
    status: ground
    source: nasa-tm-2018-219753
    where: Page 4 text
  - benchmark: yield_strength
    label: Tensile yield strength, 5083-O
    value: 140
    unit: MPa
    scope: material
    conditions: {alloy: "5083", temper: "O (annealed)", basis: "MakeItFrom page, citing Aluminum Association data; test conditions not stated"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083o
    where: Mechanical Properties, row Tensile Strength Yield
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, 5083-O
    value: 300
    unit: MPa
    scope: material
    conditions: {alloy: "5083", temper: "O (annealed)", basis: "MakeItFrom page, citing Aluminum Association data; test conditions not stated"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083o
    where: Mechanical Properties, row Tensile Strength Ultimate
  - benchmark: elongation
    label: Elongation at break, 5083-O
    value: 17
    unit: "%"
    scope: material
    conditions: {alloy: "5083", temper: "O (annealed)", basis: "MakeItFrom page; specimen not stated"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083o
    where: Mechanical Properties, row Elongation at Break
  - benchmark: yield_strength
    label: Tensile yield strength, 5083-H116
    value: 230
    unit: MPa
    scope: material
    conditions: {alloy: "5083", temper: "H116", basis: "MakeItFrom page; test conditions not stated"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083h116
    where: Mechanical, row Tensile Strength Yield
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, 5083-H116
    value: 320
    unit: MPa
    scope: material
    conditions: {alloy: "5083", temper: "H116", basis: "MakeItFrom page; test conditions not stated"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083h116
    where: Mechanical, row Tensile Strength Ultimate
  - benchmark: yield_strength
    label: Minimum proof stress, 5083-H116 plate (supplier sheet)
    value: 195
    bound: lower
    unit: MPa
    scope: material
    conditions: {alloy: "5083", temper: "H116", form: "sheet and plate with DNV class certification, per the supplier", unit_in_source: "Mpa", basis: "minimum value printed by a supplier; the standard it follows is not named"}
    method: Minimum value printed in a supplier datasheet
    status: ground
    source: dinco-5083h116
    where: Mechanical Properties table, row Proof Stress (195 Min)
  - benchmark: ultimate_tensile_strength
    label: Tensile strength range, 5083-H116 plate (supplier sheet)
    value: 305
    value_high: 385
    bound: range
    unit: MPa
    scope: material
    conditions: {alloy: "5083", temper: "H116", form: "sheet and plate with DNV class certification, per the supplier", basis: "range printed by a supplier; the standard it follows is not named"}
    method: Range printed in a supplier datasheet
    status: ground
    source: dinco-5083h116
    where: Mechanical Properties table, row Tensile Strength
  - benchmark: elongation
    label: Minimum elongation at 50 mm, 5083-H116 plate (supplier sheet)
    value: 8
    bound: lower
    unit: "%"
    scope: material
    conditions: {alloy: "5083", temper: "H116", gauge_length: "50 mm", basis: "minimum value printed by a supplier"}
    method: Minimum value printed in a supplier datasheet
    status: ground
    source: dinco-5083h116
    where: Mechanical Properties table, row Elongation at 50 mm (8 Min)
  - benchmark: yield_strength
    label: Tensile yield strength, 5086-H32
    value: 210
    unit: MPa
    scope: material
    conditions: {alloy: "5086", temper: "H32", basis: "MakeItFrom page; test conditions not stated"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5086h32
    where: Mechanical, row Tensile Strength Yield (proof)
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, 5086-H32
    value: 300
    unit: MPa
    scope: material
    conditions: {alloy: "5086", temper: "H32", basis: "MakeItFrom page; test conditions not stated"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5086h32
    where: Mechanical, row Tensile strength ultimate
  - benchmark: elongation
    label: Elongation at break, 5086-H32
    value: 11
    unit: "%"
    scope: material
    conditions: {alloy: "5086", temper: "H32", basis: "MakeItFrom page; specimen not stated"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5086h32
    where: Mechanical, row Elongation at Break
  - benchmark: density
    label: Density, 5083
    value: 2.7
    unit: g/cm3
    scope: material
    conditions: {alloy: "5083", temper: "O (annealed) and H116 pages agree", basis: "MakeItFrom pages, rounded to two figures", note: "the Dinco H116 sheet lists 2.65 g/cm3 for the same alloy"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083o
    where: Physical, row Density
  - benchmark: density
    label: Density, 5083-H116 (supplier sheet)
    value: 2.65
    unit: g/cm3
    scope: material
    conditions: {alloy: "5083", temper: "H116", basis: "generic physical property printed by a supplier"}
    method: Value printed in a supplier datasheet
    status: ground
    source: dinco-5083h116
    where: Generic Physical Properties table, row Density
  - benchmark: thermal_conductivity
    label: Thermal conductivity, 5083-O
    value: 120
    unit: W/(m·K)
    scope: material
    conditions: {alloy: "5083", temper: "O (annealed)", temperature: "not stated", basis: "MakeItFrom page", note: "Dinco lists 121 W/m.K for H116; MakeItFrom lists 130 for 5086-H32"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083o
    where: Thermal, row Thermal Conductivity
  - benchmark: thermal_conductivity
    label: Thermal conductivity, 5086-H32
    value: 130
    unit: W/(m·K)
    scope: material
    conditions: {alloy: "5086", temper: "H32", temperature: "not stated", basis: "MakeItFrom page"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5086h32
    where: Physical and thermal, row Thermal Conductivity
  - benchmark: thermal_conductivity
    label: Thermal conductivity of 5083-O at 77 K (curve-fit value)
    value: 55.3
    unit: W/(m·K)
    scope: material
    conditions: {alloy: "5083", temper: "O", temperature: "77 K", fit_range: "data 4 to 300 K, equation 1 to 300 K", fit_error: "1 % relative to the underlying data"}
    method: Calculated by Space Mushroom by evaluating the NIST log10 polynomial fit (coefficients a to i as printed on the NIST page) at 77 K; the page tabulates no values and gives only the equation
    status: calculated
    note: The same fit gives about 118 W/(m·K) at 293 K, close to the 120 and 121 W/(m·K) room-temperature values on the other pages, which supports the transcription of the coefficients.
    source: nist-5083
    where: Thermal Conductivity coefficient block (a = -0.90933, b = 5.751, c = -11.112, d = 13.612, e = -9.3977, f = 3.6873, g = -0.77295, h = 0.067336, i = 0)
  - benchmark: elastic_modulus
    label: Young's modulus of 5083-O at 77 K (curve-fit value)
    value: 80.2
    unit: GPa
    scope: material
    conditions: {alloy: "5083", temper: "O", temperature: "77 K", fit_range: "data 0 to 300 K, equation 2 to 295 K", fit_error: "1 % relative to the underlying data"}
    method: Calculated by Space Mushroom by evaluating the NIST polynomial y = a + bT + cT^2 + dT^3 + eT^4 at 77 K
    status: calculated
    note: The same fit gives about 71.9 GPa at 293 K, close to the 72.0 GPa the Dinco sheet lists for 5083-H116 at room temperature.
    source: nist-5083
    where: Young's Modulus coefficient block (a = 8.083212E1, b = 1.061708E-2, c = -3.016100E-4, d = 7.561340E-7, e = -6.994800E-10)
  - benchmark: elastic_modulus
    label: Modulus of elasticity, 5083-H116 (supplier sheet)
    value: 72.0
    unit: GPa
    scope: material
    conditions: {alloy: "5083", temper: "H116", basis: "generic physical property printed by a supplier", temperature: "not stated"}
    method: Value printed in a supplier datasheet
    status: ground
    source: dinco-5083h116
    where: Generic Physical Properties table, row Modulus of Elasticity
  - benchmark: cte
    label: Thermal expansion coefficient, 5083-O
    value: 24
    unit: ppm/K
    scope: material
    conditions: {alloy: "5083", temper: "O", unit_in_source: "µm/m-K, equal to ppm/K", temperature_range: "not stated", basis: "MakeItFrom page", note: "Dinco lists 25 x 10-6/K for H116"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083o
    where: Thermal, row Thermal Expansion (CTE)
  - benchmark: electrical_conductivity
    label: Electrical conductivity, 5083-O (equal volume)
    value: 29
    unit: "% IACS"
    scope: material
    conditions: {alloy: "5083", temper: "O", basis: "MakeItFrom page; IACS compares with annealed copper at equal volume", note: "the page also lists 96 % IACS at equal weight"}
    method: Value listed on a materials reference page
    status: ground
    source: makeitfrom-5083o
    where: "Electrical, row Electrical Conductivity: Equal Volume"
  - benchmark: electrical_resistivity
    label: Electrical resistivity, 5083-H116 (supplier sheet)
    value: 5.8
    unit: µΩ·cm
    scope: material
    conditions: {alloy: "5083", temper: "H116", unit_in_source: "0.058 x 10-6 ohm.m", conversion: "1 ohm.m = 10^8 µΩ·cm, calculated by Space Mushroom", temperature: "not stated"}
    method: Value printed in a supplier datasheet
    status: ground
    source: dinco-5083h116
    where: Generic Physical Properties table, row Electrical Resistivity
  - benchmark: melting_range
    label: Melting range, 5083 (solidus to liquidus)
    value: 580
    value_high: 640
    bound: range
    unit: °C
    scope: material
    conditions: {alloy: "5083", temper: "O", basis: "MakeItFrom page, melting onset (solidus) and melting completion (liquidus)", note: "Dinco prints a single melting point of 570 °C for H116"}
    method: Values listed on a materials reference page
    status: ground
    source: makeitfrom-5083o
    where: Thermal, rows Melting Onset (Solidus) and Melting Completion (Liquidus)
  - benchmark: max_service_temp
    label: Maximum service temperature for corrosion, 5083
    value: 65
    bound: upper
    unit: °C
    scope: material
    conditions: {alloy: "5083", temper: "O and H116 pages agree", basis: "page property named Maximum Temperature: Corrosion; the Dinco sheet says the alloy is not recommended for temperatures in excess of 65 °C"}
    method: Value listed on a materials reference page and in a supplier datasheet
    status: ground
    source: makeitfrom-5083o
    where: "Corrosion and mechanical temperature limits (page lists 65 °C corrosion and 190 °C mechanical)"
  - benchmark: hdd_platter_mg_matrix
    label: Magnesium in the aluminium matrix of a hard-drive platter (5XXX), EDS
    value: 4.1
    unit: wt%
    scope: material
    conditions: {material: "hard-drive platter whose paper-stated alloy class is 5XXX; exact grade not stated", method: "energy-dispersive X-ray spectroscopy on a matrix area of a platter cross-section", aluminium_in_same_area: "95.8 wt%"}
    method: EDS area analysis reported in an open-access paper
    status: ground
    source: pmc-hdd
    where: Section 3, Figure 4 and Table 2
  - benchmark: hdd_nickel_layer
    label: Thickness of the nickel layer on a hard-drive platter
    value: 10
    unit: µm
    scope: material
    conditions: {sides: "both sides of the platter", platter_thicknesses: "810, 1300 and 1800 micrometres in the three platter types examined", nickel_in_layer: "about 99.9 wt% Ni by EDS"}
    method: SEM cross-section with EDS
    status: ground
    source: pmc-hdd
    where: Section 3, Figure 4 and Table 2
  - benchmark: density
    label: Density of a recycled platter rod (melted, cast and extruded) with 4.53 wt% nickel
    value: 2.76
    unit: g/cm3
    scope: material
    conditions: {material: "rod made by melting platters under argon, casting and extruding; contains 4.53 wt% Ni, 3.79 wt% Mg, 91.49 wt% Al", sample: "A", note: "this is a recycled Al-Mg-Ni material, not a standard 5XXX grade"}
    method: Density measurement reported in an open-access paper
    status: ground
    source: pmc-hdd
    where: Table 5 (density) and Table 3 (composition), sample A
  - benchmark: ultimate_tensile_strength
    label: Tensile strength of a recycled platter rod (melted, cast and extruded)
    value: 271
    unit: MPa
    scope: material
    conditions: {material: "same recycled rod as the density entry above, sample A, with 4.53 wt% Ni", uncertainty_in_source: "plus or minus 4.2 MPa", extrusion: "375 °C, 1 mm/s, 8 mm rod", note: "not a standard 5XXX grade; the table column layout is garbled in the source text and the assignment follows the surrounding prose"}
    method: Tensile test reported in an open-access paper
    status: ground
    source: pmc-hdd
    where: Table 5 and Figure 8, sample A
  - benchmark: yield_strength
    label: Yield strength of a recycled platter rod (melted, cast and extruded)
    value: 95
    unit: MPa
    scope: material
    conditions: {material: "same recycled rod, sample A, with 4.53 wt% Ni", uncertainty_in_source: "plus or minus 4.1 MPa", note: "not a standard 5XXX grade; the table column layout is garbled in the source text"}
    method: Tensile test reported in an open-access paper
    status: ground
    source: pmc-hdd
    where: Table 5 and Figure 8, sample A
corrosion:
  - environment: Sea water and industrial chemical environments (5083)
    headline: "A supplier sheet calls 5083 highly resistant to sea water, but not for use above 65 °C."
    effect: "The Dinco 5083-H116 datasheet says the alloy is highly resistant to attack by both seawater and industrial chemical environments, retains exceptional strengths after welding, and is not recommended for temperatures in excess of 65 °C. The MakeItFrom pages for 5083-O and 5083-H116 also list a maximum corrosion temperature of 65 °C. This is a supplier statement, not a corrosion test, and no rate or exposure time is given."
    rating: low
    conditions: {basis: "supplier datasheet statement and a reference-page property; no exposure time, chloride level or corrosion rate stated", alloy: "5083-H116"}
    source: dinco-5083h116
    where: Description paragraph (top left of the sheet)
  - environment: Long holds at moderate temperature (grain-boundary attack, 5083)
    headline: "High-magnesium 5083 can develop precipitates along grain boundaries that make it prone to intergranular and stress corrosion."
    effect: "A Korean materials journal paper explains that Al-Mg alloys with more than about 4 % Mg hold more magnesium in solution at room temperature than they can keep for ever. After heavy cold work and a long time at room temperature, a magnesium-aluminium compound precipitates along slip bands and grain boundaries, so that in a corrosive atmosphere the grain boundaries are attacked and stress corrosion results. The paper gives 5083 as about 4.5 % Mg. It is a mechanism explanation in Korean, not a measured corrosion rate; the 65 °C limit above is the practical rule quoted by suppliers."
    rating: moderate
    conditions: {basis: "discussion in a 2007 paper (text in Korean, read by Space Mushroom); no temperature or time threshold measured in the paper", alloy: "5083"}
    source: kr-jung-2007
    where: Section 3.2, discussion on page 195
  - environment: Marine and humid air (5052)
    headline: "A supplier sheet lists very good corrosion resistance for 5052-H32 but gives no test."
    effect: "The Clinton Aluminum 5052-H32 sheet says the alloy has good workability, very good corrosion resistance, high fatigue strength and weldability with moderate strength. NASA notes that, within the 2.2 to 2.8 wt% Mg specification range, corrosion resistance does not change with magnesium content. No salt-spray, humidity or marine exposure data was found."
    rating: low
    conditions: {basis: "datasheet note and a NASA memorandum on general information taken presumably from bulk material; no environment, time or rate stated", alloy: "5052"}
    source: clinton-5052h32
    where: Material Notes (top of the sheet); NASA TM-2018-219753 page 1 for the magnesium-range statement
risks:
  hazards:
    - text: "PubChem's aggregated GHS reports for aluminium metal (4,079 company reports) give H261 in 90.8% of reports (in contact with water releases flammable gas), H228 in 60.6% (flammable solid) and H250 in 34.2% (catches fire spontaneously if exposed to air). 8.3% of reports say it does not meet GHS criteria. PubChem does not state the physical form the reports cover, so these are element-level statements, not a classification of the alloy as supplied."
      ghs: ["H261", "H228", "H250"]
      source: pubchem-al
      where: "Safety and Hazards, GHS Classification (CID 5359268)"
    - text: "PubChem's aggregated GHS reports for magnesium metal (2,205 company reports) give H228 in 44.9% of reports (flammable solid), H250 in 36.5% (catches fire spontaneously if exposed to air), and H260 in 36.7% (in contact with water releases flammable gases which may ignite spontaneously). 18.4% of reports say it does not meet GHS criteria. As with aluminium, these are element-level statements and do not classify the alloy."
      ghs: ["H228", "H250", "H260"]
      source: pubchem-mg
      where: "Safety and Hazards, GHS Classification (CID 5462224)"
  failure_risks:
    - mode: Wrong or unstabilised temper in 5052 honeycomb core
      trigger: "5052 core ordered without a stated temper, or supplied in H19 or H191, then heated during sandwich-panel curing"
      consequence: "NASA says core properties depend strongly on temper; H19 or H191 is fully hardened but not stabilised, so the alloy softens with panel curing. For aerospace use NASA recommends H38 or H39 and says the temper should be on the bill of material and checked on receipt."
      severity: moderate
      source: nasa-tm-2018-219753
      where: Pages 2 to 3 and Summary
    - mode: Strength loss of 5052-H39 foil after long hot exposure
      trigger: "Ageing at 400 °F (204 °C) for 1, 3 or 8 hours"
      consequence: "Tensile strength fell by 10 percent after 1 and 3 hours and by 15 percent after 8 hours at 400 °F; at 350 °F there was no difference until an 8 hour age, which cut strength by 6 percent."
      severity: low
      source: nasa-tm-2018-219753
      where: Pages 4 to 5, Figures 3 and 4
    - mode: Intergranular and stress corrosion of 5083
      trigger: "Long exposure at elevated temperature (suppliers say above 65 °C) or long room-temperature holds after heavy cold work, in a corrosive atmosphere"
      consequence: "Grain-boundary precipitates make the alloy prone to intergranular attack and stress corrosion; the paper gives the mechanism but no failure data."
      severity: moderate
      source: kr-jung-2007
      where: Section 3.2, page 195
    - mode: Loss of ductility after long immersion in liquid nitrogen (5083)
      trigger: "Immersion in liquid nitrogen for up to 29 weeks while testing in tension"
      consequence: "Elongation of 5083 decreased with immersion time because of non-uniform fracture of precipitates on grain boundaries, and serrated stress-strain curves appeared; tensile strength showed no large change. 6061 stayed constant in the same tests."
      severity: moderate
      source: kr-jung-2007
      where: Abstract; Section 3.2 (Figs. 5 and 6); Conclusions 1 to 3
  side_effects:
    - text: "The nickel layer on platters does not simply vanish on recycling. In the open recycling study, remelting or pressing platter pieces made hard Al3Ni particles where nickel meets the Al-Mg matrix (about 36 to 41 wt% Ni by EDS in the interface areas), and nickel stayed in the recycled rod at about 4.5 wt%."
      affects: "Composition and microstructure of recycled 5XXX aluminium from hard-drive platters"
      source: pmc-hdd
      where: Section 3, Table 3 and Table 4
  handling:
    - text: "State the temper on orders for 5052 honeycomb and check it on receipt; NASA recommends H38 or H39 for aerospace use and says H19 or H191 is not recommended for sandwich composites."
      source: nasa-tm-2018-219753
      where: Pages 2 to 3 and Summary
    - text: "Keep 5083 below 65 °C in long service, per the supplier datasheet."
      source: dinco-5083h116
      where: Description paragraph
  mitigations:
    - text: "For sandwich panels, NASA says 5052 H39 foil aged 8 hours at 400 °F could be possible if the small strength drop can be tolerated and the facesheet and core adhesive permit."
      source: nasa-tm-2018-219753
      where: Page 8, Summary
uses:
  - application: structures
    device: "Spacecraft structures (5052-H32 on a NASA list of spacecraft structural aluminium alloys)"
    example: "NASA Marshall's 2019 heritage-materials presentation lists aluminium alloys 6061-T6, 6061-T651, 7075 and 5052-H32 under Spacecraft Structural Materials. No mission is named."
    source: nasa-heritage-2019
    where: Slide Spacecraft Structural Materials
  - application: structures
    device: "Honeycomb core of composite sandwich panels for manned spaceflight programs (5052)"
    example: "NASA Glenn tested 5052 honeycomb from two vendors bought for the Composite Exploration Upper Stage (CEUS) program. Hexcel is named as offering its 5052 version in the H39 temper."
    source: nasa-tm-2018-219753
    where: Pages 1 to 2
  - application: propulsion-and-tanks
    device: "Aircraft fuel and oil lines, fuel tanks and other transportation parts (5052-H32)"
    example: "The Clinton Aluminum datasheet lists these among its uses; it also names sheet metal work, appliances, lighting, wire and rivets."
    source: clinton-5052h32
    where: Material Notes
  - application: structures
    device: "Ship building, vehicle bodies, pressure vessels, drilling rigs (5083)"
    example: "The Dinco 5083-H116 sheet lists ship building, vehicle bodies, pressure vessels, marine applications, transportation equipment and drilling rigs."
    source: dinco-5083h116
    where: Applications list
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:
      - {list: "USGS 2025 List of Critical Minerals (listed as Aluminum)", listed: true}
      - {list: "EU critical raw materials list of 34 (as shown on the European Commission page, which says aluminium and bauxite have been merged)", listed: true}
    recycling: "USGS: in 2025 aluminium recovered from purchased scrap in the United States was about 3.6 million tons, of which about 56% came from new scrap and 44% from old scrap; recovery from old scrap equalled about 28% of apparent consumption."
    substitutes: ["USGS: composites can substitute for aluminium in aircraft fuselages and wings; composites, magnesium, steel and titanium in ground transportation; copper can replace it in electrical and heat-exchange applications."]
    source: usgs-mcs2026-aluminum
    where: "World Smelter Production table, 2025e (world total 74,000 thousand t; shares calculated by Space Mushroom); Recycling; Substitutes. Lists: USGS and European Commission pages (see sources)."
  - subject: Bauxite (aluminium ore)
    producers:
      - {country: Guinea, share_percent: 34.1, year: 2025}
      - {country: Australia, share_percent: 22.0, year: 2025}
      - {country: China, share_percent: 19.8, year: 2025}
      - {country: Brazil, share_percent: 7.5, year: 2025}
      - {country: India, share_percent: 5.7, year: 2025}
    critical_lists:
      - {list: "EU critical raw materials list of 34 (Bauxite listed)", listed: true}
    recycling: "USGS bauxite and alumina chapter: 'None.'"
    substitutes: ["USGS: bauxite is the only raw material used to produce alumina on a commercial scale in the United States; clay and other materials are technically feasible but not currently economically competitive."]
    source: usgs-mcs2026-bauxite
    where: "World Alumina Refinery and Bauxite Mine Production table, bauxite 2025e (world total 440,000 thousand t; shares calculated by Space Mushroom); Recycling; Substitutes"
documents:
  - {title: "Recycling of Hard Disk Drive Platters via Plastic Consolidation (Skrzekut et al., Materials 2023)", type: paper, url: "https://pmc.ncbi.nlm.nih.gov/articles/PMC10608267/", year: 2023}
  - {title: "NASA/TM-2018-219753: Properties of 5052 Aluminum for Use as Honeycomb Core in Manned Spaceflight", type: report, url: "https://ntrs.nasa.gov/citations/20180001568", year: 2018}
  - {title: "NIST Cryogenic Material Properties: 5083 Aluminum (UNS A95083)", type: database, url: "https://trc.nist.gov/cryogenics/materials/5083%20Aluminum/5083Aluminum_rev.htm"}
  - {title: "Aluminum 5052-H32 datasheet (Clinton Aluminum, hosted by Protolabs)", type: datasheet, url: "https://Protolabs.com/media/iw0mfa0k/datasheet-sm-aluminum5052-h32.pdf"}
  - {title: "Aluminium Alloy AA 5083-H116 Data Sheet (Dinco Trading)", type: datasheet, url: "https://www.dinco.ae/files/aluminium-alloy-5083H116-data-sheet.pdf", year: 2024}
  - {title: "USGS Mineral Commodity Summaries 2026: Aluminum", type: report, url: "https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-aluminum.pdf", year: 2026}
  - {title: "USGS Mineral Commodity Summaries 2026: Bauxite and Alumina", type: report, url: "https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-bauxite-alumina.pdf", year: 2026}
gaps:
  - "No safety data sheet for the 5XXX alloys was opened. Hazards are element-level PubChem GHS data for aluminium and magnesium; dust and fumes from cutting, grinding or welding are not recorded."
  - "The recycling paper says platters are 5XXX aluminium but does not name a grade (it does not say 5052); the platter alloy is therefore not assigned to 5052, 5083 or 5086 here."
  - "Design-grade (minimum guaranteed) strengths by temper and thickness: MMPDS and MIL-HDBK-5 are not openly available. Strengths are Aluminum Association typicals marked not for design, reference-page values with unstated test conditions, or supplier minimums."
  - "5086 and 5083 Aluminum Association datasheet pages (ASM/MatWeb) could not be opened; 5086 has only the MakeItFrom values, and 5083 mechanical values by temper come from a reference page and one dealer sheet."
  - "Cryogenic strength, elongation and fracture toughness of 5083, 5052 and 5086 at 77 K and 4 K were not found as numbers in an open source (the Korean paper's tensile figures are graphs; 2025 fracture-toughness work on 5083-O was seen only as a search-result abstract). Only NIST curve-fit values of thermal conductivity and Young's modulus at 77 K are given, for 5083-O."
  - "NIST pages for 5052 and 5086 were not found in the NIST materials index page (which lists 1100, 3003-F, 5083-O, 6061-T6 and 6063-T5 as aluminium alloys); no cryogenic curve fits for them."
  - "Weldability: only a supplier rating for 5083 (arc and resistance excellent, gas average, brazability poor). No sourced weld-joint strength, heat-affected-zone softening, filler-metal rule or post-weld data for any of the three alloys."
  - "Marine and humid-air corrosion: no salt-spray, atmospheric-exposure or galvanic data with rates for 5052, 5083 or 5086 was found; the sea-water statement is a supplier claim. No sourced stress-corrosion susceptibility rating (NASA MSFC-STD-3029) was opened."
  - "Sensitisation threshold: the 65 degree C limit is a supplier and reference-page figure; an open review with temperature-time data was not opened (Scientific Reports article 10.1038/srep26870 was not readable)."
  - "Use of 5083 and 5086 in space hardware: nothing sourced. Only 5052 (H32 on a NASA list and honeycomb core) has a space-use source, and no flight mission is named."
  - "Outgassing (TML and CVCM), atomic-oxygen erosion, radiation and thermal-vacuum behaviour: no sourced values."
  - "Thermal conductivity and expansion over temperature for 5052 and 5086; thermal emittance: not found."
  - "Magnesium supply, critical-mineral listing and recycling were not looked up. Aluminium and bauxite supply come from the USGS 2026 summaries, and the same figures are in the 6061 profile."
sources:
  pmc-hdd:
    title: "Recycling of Hard Disk Drive Platters via Plastic Consolidation (Skrzekut, Wedrychowicz, Piotrowicz), Materials (Basel) 16(20):6745"
    id: "DOI 10.3390/ma16206745; PMCID PMC10608267"
    url: https://pmc.ncbi.nlm.nih.gov/articles/PMC10608267/
    year: 2023
    kind: paper
    license: CC BY 4.0
  clinton-5052h32:
    title: "Aluminum 5052-H32 datasheet (Clinton Aluminum & Stainless Steel, copy hosted by Protolabs)"
    id: "UNS A95052; data points marked AA are from the Aluminum Association and NOT FOR DESIGN"
    url: https://Protolabs.com/media/iw0mfa0k/datasheet-sm-aluminum5052-h32.pdf
    kind: datasheet
    license: supplier datasheet (cited, not reproduced)
  nasa-tm-2018-219753:
    title: "Properties of 5052 Aluminum for Use as Honeycomb Core in Manned Spaceflight (Bradley A. Lerch, NASA Glenn Research Center)"
    id: "NASA/TM-2018-219753; NTRS 20180001568; February 2018"
    url: https://ntrs.nasa.gov/citations/20180001568
    year: 2018
    kind: report
    license: public domain (NASA)
  nasa-heritage-2019:
    title: "Heritage Materials for Launch Vehicles and Spacecraft (Wayne Gamwell and Tracie Prater, NASA Marshall Space Flight Center)"
    id: "NTRS 20190020090; 23 April 2019; presentation, no abstract"
    url: https://ntrs.nasa.gov/citations/20190020090
    year: 2019
    kind: report
    license: public domain (NASA)
  nist-5083:
    title: "Material Properties: 5083 Aluminum (UNS A95083), NIST Cryogenic Material Properties"
    id: "NIST Cryogenics Technologies Group, curve fits for 4 to 300 K"
    url: https://trc.nist.gov/cryogenics/materials/5083%20Aluminum/5083Aluminum_rev.htm
    kind: database
    license: NIST public web page
  makeitfrom-5083o:
    title: "5083-O Aluminum, MakeItFrom.com"
    id: "page last modified 2020-05-30; cites Aluminum Standards and Data (Aluminum Association, 2013) and ASTM and EN standards"
    url: https://www.makeitfrom.com/material-properties/5083-O-Aluminum
    kind: web
    license: MakeItFrom terms of use (cited, not reproduced)
  makeitfrom-5083h116:
    title: "5083-H116 Aluminum, MakeItFrom.com"
    id: "MakeItFrom material properties page"
    url: https://www.makeitfrom.com/material-properties/5083-H116-Aluminum
    kind: web
    license: MakeItFrom terms of use (cited, not reproduced)
  makeitfrom-5086h32:
    title: "5086-H32 Aluminum, MakeItFrom.com"
    id: "MakeItFrom material properties page"
    url: https://www.makeitfrom.com/material-properties/5086-H32-Aluminum
    kind: web
    license: MakeItFrom terms of use (cited, not reproduced)
  dinco-5083h116:
    title: "Aluminium Alloy AA 5083-H116 Data Sheet (Dinco Trading LLC, Dubai)"
    id: "PDF created 2024-05-30"
    url: https://www.dinco.ae/files/aluminium-alloy-5083H116-data-sheet.pdf
    year: 2024
    kind: datasheet
    license: supplier datasheet (cited, not reproduced)
  kr-jung-2007:
    title: "An Extremely Low Temperature Properties of Wrought Aluminum Alloys (Jung, Kim, Lee, Lee and Jang), Korean Journal of Materials Research 17(4), 192-197 (text in Korean)"
    id: "Kor. J. Mater. Res. Vol. 17, No. 4 (2007); koreascience.kr JAKO200727542962161"
    url: https://koreascience.kr/article/JAKO200727542962161.pdf
    year: 2007
    kind: paper
    license: journal article (cited, not reproduced)
  usgs-mcs2026-aluminum:
    title: Mineral Commodity Summaries 2026, Aluminum
    id: "USGS MCS 2026, February 2026"
    url: https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-aluminum.pdf
    year: 2026
    kind: report
    license: public domain (USGS)
  usgs-mcs2026-bauxite:
    title: Mineral Commodity Summaries 2026, Bauxite and Alumina
    id: "USGS MCS 2026, February 2026"
    url: https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-bauxite-alumina.pdf
    year: 2026
    kind: report
    license: public domain (USGS)
  pubchem-al:
    title: "Aluminum, PubChem compound CID 5359268: Safety and Hazards, GHS Classification"
    id: "PubChem CID 5359268 (PUG View JSON, read 2026-10-19); aggregated from ECHA C&L notifications"
    url: https://pubchem.ncbi.nlm.nih.gov/compound/5359268
    kind: database
    license: "PubChem (NCBI) public data"
  pubchem-mg:
    title: "Magnesium, PubChem compound CID 5462224: Safety and Hazards, GHS Classification"
    id: "PubChem CID 5462224 (PUG View JSON, read 2026-10-19); aggregated from ECHA C&L notifications"
    url: https://pubchem.ncbi.nlm.nih.gov/compound/5462224
    kind: database
    license: "PubChem (NCBI) public data"
license: CC-BY-4.0

updated: "2026-10-19"
review:
  status: draft
  method: assistant
  checked_values: 42
  unreachable: 2
  caveats: 6
  note: "Deepen pass on 2026-10-19 (no property changed): added story recipe from the 5052, 5083 and 5086 composition lists, supply from USGS 2026 aluminium and bauxite tables (shares computed from printed tonnage), hazards from PubChem GHS, and four sources. Values were read from the opened sources on 2026-10-17. Caveats: strengths are Aluminum Association typicals marked not for design, reference-page values with unstated test conditions, or supplier minimums; the NIST 77 K values are calculated from printed coefficients; the Korean paper is in Korean; recycled-rod values are for an Al-Mg-Ni material, not a standard grade. Unreachable: asm.matweb.com pages for 5083 and 5086, and the Scientific Reports sensitisation article."

story:
  recipe:
    line: "Wrought Al-Mg alloys. Magnesium is the main addition: 2.20 to 2.80 wt% in 5052, 4.0 to 4.9 wt% in 5083 and 3.5 to 4.5 wt% in 5086. The other elements are held to small limits, and aluminium is the balance. Values are the envelope across the three alloys read for this profile, from their supplier datasheets and composition lists, not a single alloy."
    parts:
      - name: Aluminium
        symbol: Al
        share_note: "balance (the rest)"
        role: The matrix of the alloy; its thin oxide film gives the corrosion resistance.
      - name: Magnesium
        symbol: Mg
        share_percent: 2.2
        share_high: 4.9
        role: Main addition. It stays in solid solution and sets the strength of the non-heat-treatable alloys (5052 to 5086).
      - name: Manganese
        symbol: Mn
        share_percent: 0
        share_high: 1.0
        limit: maximum
        role: Present mainly in 5083 (0.4 to 1.0 wt%); 5052 is held to 0.10 wt% maximum.
      - name: Chromium
        symbol: Cr
        share_percent: 0.05
        share_high: 0.35
        role: Small addition, 0.15 to 0.35 wt% in 5052 and 0.05 to 0.25 wt% in 5083 and 5086.
      - name: Iron
        symbol: Fe
        share_percent: 0
        share_high: 0.5
        limit: maximum
        role: Impurity held to a maximum that differs by alloy (0.40 in 5052, 0.50 in 5086).
      - name: Silicon
        symbol: Si
        share_percent: 0
        share_high: 0.4
        limit: maximum
        role: Impurity held low; 5052 is limited to 0.25 wt% maximum.
      - name: Zinc
        symbol: Zn
        share_percent: 0
        share_high: 0.25
        limit: maximum
        role: Impurity held to a maximum of 0.10 in 5052 and 0.25 in 5083 and 5086.
      - name: Copper
        symbol: Cu
        share_percent: 0
        share_high: 0.1
        limit: maximum
        role: Impurity held to 0.10 wt% maximum in all three alloys.
  risk_groups:
    - title: For people
      lead: "No safety data sheet for these alloys was opened. Element-level GHS data for aluminium and magnesium from PubChem is in the hazards list, but the profile records no toxicity or dust data for the alloys."
      gap: "Hazard classification for 5052, 5083 and 5086 as supplied, and for dust or fumes from cutting or welding, was not found in a source we could open."
      points:
        - label: What the sources cover
          line: "The sources opened describe strength, temper and corrosion, not health effects. Read the supplier's safety data sheet before cutting, grinding or welding."
    - title: If it fails
      lead: "These routes come from a NASA memorandum, a supplier sheet and a 2007 research paper, not from field incident data."
      points:
        - label: Wrong temper in honeycomb
          line: "NASA says 5052 core properties depend strongly on temper, that the temper is rarely stated on orders, and that H19 or H191 softens during panel curing. It recommends H38 or H39 for aerospace."
        - label: Heat softening
          line: "5052 H39 foil lost 10 percent of its strength after 1 or 3 hours at 400 °F and 15 percent after 8 hours."
        - label: Grain-boundary attack in 5083
          line: "With about 4.5 % magnesium, 5083 can develop precipitates along grain boundaries that make it prone to intergranular and stress corrosion. Suppliers say not to use it above 65 °C."
        - label: Ductility in liquid nitrogen
          line: "In tests with up to 29 weeks of immersion in liquid nitrogen, the elongation of 5083 decreased and serrations appeared on the stress-strain curve, while 6061 stayed constant."
    - title: Handling and storage
      points:
        - label: Specify the temper
          line: "State H38 or H39 for 5052 honeycomb on the bill of material and check it when the material arrives."
        - label: Temperature limit
          line: "Keep 5083 below 65 °C in long service, as the supplier sheet advises."
  why: >-
    The 5XXX series are aluminium alloys whose main addition is magnesium. They are wrought, meaning they are rolled into sheet and plate.
    NASA explains that 5052 is hardened by magnesium and often coupled with cold work, which is shaping at low temperature that makes the metal harder.
    The letter and number after the alloy, such as H32 or H38, is the temper: H means strain hardened, and a higher second digit means more
    strength and less ductility. Magnesium content sets the family. 5052 allows 2.2 to 2.8 wt% Mg, 5086 allows 3.5 to 4.5 wt% and 5083 allows 4.0 to 4.9 wt%.
    This differs from 6061, which gets its strength from heat treatment; see the aluminium 6061 profile. An open recycling study found
    hard-drive platters made of 5XXX aluminium: an aluminium matrix with about 4.1 wt% Mg, covered on both sides by a nickel layer 10 micrometres thick.
  uses:
    - where: Spacecraft structures
      line: >-
        NASA Marshall's 2019 presentation on heritage materials lists 5052-H32 with 6061 and 7075 under spacecraft structural aluminium alloys.
        It names no mission.
    - where: Honeycomb core in sandwich panels
      line: >-
        NASA Glenn describes 5052 as the usual core of composite sandwich panels for lightweight structures, and tested 5052 core bought for the
        Composite Exploration Upper Stage program. It recommends the H38 or H39 temper for aerospace.
    - where: Ships, vehicles and pressure vessels
      line: >-
        A supplier datasheet lists ship building, vehicle bodies, pressure vessels, marine applications and drilling rigs for 5083-H116.
    - where: Hard-drive platters
      line: >-
        An open study of recycling found platters made mostly of 5XXX aluminium, with a thin nickel layer on both sides. Remelting or pressing them
        made a recycled rod with nickel left in the metal at about 4.5 wt%.
  can_do:
    - label: Strength of 5052 by temper
      value: 89.6 to 255 MPa yield
      line: >-
        NASA quotes datasheet values for 5052: yield 13 ksi (89.6 MPa) annealed with 25 percent elongation, rising to 37 ksi (255 MPa) in H38 with
        7 percent elongation. In H32 the Aluminum Association typical yield is 193 MPa and the ultimate tensile strength is 228 MPa. These typicals are marked not for design.
    - label: Strength of 5083 and 5086
      value: 140 to 230 MPa yield
      line: >-
        A reference page lists a yield of 140 MPa and a tensile strength of 300 MPa for 5083-O, and 230 and 320 MPa for 5083-H116. A supplier sheet prints a minimum
        proof stress of 195 MPa and a tensile range of 305 to 385 MPa for H116. For 5086-H32 the reference page lists 210 MPa yield and 300 MPa tensile strength.
    - label: Weight
      value: 2.68 g/cm3
      line: >-
        5052-H32 has a typical density of 2.68 g/cm3. A reference page lists 2.7 g/cm3 for 5083, and a supplier sheet 2.65 g/cm3.
    - label: Weldability
      value: Arc excellent (5083 supplier rating)
      line: >-
        The 5083 supplier sheet rates arc and resistance welding as excellent, gas welding as average and brazing as poor, and says the alloy retains
        exceptional strengths after welding. No weld-joint test data was found.
    - label: Heat conduction
      value: 120 to 138 W/(m·K)
      line: >-
        Thermal conductivity is 138 W/(m·K) for 5052-H32, 130 for 5086-H32 and 120 for 5083-O. Evaluating the NIST curve fit for 5083-O at 77 K gives
        55.3 W/(m·K), so conduction drops at low temperature.
    - label: Cold behaviour
      value: 80.2 GPa stiffness at 77 K
      line: >-
        The NIST fit for 5083-O gives a Young's modulus of 80.2 GPa at 77 K, against 71.9 GPa at 293 K. A Korean paper found no large change in 5083
        tensile strength after up to 29 weeks in liquid nitrogen, but a lower elongation.
    - label: Electrical conduction
      value: 29 % IACS
      line: >-
        5083-O conducts 29 % as well as annealed copper at equal volume, per a reference page; a supplier lists a resistivity of 5.8 µΩ·cm for H116.
  compare: >-
    6061 is hardened by heat treatment and 5XXX alloys by magnesium and cold work, so 5XXX values depend on the temper letter and number rather than T6.
    The 6061 profile on this site gives its own values and these are not blended with the three alloys here. In the sources, 5083 has the most
    magnesium and carries a 65 °C limit for corrosion; 5052 has the least and is the one with a space-use source.
  compare_rows:
    - {label: Density, benchmark: density}
    - {label: Thermal conductivity, benchmark: thermal_conductivity}
    - {label: Thermal expansion, benchmark: cte}
    - {label: Yield strength, benchmark: yield_strength}
  handling:
    - Specify and check the temper of 5052 honeycomb core; NASA recommends H38 or H39.
    - Keep 5083 below 65 °C in long service.
    - Read the supplier's safety data sheet before cutting, grinding or welding.
  good_for:
    - "Welded plate and sheet at moderate strength. A supplier rates 5083 arc weldability as excellent."
    - "Sandwich-panel core. NASA describes 5052 as commonly used as the core of composite sandwich panels."
    - "Light structures. Densities are 2.65 to 2.7 g/cm3 across the three alloys in the sources."
  watch_out:
    - "5083 above 65 °C: grain-boundary precipitates can make it prone to intergranular and stress corrosion."
    - "Unstated or wrong temper in 5052 honeycomb: properties and stability depend on it."
    - "Strengths here are typicals, reference-page values or supplier minimums, not design allowables."
    - "No sourced outgassing, atomic-oxygen, radiation or cryogenic strength numbers, and no sourced space use for 5083 or 5086."
  verdict: "The 5XXX alloys are light, weldable, magnesium-hardened sheet and plate, with 5052 the one that has a space-use source (spacecraft structure list and honeycomb core). Their weak points in the record are 5083 above 65 °C, the temper dependence of 5052, and the lack of design-grade, cryogenic and space-environment numbers."