spore: profile
id: aluminium-5052
spore_version: 0.2
family: aluminium-alloys
name: Aluminium alloy 5052
abbreviation: '5052'
role: structural alloy
category: metals
type: aluminium
summary: |
  5052 is a wrought aluminium-magnesium alloy (UNS A95052) with 2.20 to 2.80 wt% magnesium. NASA says its strength comes from the magnesium and from cold work, so strength depends strongly on temper: the Aluminum Association typical yield strength is 193 MPa in H32, against 13 ksi annealed (O) and 37 ksi in H38. The datasheets rate it very good against seawater, but the sources read for this profile give no measured seawater corrosion rate.
best_for: Welded sheet and tank or marine-style parts at medium strength, where the temper is named and checked (the datasheets rate its seawater resistance very good)
weakest_at: Strength depends on temper (yield 13 ksi annealed to 37 ksi in H38), and no measured seawater corrosion rate was found in the sources read
identity:
  formula: 'Al-Mg alloy, UNS A95052; composition limits in wt%: 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)'
  source: clinton-5052-h32
  where: Component Elements table of the Clinton 5052-H32 datasheet (Aluminum Association composition, not for design); the AMS4004D chemistry in NASA TM Table I (p. 2) gives the same magnesium and chromium limits; the Wikipedia composition list agrees (cross-check only)
  designations:
    - system: UNS
      code: A95052
      source: clinton-5052-h32
      where: Key Words line on page 1 of the Clinton datasheet
    - system: ISO
      code: AlMg2.5
      source: clinton-5052-h32
      where: Key Words line on page 1 of the Clinton datasheet
    - system: AA
      code: '5052'
      source: clinton-5052-h32
      where: Key Words line on page 1, printed AA5052-H32 (the temper is not part of the code)
    - system: AMS
      code: 4004D
      note: foil, strain hardened
      source: nasa-tm-2018-219753
      where: Text before Table I and the Table I column head, which give AMS4004D as the standard 5052 chemistry; reference 3
    - system: AMS
      code: A81596
      note: foil for sandwich construction
      source: nasa-tm-2018-219753
      where: Temper paragraph, which names AMSA81596 for 5052 temper H191; reference 2
    - system: AMS
      code: QQ-A-250/8
      note: plate and sheet
      source: nasa-tm-2018-219753
      where: Foil tensile paragraph, which cites AMSQQA250/8; reference 5
tags:
  environments: []
  stresses: []
  applications:
    - structures
    - propulsion-and-tanks
properties:
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, datasheet value, O (annealed)
    value: 28
    unit: ksi
    scope: material
    conditions:
      temper: O (annealed)
      product_form: bulk material (product form not stated)
      temperature: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row O (annealed)
  - benchmark: yield_strength
    label: Yield strength, datasheet value, O (annealed)
    value: 13
    unit: ksi
    scope: material
    conditions:
      temper: O (annealed)
      product_form: bulk material (product form not stated)
      temperature: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row O (annealed)
  - benchmark: elongation
    label: Elongation at break, datasheet value, O (annealed)
    value: 25
    unit: '%'
    scope: material
    conditions:
      temper: O (annealed)
      product_form: bulk material (product form not stated)
      specimen: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row O (annealed)
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, datasheet value, H32
    value: 33
    unit: ksi
    scope: material
    conditions:
      temper: H32
      product_form: bulk material (product form not stated)
      temperature: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H32
  - benchmark: yield_strength
    label: Yield strength, datasheet value, H32
    value: 28
    unit: ksi
    scope: material
    conditions:
      temper: H32
      product_form: bulk material (product form not stated)
      temperature: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H32
  - benchmark: elongation
    label: Elongation at break, datasheet value, H32
    value: 12
    unit: '%'
    scope: material
    conditions:
      temper: H32
      product_form: bulk material (product form not stated)
      specimen: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H32
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, datasheet value, H34
    value: 38
    unit: ksi
    scope: material
    conditions:
      temper: H34
      product_form: bulk material (product form not stated)
      temperature: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H34
  - benchmark: yield_strength
    label: Yield strength, datasheet value, H34
    value: 31
    unit: ksi
    scope: material
    conditions:
      temper: H34
      product_form: bulk material (product form not stated)
      temperature: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H34
  - benchmark: elongation
    label: Elongation at break, datasheet value, H34
    value: 10
    unit: '%'
    scope: material
    conditions:
      temper: H34
      product_form: bulk material (product form not stated)
      specimen: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H34
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, datasheet value, H38
    value: 42
    unit: ksi
    scope: material
    conditions:
      temper: H38
      product_form: bulk material (product form not stated)
      temperature: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H38
  - benchmark: yield_strength
    label: Yield strength, datasheet value, H38
    value: 37
    unit: ksi
    scope: material
    conditions:
      temper: H38
      product_form: bulk material (product form not stated)
      temperature: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H38
  - benchmark: elongation
    label: Elongation at break, datasheet value, H38
    value: 7
    unit: '%'
    scope: material
    conditions:
      temper: H38
      product_form: bulk material (product form not stated)
      specimen: not stated
      basis: datasheet value that NASA cites from Metal Suppliers Online and Alcoa
    method: Datasheet value tabulated by NASA (Table II); the authors did not test it
    status: ground
    source: nasa-tm-2018-219753
    where: Table II, datasheet values for 5052 bulk material (p. 3), row H38
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, typical, H32
    value: 228
    unit: MPa
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      product_form: not stated
      temperature: not stated
      basis: Aluminum Association typical value, marked NOT FOR DESIGN
    method: Typical value listed in a datasheet (Aluminum Association data)
    status: ground
    source: clinton-5052-h32
    where: Mechanical Properties table, row Tensile Strength, Ultimate
  - benchmark: yield_strength
    label: Yield strength, typical, H32
    value: 193
    unit: MPa
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      product_form: not stated
      temperature: not stated
      basis: Aluminum Association typical value, marked NOT FOR DESIGN
    method: Typical value listed in a datasheet (Aluminum Association data)
    status: ground
    source: clinton-5052-h32
    where: Mechanical Properties table, row Tensile Strength, Yield
  - benchmark: elongation
    label: Elongation at break, typical, H32, 1.59 mm thickness
    value: 12
    unit: '%'
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      specimen: thickness 1.59 mm (0.0625 in)
      product_form: not stated
      basis: Aluminum Association typical value, marked NOT FOR DESIGN
    method: Typical value listed in a datasheet (Aluminum Association data)
    status: ground
    source: clinton-5052-h32
    where: Mechanical Properties table, row Elongation at Break, @Thickness 1.59 mm
  - benchmark: elongation
    label: Elongation at break, typical, H32, 12.7 mm round specimen
    value: 18
    unit: '%'
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      specimen: round, diameter 12.7 mm (0.500 in)
      product_form: not stated
      basis: Aluminum Association typical value, marked NOT FOR DESIGN
    method: Typical value listed in a datasheet (Aluminum Association data)
    status: ground
    source: clinton-5052-h32
    where: Mechanical Properties table, row Elongation at Break, @Diameter 12.7 mm
  - benchmark: elastic_modulus
    label: Modulus of elasticity, typical, H32
    value: 70.3
    unit: GPa
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      basis: Aluminum Association typical; average of tension and compression, compression about 2 % greater than tension (datasheet comment)
    method: Typical value listed in a datasheet (Aluminum Association data)
    status: ground
    source: clinton-5052-h32
    where: Mechanical Properties table, row Modulus of Elasticity
  - benchmark: fatigue_strength
    label: Fatigue strength at 500,000,000 cycles, typical, H32
    value: 117
    unit: MPa
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      loading: completely reversed stress
      test: RR Moore machine and specimen
      cycles: 5.00 x 10^8 (500,000,000)
      basis: datasheet value, no basis comment printed
    method: Value listed in a datasheet
    status: ground
    source: clinton-5052-h32
    where: Mechanical Properties table, row Fatigue Strength
  - benchmark: shear_modulus
    label: Shear modulus, H32
    value: 25.9
    unit: GPa
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      basis: datasheet value, no basis comment printed
    method: Value listed in a datasheet
    status: ground
    source: clinton-5052-h32
    where: Mechanical Properties table, row Shear Modulus
  - benchmark: poissons_ratio
    label: Poisson's ratio, H32
    value: 0.33
    unit: '-'
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      basis: datasheet value, printed as 0.330
    method: Value listed in a datasheet
    status: ground
    source: clinton-5052-h32
    where: Mechanical Properties table, row Poissons Ratio
  - benchmark: density
    label: Density, typical, H32
    value: 2.68
    unit: g/cc
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      temperature: not stated
      basis: Aluminum Association typical
    method: Typical value listed in a datasheet (Aluminum Association data)
    status: ground
    source: clinton-5052-h32
    where: Physical Properties table, row Density
  - benchmark: thermal_conductivity
    label: Thermal conductivity, typical, H32
    value: 138
    unit: W/m-K
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      temperature: 77 °F
      basis: Aluminum Association typical at 77 °F
    method: Typical value listed in a datasheet (Aluminum Association data)
    status: ground
    source: clinton-5052-h32
    where: Thermal Properties table, row Thermal Conductivity
  - benchmark: cte
    label: Mean coefficient of thermal expansion, 20 to 200 °C, H32
    value: 24.8
    unit: µm/m-°C
    scope: material
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      temperature_range: 20.0 to 200 °C (68.0 to 392 °F)
      unit_in_source: µm/m-°C, equal to ppm/K
      basis: no basis comment printed on this row
    method: Value listed in a datasheet
    status: ground
    source: clinton-5052-h32
    where: Thermal Properties table, first CTE row, @Temperature 20.0 - 200 °C
  - benchmark: melting_point
    label: Melting range, solidus to liquidus, typical
    value: 607.2
    value_high: 649
    bound: range
    unit: °C
    scope: material
    conditions:
      basis: Aluminum Association typical range for typical composition of wrought products 1/4 inch thickness or greater
      solidus: 607.2 °C
      liquidus: 649 °C
    method: Typical range listed in a datasheet
    status: ground
    source: clinton-5052-h32
    where: Melting Point, Solidus and Liquidus rows of the Thermal Properties table
corrosion:
  - environment: Seawater and marine atmosphere (datasheet rating for H32)
    headline: The Smiths datasheet rates 5052-H32 very good against seawater and marine atmospheres.
    effect: The datasheet lists very good corrosion resistance to seawater and to marine and industrial atmospheres, and names marine components among typical uses. It gives no exposure time, corrosion rate or pit depth. It is a distributor rating, not a test result.
    rating: low
    conditions:
      temper: H32 (the datasheet says its properties are for H32)
      basis: distributor rating, not a test result
    source: smith-5052-datasheet
    where: Key features and Corrosion Resistance box
  - environment: Atmospheres, no environment named (datasheet rating)
    headline: The Clinton datasheet also rates 5052-H32 very good for corrosion, without naming an environment.
    effect: The material notes say the alloy has very good corrosion resistance, good workability, high fatigue strength and moderate strength. No environment, exposure time or rate is given.
    rating: low
    conditions:
      temper: H32 (datasheet title Aluminum 5052-H32)
      basis: general statement in the material notes
    source: clinton-5052-h32
    where: Material notes paragraph
  - environment: Sea water, stagnant and flowing (aluminium alloys in general, 1985 study)
    headline: Aluminium corrodes in sea water by different routes from sodium chloride solution, and faster flow reduces attack.
    effect: The 1985 Sea Grant report (Dexter and Hartt) found the corrosion processes on aluminium in seawater significantly different from those in sodium chloride solutions. Faster seawater flow, as in tidal and wind-driven currents, gives less corrosive conditions than stagnant water. The abstract covers aluminium alloys in general and does not name 5052.
    rating: unknown
    conditions:
      basis: abstract of a 1985 report on aluminium alloys; 5052 is not named in the abstract
    source: trid-sea-grant-1985
    where: Abstract (TRID record)
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. These are element-level statements, not a classification of 5052 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), H261 in 44.8% (in contact with water releases flammable gas), H260 in 36.7% (in contact with water releases flammable gases which may ignite spontaneously) and H250 in 36.5% (catches fire spontaneously if exposed to air). 18.4% say it does not meet GHS criteria. These are element-level statements and do not classify the alloy.
      ghs:
        - H228
        - H261
        - H260
        - H250
      source: pubchem-mg
      where: Safety and Hazards, GHS Classification (CID 5462224)
  failure_risks:
    - mode: Core crushing under flatwise compression
      trigger: Off-axis loads on a 5052 honeycomb core in a sandwich panel
      consequence: In the NASA flatwise compression tests the maximum stress before buckling was 165 to 219 psi, with scatter and two failure modes. Samples aged 8 hours at 350 °F or 400 °F showed no clear change. The report calls one 400 °F result lower and says more study is needed to confirm an aging effect.
      severity: moderate
      source: nasa-tm-2018-219753
      where: Table III, maximum stress for flatwise compression samples (p. 7)
    - mode: Softening during high-temperature cure
      trigger: A non-stabilised temper (H19 or H191), or a stabilised H39 foil held at a high cure temperature for a long time
      consequence: H39 foil aged at 400 °F lost about 10 % of its room temperature tensile strength after 1 hour and after 3 hours, and 15 % after 8 hours. At 350 °F the tensile properties were unchanged until the 8-hour age, which lost 6 %.
      severity: moderate
      source: nasa-tm-2018-219753
      where: Aging studies on 5052 H39 foil, pp. 4 to 5, and Summary, p. 7
  side_effects: []
  handling:
    - text: Anneal at 343 °C (650 °F); holding at temperature is not required.
      source: clinton-5052-h32
      where: Processing Properties table, row Annealing Temperature
    - text: Hot work between 260 and 510 °C (500 and 950 °F).
      source: clinton-5052-h32
      where: Processing Properties table, row Hot-Working Temperature
    - text: Specify the temper on the order and verify it on receipt. The report says 5052 honeycomb is often bought with no temper stated, and recommends H38 or H39 for aerospace use.
      source: nasa-tm-2018-219753
      where: Introduction, p. 2, and Summary, p. 7
    - text: Do not use H19 or H191 in sandwich composites, because they are not stabilised and will soften during panel cure.
      source: nasa-tm-2018-219753
      where: Introduction, p. 2
  mitigations:
    - text: Use a stabilised temper, H38 or H39, for aerospace core, as the report recommends.
      source: nasa-tm-2018-219753
      where: Summary, p. 7
    - text: Check the cure schedule against the temper. In the test, H39 foil aged 1 to 3 hours at 350 °F showed no change in tensile properties.
      source: nasa-tm-2018-219753
      where: Aging studies, pp. 4 to 5
uses:
  - application: structures
    device: Honeycomb core of composite sandwich panels for lightweight structures
    example: NASA says 5052 honeycomb is commonly used as the core of composite sandwich panels, and its benchmark properties matter for manned spaceflight.
    source: nasa-tm-2018-219753
    where: Introduction, p. 1
  - application: structures
    device: Spacecraft structural materials list, next to 6061-T6, 6061-T651 and 7075
    example: NASA's heritage presentation lists 5052-H32 among the aluminium alloys used for spacecraft structural materials.
    source: nasa-heritage-2019
    where: Spacecraft Structural Materials slide
  - application: propulsion-and-tanks
    device: Aircraft fuel and oil lines, and fuel tanks
    example: The Clinton datasheet says the alloy is used for aircraft fuel and oil lines and fuel tanks, among other transport areas.
    source: clinton-5052-h32
    where: Material notes paragraph
  - application: structures
    device: Marine components, containers and pressure vessels
    example: The Smiths datasheet lists pressure vessels, marine components, containers and chemical equipment among typical applications.
    source: smith-5052-datasheet
    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: EU critical raw materials list (aluminium and bauxite merged, per the Commission page)
        listed: true
    recycling: 'USGS: in 2025 aluminium recovered from purchased scrap in the United States was about 3.6 million tons, and old-scrap recovery equalled about 28% of apparent consumption. US net import reliance was 60% in 2025e.'
    substitutes:
      - 'USGS: composites can substitute for aluminium in aircraft fuselages and wings; composites, magnesium, steel and titanium in ground transportation; copper 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 from the printed tonnages); Recycling; Substitutes; Salient Statistics
  - subject: Bauxite (aluminium ore)
    producers:
      - country: Guinea
        share_percent: 34.1
        year: 2025
      - country: Australia
        share_percent: 22
        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 (bauxite listed, merged with aluminium)
        listed: true
    recycling: 'USGS: 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-alumina
    where: World Alumina Refinery and Bauxite Mine Production table, bauxite 2025e (world total 440,000 thousand t; shares calculated by Space Mushroom from the printed tonnages); Recycling; Substitutes
  - subject: Magnesium metal
    abundance: 'USGS: magnesium resources range from large to virtually unlimited and are globally widespread; magnesium could be recovered from seawater along world coastlines.'
    producers:
      - country: China
        share_percent: 86.4
        year: 2025
      - country: Russia
        share_percent: 5.5
        year: 2025
      - country: Brazil
        share_percent: 1.8
        year: 2025
      - country: Israel
        share_percent: 1.8
        year: 2025
      - country: Turkey
        share_percent: 1.4
        year: 2025
    critical_lists:
      - list: EU critical raw materials list (magnesium listed)
        listed: true
    recycling: 'USGS: about 26,000 tons of secondary magnesium was recovered from old scrap and 82,000 tons from new scrap in 2025; aluminium-base alloys took about 53% of the secondary magnesium recovered.'
    substitutes:
      - 'USGS: aluminum and zinc may substitute for magnesium in castings and wrought products; magnesium is lighter, but its high cost is a disadvantage relative to them.'
    source: usgs-mcs2026-magnesium-metal
    where: World Primary Production and Reserves table, 2025 smelter production (world total 1,100 thousand t; shares calculated by Space Mushroom from the printed tonnages); Recycling; Substitutes; US net import reliance above 75% in 2025e
media: []
documents:
  - title: Aluminum 5052-H32 datasheet (Clinton Aluminum and Stainless Steel, copy hosted by Protolabs)
    type: datasheet
    url: https://Protolabs.com/media/iw0mfa0k/datasheet-sm-aluminum5052-h32.pdf
  - title: 5052 Aluminium Technical Datasheet (Smiths Metal Centres)
    type: datasheet
    url: https://www.smithmetal.com/pdf/aluminium/5xxx/5052.pdf
    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: Heritage Materials for Launch Vehicles and Spacecraft (NASA, 2019)
    type: report
    url: https://ntrs.nasa.gov/citations/20190020090
    year: 2019
  - title: 'Sea Grant Program on Marine Corrosion, Volume 3: Localized Corrosion, Aluminum Alloys (1985)'
    type: report
    url: https://trid.trb.org/View/399688
    year: 1985
  - 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
  - title: 'USGS Mineral Commodity Summaries 2026: Magnesium Metal'
    type: report
    url: https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-magnesium-metal.pdf
    year: 2026
  - title: Critical raw materials (European Commission)
    type: report
    url: https://single-market-economy.ec.europa.eu/sectors/raw-materials/areas-specific-interest/critical-raw-materials_en
  - title: 'PubChem: Aluminum, CID 5359268, Safety and Hazards'
    type: database
    url: https://pubchem.ncbi.nlm.nih.gov/compound/5359268
  - title: 'PubChem: Magnesium, CID 5462224, Safety and Hazards'
    type: database
    url: https://pubchem.ncbi.nlm.nih.gov/compound/5462224
gaps:
  - No measured corrosion rate, pit depth, exposure time or galvanic potential for 5052 in seawater was read in this run. The MDPI Metals 2026 article (15/3/327) was blocked, a 2017 AMPP paper on 5052 for desalination is a paid store page, and the Alcoa seawater catalogue (OSTI 1069242) and the NRL under-pier report (DTIC AD0685588) did not open.
  - Design allowable strengths (MMPDS, MIL-HDBK-5, A or B basis) and ASTM B209 minimum strengths were not opened. The strengths here are typical or datasheet values, and the Aluminum Association values are marked NOT FOR DESIGN.
  - Galvanic coupling data for 5052 with other metals were not found in an open source read in this run.
  - 'No supplier safety data sheet for 5052 was read: the Wyman and Pine aluminium SDS PDFs were refused (403), and the Speira SDS is for a different reference-material product. Hazards are element-level PubChem data. Dust and fume from machining or welding are not recorded.'
  - 'Cryogenic data: no NIST 5052 page was found at the address tried, and the 2007 Korean paper on wrought aluminium alloys at very low temperature is in Korean and was not read.'
  - 'Space behaviour: no outgassing (TML and CVCM), atomic-oxygen, radiation or flight data for 5052 was found in the sources read, so side effects are left empty.'
  - 'Fatigue: only one value was found (H32, 117 MPa at 5.00 x 10^8 cycles). No S-N curves for O, H34 or H38 were read.'
  - Shear strength (138 MPa, H32) and Brinell hardness (60, H32) are on the Clinton datasheet but are left out, because neither name is in property-canon.yaml and no short name was added.
  - The USGS 2025 critical minerals list was not checked, because the USGS page returned a 403 block. Only the EU critical raw materials list is recorded for aluminium, bauxite and magnesium.
  - 'Chromium limit: the Smiths datasheet gives 0.25 % maximum, against 0.35 % in the Clinton datasheet and the NASA AMS4004D table. The file uses 0.35 %.'
  - 'Standards: AMS4004D and AMS QQ-A-250/8 (cited by NASA) and ASTM B209 were not opened. The SAE pages found show catalogue metadata only.'
  - No images or diagrams were added.
  - 'Designations not found in any source read in this run: EN AW-5052, EN 3.3523, DIN, JIS A5052, AFNOR, ASTM B209 and ASTM B210. No 5052 grade page could be read on the Aluminum Association, Kaiser or Constellium sites, the Aalco page returned an error, and the ASM (MatWeb), Metals Depot and Online Metals pages returned a bot challenge.'
sources:
  nasa-tm-2018-219753:
    title: Properties of 5052 Aluminum for Use as Honeycomb Core in Manned Spaceflight, NASA/TM-2018-219753 (Bradley A. Lerch, NASA Glenn Research Center)
    id: NASA/TM-2018-219753; NTRS 20180001568; February 2018
    url: https://ntrs.nasa.gov/api/citations/20180001568/downloads/20180001568.pdf
    year: 2018
    kind: report
    license: public domain (NASA)
  clinton-5052-h32:
    title: Aluminum 5052-H32 datasheet (Clinton Aluminum and Stainless Steel, copy hosted by Protolabs)
    id: Clinton datasheet; values marked AA are Aluminum Association data, NOT FOR DESIGN
    url: https://Protolabs.com/media/iw0mfa0k/datasheet-sm-aluminum5052-h32.pdf
    kind: datasheet
    license: datasheet copy (cited, not reproduced)
  smith-5052-datasheet:
    title: 5052 Aluminium Technical Datasheet (Smiths Metal Centres, UK)
    id: Smiths Metal Centres data sheet, copyright 2023
    url: https://www.smithmetal.com/pdf/aluminium/5xxx/5052.pdf
    year: 2023
    kind: datasheet
    license: distributor datasheet (cited, not reproduced)
  nasa-heritage-2019:
    title: Heritage Materials for Launch Vehicles and Spacecraft (Wayne Gamwell and Tracie Prater, NASA Marshall Space Flight Center)
    id: NTRS 20190020090; NASA Breakthrough Materials Workshop, April 2019
    url: https://ntrs.nasa.gov/citations/20190020090
    year: 2019
    kind: report
    license: public domain (NASA)
  trid-sea-grant-1985:
    title: 'Sea Grant Program on Marine Corrosion, Volume 3: Supporting Data, Localized Corrosion, Aluminum Alloys (Dexter and Hartt, 1985)'
    id: NOAA Sea Grant; TRID record 399688; University of Delaware and Florida Atlantic University
    url: https://trid.trb.org/View/399688
    year: 1985
    kind: report
    license: public record (TRID)
  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-alumina:
    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)
  usgs-mcs2026-magnesium-metal:
    title: Mineral Commodity Summaries 2026, Magnesium Metal
    id: USGS MCS 2026, February 2026
    url: https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-magnesium-metal.pdf
    year: 2026
    kind: report
    license: public domain (USGS)
  ec-crm-list:
    title: Critical raw materials (European Commission, list of critical raw materials)
    id: European Commission critical raw materials page
    url: https://single-market-economy.ec.europa.eu/sectors/raw-materials/areas-specific-interest/critical-raw-materials_en
    kind: web
    license: European Commission web page
  pubchem-al:
    title: 'Aluminum, PubChem compound CID 5359268: Safety and Hazards, GHS Classification'
    id: PubChem CID 5359268 (PUG View JSON, read 2026-10-24); 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 2026-10-24); aggregated from ECHA C&L notifications
    url: https://pubchem.ncbi.nlm.nih.gov/compound/5462224
    kind: database
    license: PubChem (NCBI) public data
  wikipedia-5052:
    title: 5052 aluminium alloy (Wikipedia), used for composition cross-check only
    url: https://en.wikipedia.org/wiki/5052_aluminium_alloy
    kind: web
    license: CC BY-SA 4.0 (cited, not reproduced)
license: CC-BY-4.0
updated: '2026-10-24'
review:
  status: draft
  method: assistant
  checked_values: 24
  unreachable: 8
  caveats: 3
  note: 'Written 2026-10-24 by an AI assistant from pages fetched in this run. NASA Table II values are datasheet values that NASA cites from Metal Suppliers Online and Alcoa, not NASA tests. Clinton values are Aluminum Association typicals marked NOT FOR DESIGN. The Smiths datasheet gives chromium 0.25 % maximum where the Clinton datasheet and the NASA AMS4004D table give 0.35 %. Unreachable: the MakeItFrom 5052 pages (a cookie challenge page), the USGS 2025 critical minerals page (403), the MDPI Metals 2026 corrosion article, the OSTI Alcoa seawater catalogue, the NRL DTIC report, the Aalco 5052-H32 datasheet (empty download), and the Wyman and Pine SDS PDFs (403).'
story:
  recipe:
    line: Wrought aluminium-magnesium alloy with 2.2 to 2.8 wt% magnesium and 0.15 to 0.35 wt% chromium, aluminium as the balance. NASA says the magnesium hardens the alloy and cold work adds strength, and the H temper code records the cold work and the stabilising heat treatment that follows (NASA TM, p. 2).
    parts:
      - name: Aluminium
        symbol: Al
        share_note: balance; 95.7 to 97.7 wt% per the Clinton datasheet
        role: The matrix of the alloy. Its thin oxide film gives the corrosion resistance.
        source: clinton-5052-h32
        where: Component Elements table
      - name: Magnesium
        symbol: Mg
        share_percent: 2.2
        share_high: 2.8
        role: Main strengthening element. NASA says the alloy is hardened by magnesium (NASA TM, p. 1).
        source: clinton-5052-h32
        where: Component Elements table
      - name: Chromium
        symbol: Cr
        share_percent: 0.15
        share_high: 0.35
        role: Minor addition inside the composition limits; the AMS4004D chromium range is the same (NASA TM Table I).
        source: clinton-5052-h32
        where: Component Elements table
      - name: Silicon
        symbol: Si
        share_note: maximum 0.25
        role: Impurity, held to a maximum limit.
        source: clinton-5052-h32
        where: Component Elements table
      - name: Iron
        symbol: Fe
        share_note: maximum 0.40
        role: Impurity, held to a maximum limit.
        source: clinton-5052-h32
        where: Component Elements table
      - name: Copper
        symbol: Cu
        share_note: maximum 0.10
        role: Impurity, held to a maximum limit.
        source: clinton-5052-h32
        where: Component Elements table
      - name: Manganese
        symbol: Mn
        share_note: maximum 0.10
        role: Impurity, held to a maximum limit.
        source: clinton-5052-h32
        where: Component Elements table
      - name: Zinc
        symbol: Zn
        share_note: maximum 0.10
        role: Impurity, held to a maximum limit.
        source: clinton-5052-h32
        where: Component Elements table
  risk_groups:
    - title: For people
      lead: No supplier safety data sheet for 5052 was read in this run. The element-level PubChem GHS data for aluminium and magnesium is in the hazards list, but this profile records no toxicity or dust data for the alloy.
      gap: Hazard classification of 5052 as supplied, and of dust or fume from machining or welding, was not found in a source opened in this run.
      points:
        - label: What the sources cover
          line: The sources read describe corrosion, fatigue and temper behaviour, not health effects. Before cutting, grinding or welding, read the supplier's safety data sheet for the exact product.
    - title: If it fails
      lead: These failure routes come from the NASA technical memorandum, which tested honeycomb core and foil. They are test results, not field incident data.
      points:
        - label: Core crushing
          line: In flatwise compression tests the maximum stress before a 5052 core buckled ranged from 165 to 219 psi, with two failure modes seen in the samples.
        - label: Softening during cure
          line: A non-stabilised temper (H19 or H191) softens during panel cure. In the test, H39 foil lost about 10 % of its tensile strength after a 1 hour age at 400 °F and 15 % after 8 hours.
        - label: Seawater
          line: The seawater rating is a datasheet claim. No measured rate or galvanic result for 5052 was read, so this profile cannot say how fast it corrodes in sea water.
    - title: Handling and storage
      points:
        - label: Temper
          line: Name the temper on every order and check it on receipt. The report says honeycomb is often bought with no temper stated, and recommends H38 or H39 for aerospace use.
        - label: Annealing and hot work
          line: The datasheet gives an annealing temperature of 343 °C (650 °F), with no hold needed, and hot working between 260 and 510 °C (500 and 950 °F).
        - label: Stabilising
          line: H19 and H191 are not stabilised and should not be used in sandwich cures (NASA TM, p. 2).
  why: Aluminium alloy 5052 is a wrought alloy, meaning it is worked into sheet, plate, tube or shapes. Its main addition is magnesium, at 2.2 to 2.8 wt%, with a little chromium. NASA says magnesium hardens the alloy and cold work adds strength, and the temper code (for example H32 or H38) records how much cold work was given. This profile covers the O, H32, H34 and H38 tempers and keeps them apart. The wider family is described on the [5XXX family page](/materials/aluminium-5xxx), which this page does not repeat. Datasheets rate the alloy very good against seawater, which is why marine parts appear among its listed uses.
  uses:
    - where: Spacecraft structural materials
      line: NASA's heritage presentation lists 5052-H32 among the aluminium alloys used for spacecraft structures, next to 6061 and 7075.
    - where: Honeycomb core of sandwich panels
      line: 5052 honeycomb is the core of many composite sandwich panels for light structures. NASA says the core matters most when off-axis loads act on it, and it recommends H38 or H39 for aerospace use.
    - where: Fuel and oil lines and tanks
      line: The Clinton datasheet says the alloy is used for aircraft fuel and oil lines and fuel tanks.
    - where: Marine components and pressure vessels
      line: A UK distributor datasheet lists marine components, containers and pressure vessels among typical applications.
  can_do:
    - label: Strength by temper
      value: 13 ksi (O) to 37 ksi (H38) yield
      line: Yield strength rises from 13 ksi annealed (O) through 28 ksi (H32), 31 ksi (H34) and 37 ksi (H38). Elongation falls over the same steps, from 25 % to 7 %. These are NASA's datasheet values, and each belongs to its own temper.
    - label: Typical strength in H32
      value: 193 MPa yield, 228 MPa ultimate
      line: In the H32 temper the Aluminum Association typical yield strength is 193 MPa and the ultimate tensile strength is 228 MPa. The datasheet marks these not for design. Elongation is 12 % at 1.59 mm thickness and 18 % on a 12.7 mm round specimen.
    - label: Stiffness and weight
      value: 2.68 g/cc and 70.3 GPa
      line: Density is 2.68 g/cc and the modulus of elasticity is 70.3 GPa (H32, average of tension and compression).
    - label: Fatigue
      value: 117 MPa at 500,000,000 cycles
      line: The fatigue strength is 117 MPa after 500,000,000 cycles of completely reversed stress, in an RR Moore test on H32 material.
    - label: Heat conduction
      value: 138 W/m-K at 77 °F
      line: Thermal conductivity is 138 W/m-K at 77 °F.
    - label: Thermal expansion
      value: 24.8 µm/m-°C
      line: Between 20 and 200 °C the mean coefficient of thermal expansion is 24.8 µm/m-°C, which is the same as ppm/K.
  compare: The record supports only a limited comparison. This profile holds no strength or price figures for other alloys read in this run, so it does not rank 5052 against them. The USGS lists composites, magnesium, steel and titanium as substitutes for aluminium in ground transport, and copper for electrical and heat-exchange uses. The sibling heat-treatable alloy page is linked from the [5XXX family page](/materials/aluminium-5xxx), which holds the wider series.
  compare_rows:
    - label: Density
      benchmark: density
    - label: Thermal conductivity
      benchmark: thermal_conductivity
    - label: Thermal expansion
      benchmark: cte
  handling:
    - Anneal at 343 °C (650 °F) with no hold time needed, according to the datasheet.
    - Hot work between 260 and 510 °C (500 and 950 °F).
    - Name the temper on every order and check it on receipt. Keep H19 and H191 out of sandwich cures.
    - Read the supplier's safety data sheet before cutting, grinding or welding.
  good_for:
    - Sheet and plate that needs medium strength, good weldability and seawater resistance (datasheet ratings), with the temper named.
    - Honeycomb core and fuel line or tank parts where the temper is fixed (NASA recommends H38 or H39 for aerospace).
    - Marine parts, on the strength of a datasheet claim of very good seawater resistance (not measured here).
  watch_out:
    - Strength depends on temper. Yield runs from 13 ksi annealed to 37 ksi in H38, so always name the temper.
    - The datasheet strengths are Aluminum Association typicals marked not for design. No design allowables (MMPDS, ASTM B209 minimums) were read.
    - No measured seawater corrosion rate or galvanic result for 5052 was found, so the marine rating is not a measured value.
    - 'Chromium limits differ between sources: the Smiths datasheet gives a 0.25 % maximum, and the Clinton datasheet and the NASA table give 0.35 %.'
  verdict: 5052 is a magnesium-hardened alloy whose strength is set by its temper, with a datasheet rating of very good seawater resistance. Name the temper on every order, and treat the seawater rating as a datasheet claim until a measured corrosion rate is read.