Aluminium alloy 5052 5052
Al-Mg alloy, UNS A95052
Also known as UNS A95052, ISO AlMg2.5, AA 5052, AMS 4004D, AMS A81596, AMS QQ-A-250/8
5052 is a wrought aluminium-magnesium alloy (UNS A95052) with 2.20 to 2.80 wt% magnesium.
Evidence level
2 of 5
Lab-measured
- 0Predicted only. No one has made it, or no measurement exists.
- 1Calculated. Only calculated or predicted values from sources.
- 2Lab-measured. Measured properties with their conditions stated.
- 3Space-relevant tests. Measured in conditions relevant to space, such as vacuum or atomic oxygen.
- 4Ground-qualified. Qualified for an application on the ground.
- 5Flown or field-proven. Flight or field results exist.
Strength by temper
13 ksi (O) to 37 ksi (H38) yield
Typical strength in H32
193 MPa yield, 228 MPa ultimate
Stiffness and weight
2.68 g/cc and 70.3 GPa
Fatigue
117 MPa at 500,000,000 cycles
Heat conduction
138 W/m-K at 77 °F
Recipe, share of the weight
- Al balance; 95.7 to 97.7 wt% per the Clinton datasheetAluminium
- Mg 2.2 to 2.8%Magnesium
- Cr 0.15 to 0.35%Chromium
- Si maximum 0.25Silicon
- Fe maximum 0.40Iron
- Cu maximum 0.10Copper
- Mn maximum 0.10Manganese
- Zn maximum 0.10Zinc
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
Risk at a glance
- People No data. No hazard data recorded
- If it fails Moderate. Core crushing under flatwise compression
- Corrosion Low. The Smiths datasheet rates 5052-H32 very good against seawater and marine atmospheres.
Quick facts: 5052
| Property | Value | Basis |
|---|---|---|
| Density | 2.68 g/cm³ | 1 sourced value |
| Yield strength | 89.6 to 255 MPa | 5 sourced values across conditions |
| Tensile strength | 193 to 290 MPa | 5 sourced values across conditions |
| Young's modulus | 70.3 GPa | 1 sourced value |
| Thermal conductivity | 138 W/(m·K) | 1 sourced value |
| Thermal expansion (CTE) | 24.8 ppm/K | 1 sourced value |
| Melting point | 607 to 649 °C | 1 sourced value |
What is the density of Aluminium alloy 5052?
Aluminium alloy 5052 has a density of 2.68 g/cm³. The source and test conditions are listed in the properties table on this page.
What is the thermal conductivity of Aluminium alloy 5052?
Aluminium alloy 5052 has a thermal conductivity of 138 W/(m·K). The source and test conditions are listed in the properties table on this page.
What is the coefficient of thermal expansion of Aluminium alloy 5052?
Aluminium alloy 5052 has a coefficient of thermal expansion of 24.8 ppm/K. The source and test conditions are listed in the properties table on this page.
What is the melting point of Aluminium alloy 5052?
Aluminium alloy 5052 has a melting point of 607 to 649 °C. The source and test conditions are listed in the properties table on this page.
What is the yield strength of Aluminium alloy 5052?
Aluminium alloy 5052 has a yield strength of 89.6 to 255 MPa. The range covers 5 sourced values across the tempers, forms and test conditions the sources report; room-temperature values are used where a source states a temperature.
What are the other names and codes for Aluminium alloy 5052?
Aluminium alloy 5052 is also written as UNS A95052, ISO AlMg2.5, AA 5052, AMS 4004D, AMS A81596, AMS QQ-A-250/8. Each code is printed in the source listed beside it in the designations table.
What is Aluminium alloy 5052 used for?
Uses recorded in the sources include Honeycomb core of composite sandwich panels for lightweight structures; Spacecraft structural materials list, next to 6061-T6, 6061-T651 and 7075; Aircraft fuel and oil lines, and fuel tanks.
Why it exists
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.
Where it's used
Spacecraft structural materials
NASA's heritage presentation lists 5052-H32 among the aluminium alloys used for spacecraft structures, next to 6061 and 7075.
Honeycomb core of sandwich panels
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.
Fuel and oil lines and tanks
The Clinton datasheet says the alloy is used for aircraft fuel and oil lines and fuel tanks.
Marine components and pressure vessels
A UK distributor datasheet lists marine components, containers and pressure vessels among typical applications.
Recipe
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)
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).
| Ingredient | Share of the weight | What it does |
|---|---|---|
| Aluminium Al | balance; 95.7 to 97.7 wt% per the Clinton datasheet | The matrix of the alloy. Its thin oxide film gives the corrosion resistance. |
| Magnesium Mg | 2.2 to 2.8% | Main strengthening element. NASA says the alloy is hardened by magnesium (NASA TM, p. 1). |
| Chromium Cr | 0.15 to 0.35% | Minor addition inside the composition limits; the AMS4004D chromium range is the same (NASA TM Table I). |
| Silicon Si | maximum 0.25 | Impurity, held to a maximum limit. |
| Iron Fe | maximum 0.40 | Impurity, held to a maximum limit. |
| Copper Cu | maximum 0.10 | Impurity, held to a maximum limit. |
| Manganese Mn | maximum 0.10 | Impurity, held to a maximum limit. |
| Zinc Zn | maximum 0.10 | Impurity, held to a maximum limit. |
Weight shares are as printed in the sources.
What it can do
Strength by temper
13 ksi (O) to 37 ksi (H38) yield
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.
Typical strength in H32
193 MPa yield, 228 MPa ultimate
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.
Stiffness and weight
2.68 g/cc and 70.3 GPa
Density is 2.68 g/cc and the modulus of elasticity is 70.3 GPa (H32, average of tension and compression).
Fatigue
117 MPa at 500,000,000 cycles
The fatigue strength is 117 MPa after 500,000,000 cycles of completely reversed stress, in an RR Moore test on H32 material.
Heat conduction
138 W/m-K at 77 °F
Thermal conductivity is 138 W/m-K at 77 °F.
Thermal expansion
24.8 µm/m-°C
Between 20 and 200 °C the mean coefficient of thermal expansion is 24.8 µm/m-°C, which is the same as ppm/K.
How it compares
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.
The same measurements for each material, so you can compare them. Each row names the key condition under the value; the full conditions and methods are in the numbered notes under Technical details. Other materials are shown beside it; each was measured under its own conditions, so open its page before comparing closely. Compare every grade in the family.
| Measurement | 5052 | 6061 | 7075-T6 | 2024 | 5XXX | 2195 (Al-Cu-Li) | Al | 1050 | 2011 | 2014 | 2017 | 2017A | 2219 | 2319 | 2618A | 3003 | 3103 | 4047 | 5019 | 5056 | 5083 | AlMg2 | AlMg3 | 6013 | 6063 | 6082 | 6101 | AA7050 | AA8011 | Au-Al IMCs | Al master alloys |
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Thermal behavior and safety | |||||||||||||||||||||||||||||||
| Thermal conductivity, typical, H32 | 138 W/m-K20 | 167 W/(m·K) | 130 W/m·K | 121 W/m-K | 138 W/(m·K) | no data | 220 W/(m·K) | 229 W/m.K | 140 W/m.K | 138 W/(m·K) | 140 W/m.K | 140 W/m.K | 130 W.m/m2.°C | no data | 147 W/m.K | 190 W/m.K | 160 W/m.K | no data | 110 to 140 W/(m·K) | 109 to 117 W/(m·K) | 121 W/(m·K) | 138 W/(m·K) | 140 to 160 W/(m·K) | 164 W/(m·K) | 200 W/(m·K) | 180 W/(m·K) | no data | 154 W/(m·K) | 210 to 220 W/(m·K) | no data | no data |
| Melting range, solidus to liquidus, typicalTypical range listed in a datasheet | 607.2 to 649 °C22 | no data | 532 °C | no data | no data | 1020 degF | 660 °C | 645 to 657 °C | 540 °C | 535 °C | 510 °C | 510 °C | 543 °C | 543 to 643 °C | 549 °C | 655 °C | 655 °C | 1068 to 1080 °F | 575 to 630 °C | 565 to 640 °C | 570 °C | 605 to 650 °C | 590 to 645 °C | 579 °C | 600 °C | 575 °C | 1090 °F | 490 °C | 640 to 655 °C | no data | 880 °C |
| Physical and electrical | |||||||||||||||||||||||||||||||
| Density, typical, H32 | 2.68 g/cc19 | 2.7 g/cm³ | 2.8 Mg/m3 | 2.78 g/cc | 2.68 g/cm³ | 0.096 lb/in3 | 2.7 g/cm³ | 2.71 g/cm³ | 2.82 g/cm³ | 2.82 g/cm³ | 2.79 g/cm³ | 2.79 g/cm³ | 2.84 g/cm³ | 2.84 g/cm³ | 2.76 g/cm³ | 2.73 g/cm³ | 2.73 g/cm³ | 2.65 g/cm³ | 2.64 g/cm³ | 2.64 g/cm³ | 2.65 g/cm³ | 2.69 g/cm³ | 2.67 g/cm³ | 2.71 g/cm³ | 2700 kg/m3 | 2.7 g/cm³ | 0.097 lb/cu.in | 2.83 g/cm³ | 2.71 g/cm³ | no data | no data |
| Other measurements | |||||||||||||||||||||||||||||||
| Ultimate tensile strength, datasheet value, O (annealed) | 28 ksi1 | 310 MPa | 572 MPa | 469 MPa | 228 MPa | 80 ksi | 88 MPa | 105 to 145 MPa | 300 MPa | > 460 MPa | 427 MPa | 427 MPa | > 62 ksi | 160 MPa | 420 MPa | 110 MPa | > 140 MPa | 124 MPa | 270 to 350 MPa | 300 MPa | 275 to 350 MPa | 190 to 230 MPa | 190 to 260 MPa | 410 MPa | 27 ksi | > 300 MPa | 32000 psi | > 483 MPa | 180 to 195 MPa | no data | no data |
| Yield strength, datasheet value, O (annealed) | 13 ksi2 | 276 MPa | 503 MPa | 324 MPa | 193 MPa | 74 ksi | 29 MPa | > 85 MPa | 140 MPa | > 400 MPa | 276 MPa | 276 MPa | > 50 ksi | 70 MPa | 350 MPa | 50 MPa | > 110 MPa | 55 MPa | no data | no data | > 125 MPa | > 120 MPa | > 80 MPa | 350 MPa | 21 ksi | > 255 MPa | 28000 psi | > 414 MPa | no data | no data | no data |
| Elongation at break, datasheet value, O (annealed) | 25 %3 | 17 % | 11 % | 19 % | 12 % | 8 % | 50 to 65 % | 4 to 8 % | 16 % | > 6 % | 18 % | 18 % | > 6 % | 12 % | > 5 % | 25 % | > 8 % | 12 % | > 2 % | 20 % | > 12 % | 4 to 12 % | > 12 % | 4 % | 8 % | > 9 % | > 8 % | > 7 % | > 1 % | no data | no data |
| Ultimate tensile strength, datasheet value, H32 | 33 ksi4 | 310 MPa | 572 MPa | 469 MPa | 228 MPa | 80 ksi | 88 MPa | 105 to 145 MPa | 300 MPa | > 460 MPa | 427 MPa | 427 MPa | > 62 ksi | 160 MPa | 420 MPa | 110 MPa | > 140 MPa | 124 MPa | 270 to 350 MPa | 300 MPa | 275 to 350 MPa | 190 to 230 MPa | 190 to 260 MPa | 410 MPa | 27 ksi | > 300 MPa | 32000 psi | > 483 MPa | 180 to 195 MPa | no data | no data |
| Yield strength, datasheet value, H32 | 28 ksi5 | 276 MPa | 503 MPa | 324 MPa | 193 MPa | 74 ksi | 29 MPa | > 85 MPa | 140 MPa | > 400 MPa | 276 MPa | 276 MPa | > 50 ksi | 70 MPa | 350 MPa | 50 MPa | > 110 MPa | 55 MPa | no data | no data | > 125 MPa | > 120 MPa | > 80 MPa | 350 MPa | 21 ksi | > 255 MPa | 28000 psi | > 414 MPa | no data | no data | no data |
| Elongation at break, datasheet value, H32 | 12 %6 | 17 % | 11 % | 19 % | 12 % | 8 % | 50 to 65 % | 4 to 8 % | 16 % | > 6 % | 18 % | 18 % | > 6 % | 12 % | > 5 % | 25 % | > 8 % | 12 % | > 2 % | 20 % | > 12 % | 4 to 12 % | > 12 % | 4 % | 8 % | > 9 % | > 8 % | > 7 % | > 1 % | no data | no data |
| Ultimate tensile strength, datasheet value, H34 | 38 ksi7 | 310 MPa | 572 MPa | 469 MPa | 228 MPa | 80 ksi | 88 MPa | 105 to 145 MPa | 300 MPa | > 460 MPa | 427 MPa | 427 MPa | > 62 ksi | 160 MPa | 420 MPa | 110 MPa | > 140 MPa | 124 MPa | 270 to 350 MPa | 300 MPa | 275 to 350 MPa | 190 to 230 MPa | 190 to 260 MPa | 410 MPa | 27 ksi | > 300 MPa | 32000 psi | > 483 MPa | 180 to 195 MPa | no data | no data |
| Yield strength, datasheet value, H34 | 31 ksi8 | 276 MPa | 503 MPa | 324 MPa | 193 MPa | 74 ksi | 29 MPa | > 85 MPa | 140 MPa | > 400 MPa | 276 MPa | 276 MPa | > 50 ksi | 70 MPa | 350 MPa | 50 MPa | > 110 MPa | 55 MPa | no data | no data | > 125 MPa | > 120 MPa | > 80 MPa | 350 MPa | 21 ksi | > 255 MPa | 28000 psi | > 414 MPa | no data | no data | no data |
| Elongation at break, datasheet value, H34 | 10 %9 | 17 % | 11 % | 19 % | 12 % | 8 % | 50 to 65 % | 4 to 8 % | 16 % | > 6 % | 18 % | 18 % | > 6 % | 12 % | > 5 % | 25 % | > 8 % | 12 % | > 2 % | 20 % | > 12 % | 4 to 12 % | > 12 % | 4 % | 8 % | > 9 % | > 8 % | > 7 % | > 1 % | no data | no data |
| Ultimate tensile strength, datasheet value, H38 | 42 ksi10 | 310 MPa | 572 MPa | 469 MPa | 228 MPa | 80 ksi | 88 MPa | 105 to 145 MPa | 300 MPa | > 460 MPa | 427 MPa | 427 MPa | > 62 ksi | 160 MPa | 420 MPa | 110 MPa | > 140 MPa | 124 MPa | 270 to 350 MPa | 300 MPa | 275 to 350 MPa | 190 to 230 MPa | 190 to 260 MPa | 410 MPa | 27 ksi | > 300 MPa | 32000 psi | > 483 MPa | 180 to 195 MPa | no data | no data |
| Yield strength, datasheet value, H38 | 37 ksi11 | 276 MPa | 503 MPa | 324 MPa | 193 MPa | 74 ksi | 29 MPa | > 85 MPa | 140 MPa | > 400 MPa | 276 MPa | 276 MPa | > 50 ksi | 70 MPa | 350 MPa | 50 MPa | > 110 MPa | 55 MPa | no data | no data | > 125 MPa | > 120 MPa | > 80 MPa | 350 MPa | 21 ksi | > 255 MPa | 28000 psi | > 414 MPa | no data | no data | no data |
| Elongation at break, datasheet value, H38 | 7 %12 | 17 % | 11 % | 19 % | 12 % | 8 % | 50 to 65 % | 4 to 8 % | 16 % | > 6 % | 18 % | 18 % | > 6 % | 12 % | > 5 % | 25 % | > 8 % | 12 % | > 2 % | 20 % | > 12 % | 4 to 12 % | > 12 % | 4 % | 8 % | > 9 % | > 8 % | > 7 % | > 1 % | no data | no data |
| Ultimate tensile strength, typical, H32 | 228 MPa13 | 310 MPa | 572 MPa | 469 MPa | 228 MPa | 80 ksi | 88 MPa | 105 to 145 MPa | 300 MPa | > 460 MPa | 427 MPa | 427 MPa | > 62 ksi | 160 MPa | 420 MPa | 110 MPa | > 140 MPa | 124 MPa | 270 to 350 MPa | 300 MPa | 275 to 350 MPa | 190 to 230 MPa | 190 to 260 MPa | 410 MPa | 27 ksi | > 300 MPa | 32000 psi | > 483 MPa | 180 to 195 MPa | no data | no data |
| Yield strength, typical, H32 | 193 MPa14 | 276 MPa | 503 MPa | 324 MPa | 193 MPa | 74 ksi | 29 MPa | > 85 MPa | 140 MPa | > 400 MPa | 276 MPa | 276 MPa | > 50 ksi | 70 MPa | 350 MPa | 50 MPa | > 110 MPa | 55 MPa | no data | no data | > 125 MPa | > 120 MPa | > 80 MPa | 350 MPa | 21 ksi | > 255 MPa | 28000 psi | > 414 MPa | no data | no data | no data |
| Elongation at break, typical, H32, 1.59 mm thickness | 12 %15 | 17 % | 11 % | 19 % | 12 % | 8 % | 50 to 65 % | 4 to 8 % | 16 % | > 6 % | 18 % | 18 % | > 6 % | 12 % | > 5 % | 25 % | > 8 % | 12 % | > 2 % | 20 % | > 12 % | 4 to 12 % | > 12 % | 4 % | 8 % | > 9 % | > 8 % | > 7 % | > 1 % | no data | no data |
| Elongation at break, typical, H32, 12.7 mm round specimen | 18 %16 | 17 % | 11 % | 19 % | 12 % | 8 % | 50 to 65 % | 4 to 8 % | 16 % | > 6 % | 18 % | 18 % | > 6 % | 12 % | > 5 % | 25 % | > 8 % | 12 % | > 2 % | 20 % | > 12 % | 4 to 12 % | > 12 % | 4 % | 8 % | > 9 % | > 8 % | > 7 % | > 1 % | no data | no data |
| Modulus of elasticity, typical, H32 | 70.3 GPa17 | 68.9 GPa | 71 GPa | 73.1 GPa | 70.3 GPa | 11 MSI | 69 GPa | 69000 MPa | 70 GPa | 71 GPa | 72 GPa | 72 GPa | 73.8 x10^3 N/mm2 | no data | 71 GPa | 69.5 GPa | 69.5 GPa | no data | 70 GPa | 71 GPa | 72 GPa | 70 GPa | 70 GPa | 71 GPa | 69.5 GPa | 70 GPa | no data | 71.5 GPa | 70 GPa | no data | no data |
| Fatigue strength at 500,000,000 cycles, typical, H32Value listed in a datasheet | 117 MPa18 | 96.5 MPa | 158 MPa | 138 MPa | 117 MPa | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data |
| Shear modulus, H32Value listed in a datasheet | 25.9 GPa | no data | 3.9 10^3 ksi | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data |
| Poisson's ratio, H32Value listed in a datasheet | 0.33 - | no data | 0.33 - | no data | no data | no data | no data | no data | no data | no data | no data | no data | 0.33 - | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data | no data |
| Mean coefficient of thermal expansion, 20 to 200 °C, H32Value listed in a datasheet | 24.8 µm/m-°C21 | 23.6 ppm/K | 23.4 µm/m·K | 23.2 ppm/K | 24 ppm/K | no data | 22.5 ppm/K | 23.5 x10-6/K | 21.4 µm/m.°C | 23 ppm/K | 22.9 µm/(m·°C) | 22.9 µm/m.°C | 22.5 x10^-6 m/m.°C | no data | 21.6 µm/m°C | 23.1 ppm/K | 23.1 x10-6/K | no data | no data | 2.41×10^-5 1/K | 25 ppm/K | 23.8 µm/m/°C | 23.9 ppm/K | 21.7 µm/m°C | 23.5 ppm/K | 23.1 ppm/K | no data | 23.5 ppm/K | 2.35×10^-5 1/K | no data | no data |
Why choose it, and why not
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 for
- 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 %.
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.
Technical details
For scientists and researchers. Everything above comes from the record below: every number with its method, its conditions and its source.
Other names and standards
The same grade under other systems, as datasheets and standards print them. Each code was checked against the page it comes from.
| System | Codes |
|---|---|
| UNS | A95052 |
| ISO | AlMg2.5 |
| AA | 5052 |
| AMS | 4004D (foil, strain hardened), A81596 (foil for sandwich construction), QQ-A-250/8 (plate and sheet) |
Notes
The method, full conditions and any caveat for the numbered rows above.
| # | Measurement | Method | Conditions | Caveat |
|---|---|---|---|---|
| 1 | Ultimate tensile strength, datasheet value, O (annealed) | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper O (annealed)product form bulk material (product form not stated)temperature not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 2 | Yield strength, datasheet value, O (annealed) | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper O (annealed)product form bulk material (product form not stated)temperature not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 3 | Elongation at break, datasheet value, O (annealed) | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper O (annealed)product form bulk material (product form not stated)specimen not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 4 | Ultimate tensile strength, datasheet value, H32 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H32product form bulk material (product form not stated)temperature not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 5 | Yield strength, datasheet value, H32 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H32product form bulk material (product form not stated)temperature not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 6 | Elongation at break, datasheet value, H32 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H32product form bulk material (product form not stated)specimen not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 7 | Ultimate tensile strength, datasheet value, H34 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H34product form bulk material (product form not stated)temperature not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 8 | Yield strength, datasheet value, H34 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H34product form bulk material (product form not stated)temperature not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 9 | Elongation at break, datasheet value, H34 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H34product form bulk material (product form not stated)specimen not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 10 | Ultimate tensile strength, datasheet value, H38 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H38product form bulk material (product form not stated)temperature not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 11 | Yield strength, datasheet value, H38 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H38product form bulk material (product form not stated)temperature not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 12 | Elongation at break, datasheet value, H38 | Datasheet value tabulated by NASA (Table II); the authors did not test it | temper H38product form bulk material (product form not stated)specimen not statedbasis datasheet value that NASA cites from Metal Suppliers Online and Alcoa | — |
| 13 | Ultimate tensile strength, typical, H32 | Typical value listed in a datasheet (Aluminum Association data) | temper H32 (datasheet title Aluminum 5052-H32)product form not statedtemperature not statedbasis Aluminum Association typical value, marked NOT FOR DESIGN | — |
| 14 | Yield strength, typical, H32 | Typical value listed in a datasheet (Aluminum Association data) | temper H32 (datasheet title Aluminum 5052-H32)product form not statedtemperature not statedbasis Aluminum Association typical value, marked NOT FOR DESIGN | — |
| 15 | Elongation at break, typical, H32, 1.59 mm thickness | Typical value listed in a datasheet (Aluminum Association data) | temper H32 (datasheet title Aluminum 5052-H32)specimen thickness 1.59 mm (0.0625 in)product form not statedbasis Aluminum Association typical value, marked NOT FOR DESIGN | — |
| 16 | Elongation at break, typical, H32, 12.7 mm round specimen | Typical value listed in a datasheet (Aluminum Association data) | temper H32 (datasheet title Aluminum 5052-H32)specimen round, diameter 12.7 mm (0.500 in)product form not statedbasis Aluminum Association typical value, marked NOT FOR DESIGN | — |
| 17 | Modulus of elasticity, typical, H32 | Typical value listed in a datasheet (Aluminum Association data) | temper H32 (datasheet title Aluminum 5052-H32)basis Aluminum Association typical; average of tension and compression, compression about 2 % greater than tension (datasheet comment) | — |
| 18 | Fatigue strength at 500,000,000 cycles, typical, H32 | — | temper H32 (datasheet title Aluminum 5052-H32)loading completely reversed stresstest RR Moore machine and specimencycles 5.00 x 10^8 (500,000,000)basis datasheet value, no basis comment printed | — |
| 19 | Density, typical, H32 | Typical value listed in a datasheet (Aluminum Association data) | temper H32 (datasheet title Aluminum 5052-H32)temperature not statedbasis Aluminum Association typical | — |
| 20 | Thermal conductivity, typical, H32 | Typical value listed in a datasheet (Aluminum Association data) | temper H32 (datasheet title Aluminum 5052-H32)temperature 77 °Fbasis Aluminum Association typical at 77 °F | — |
| 21 | Mean coefficient of thermal expansion, 20 to 200 °C, H32 | — | 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/Kbasis no basis comment printed on this row | — |
| 22 | Melting range, solidus to liquidus, typical | — | basis Aluminum Association typical range for typical composition of wrought products 1/4 inch thickness or greatersolidus 607.2 °Cliquidus 649 °C | — |
Corrosion and compatibility
What happens when it meets other materials and environments.
| Environment | Concern | What happens |
|---|---|---|
| Seawater and marine atmosphere (datasheet rating for H32) | low | The Smiths datasheet rates 5052-H32 very good against seawater and marine atmospheres.1 |
| Atmospheres, no environment named (datasheet rating) | low | The Clinton datasheet also rates 5052-H32 very good for corrosion, without naming an environment.2 |
| Sea water, stagnant and flowing (aluminium alloys in general, 1985 study) | not rated | Aluminium corrodes in sea water by different routes from sodium chloride solution, and faster flow reduces attack.3 |
| # | Environment | Details | Test conditions |
|---|---|---|---|
| 1 | Seawater and marine atmosphere (datasheet rating for H32) | 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. | temper H32 (the datasheet says its properties are for H32)basis distributor rating, not a test result |
| 2 | Atmospheres, no environment named (datasheet rating) | 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. | temper H32 (datasheet title Aluminum 5052-H32)basis general statement in the material notes |
| 3 | Sea water, stagnant and flowing (aluminium alloys in general, 1985 study) | 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. | basis abstract of a 1985 report on aluminium alloys; 5052 is not named in the abstract |
Risks and side effects
Hazards to people, what happens when a cell overheats, and how the material is handled and stored.
For people
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.
- What the sources cover
- 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.
- Not covered
- 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.
If it fails
These failure routes come from the NASA technical memorandum, which tested honeycomb core and foil. They are test results, not field incident data.
- Core crushing
- 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.
- Softening during cure
- 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.
- Seawater
- 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.
Handling and storage
- Temper
- 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.
- Annealing and hot work
- 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).
- Stabilising
- H19 and H191 are not stabilised and should not be used in sandwich cures (NASA TM, p. 2).
Test details
The original wording and numbers from the sources, for readers who want them.
Failure risks
| Failure | Trigger and consequence |
|---|---|
| Core crushing under flatwise compressionmoderate severity | Off-axis loads on a 5052 honeycomb core in a sandwich panelIn 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. |
| Softening during high-temperature curemoderate severity | A non-stabilised temper (H19 or H191), or a stabilised H39 foil held at a high cure temperature for a long timeH39 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 %. |
Handling and storage
- Anneal at 343 °C (650 °F); holding at temperature is not required.
- Hot work between 260 and 510 °C (500 and 950 °F).
- 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.
- Do not use H19 or H191 in sandwich composites, because they are not stabilised and will soften during panel cure.
Mitigations
- Use a stabilised temper, H38 or H39, for aerospace core, as the report recommends.
- 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.
Supply and geography
How common the raw materials are and where they come from.
Aluminium (primary smelter production)
- Top producers (2025)
- China 60.8%, India 5.7%, Russia 5.3%, Canada 4.5%, United Arab Emirates 3.6%
- Critical mineral lists
- EU: listed
- 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.
Bauxite (aluminium ore)
- Top producers (2025)
- Guinea 34.1%, Australia 22%, China 19.8%, Brazil 7.5%, India 5.7%
- Critical mineral lists
- EU: listed
- 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.
Magnesium metal
USGS: magnesium resources range from large to virtually unlimited and are globally widespread; magnesium could be recovered from seawater along world coastlines.
- Top producers (2025)
- China 86.4%, Russia 5.5%, Brazil 1.8%, Israel 1.8%, Turkey 1.4%
- Critical mineral lists
- EU: listed
- 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.
Documents
Datasheets, safety data sheets, papers and standards you can open.
Full record
The complete spore, as stored. Free to reuse under CC-BY-4.0. Images keep the licence shown with each one.
Show the full YAML
spore: profile
id: aluminium-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.
References
Every number above carries a reference number. Click one to see the source and where in it the value comes from.