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Aluminum Sheet
Introduction to Aluminum AlloysAluminum is designated by its major corresponding alloying elements. A system of 4 digit numerical designations is used to identify wrought aluminum and wrought aluminum alloys. The first digit indicates the alloy group as follows: Aluminum alloys grouped by major alloying elements
Typical Physical Properties of All Aluminum Alloys
Descriptions of Individual Aluminum Alloys1100 Aluminum SheetLow strength aluminum alloy has excellent corrosion resistance and satisfactory anodizing and conversion coating finishing characteristics. It is unmatched by any other commercial aluminum alloy in workability. Readily to welding, brazing, and soldering. Machinability is poor and tends to be "gummy". Non-heat treatable. Typical applications include chemical storage, processing equipment, kitchen utensils, and general sheet metal work. 2014 Aluminum SheetAlloy must have a protective finish in order to have fair corrosion resistance, resulting this to be mainly in Alcad form. Very high strength at normal and high temperatures, satisfactory finishability, fair to good workability and weldability, and good machinability. Heat treatable. 2024 Aluminum SheetAlloy 2024 was introduced as an alclad sheet in the T3 temper. It was the first Al-Cu-Mg alloy to have a yield strength approaching 50,000-psi and generally replaced 2017-T4 (Duralumin) as the predominant 2XXX series aircraft alloy. With its relatively good fatigue resistance, especially in thick plate forms, alloy 2024 continues to be specified for many aerospace structural applications. 2024 variant alloys, such as higher purity 2124 and 2324, with improvements in strength and other specific characteristics, have also found application in critical aircraft structures. An improved sheet alloy for fuselage applications was introduced in 1991. Alclad C188 offers improved fracture toughness and fatigue crack growth while maintaining the strength characteristics of 2024. It is considered as the "aircraft" alloy because of its strength. Good machinability but only fair corrosion resistance. Heat treatable. Not recommended for brazing or soldering. Good workability. Good appearance. Typical Chemical Analysis (max)
Note: Value maximum if range not shown. 2124 Aluminum SheetAlloy 2124 was developed primarily for elevated temperature applications requiring guaranteed fracture toughness and improved short transverse properties in plate gauges over 1.0 inches (25.40 mm) thick. This alloy also exhibits good strength retention and creep resistance at elevated temperatures up to 350° F (177°C). Fracture toughness levels of 2124 are substantially higher than 2024. Heat treatable. 2219 Aluminum SheetControlled availability. Welded structures at high temperature (up to 600F). 2219 is an age-hardenable copper containing alloy of aluminum. It is noted for applications at elevated temperatures. Heat treatable. Typical Chemical Analysis
Machinability Forming The alloy may be readily formed by conventional methods. However there are precautions in regard to hot forming - see "Hot Working". Welding Heat Treatment Forging Hot Working Cold Working Annealing Solution Aging Tempering Hardening Other Physical Properties Applications 3003 Aluminum SheetApprox. 20% higher strength than the 1100 series, but retaining an excellent workability rating. May show some slight discoloration when anodized, but reacts well to mechanical and organic finishings. 3003 is easily welded and brazed, but solder is limited to the torch method. Like 1100, tends to be "gummy" when machined. Non-heat treatable. Typical applications include food and chemical equipment, appliance components, truck and trailer roofing, heat exchangers, and lawn furniture components.
3004 Aluminum SheetApproaching 5052 in strength because of the magnesium addition, this alloy sacrifices formability in tempers other than annealed. Although it has excellent corrosion resistance in many applications, it will generally be clad for use in marine, industrial, or roofing and siding applications. Machinability is poor, but rates high in weldability. Non-heat treatable. Typical applications include storage tanks, pressure vessels, lamp bases, and truck/trailer parts.
3005 Aluminum SheetControlled availability. Similar to 3105 series.
3104 Aluminum SheetControlled availability. Similar to 3004 series.
3105 Aluminum SheetNear 3003 in strength, this alloy has excellent corrosion resistance and finishes well although, if anodized, would not be chosen if aesthetics is a factor. Adapts to welding only in the hot joining processes and is not recommended for drawing or complex forming operations. Non-heat treatable. Typical applications include gutters, downspouts, truck and trailer roofing, vent pipes, and solar panels.
5005 Aluminum SheetComparable to 3003 in strength and close to it in formability, but his alloy has superior finishing characteristics making much better for anodizing. Excellent corrosion resistance and weldability, but would rate somewhat low below 1100 and 3003 for brazing and soldering, and it is not the alloy on would choose for machinability. Non-heat treatable. Typical applications include decorative trim, utensils, mobile home siding, and reflectors.
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| Chromium (CR) | 0.15-0.35% |
| Copper (Cu) | 0.1% max |
| Magnesium (Mg) | 2.2-2.8% |
| Manganese (Ms) | 0.1% max |
| Silicon (Si) & Iron (Fe) | 0.45% max |
| Zinc (Zn) | 0.1 max |
5056 Aluminum Sheet
Controlled availability. Medium strength commercial alloy. Non-heat treatable.
5083 Aluminum Sheet
With excellent corrosion resistance and weldability, together with high strength, this alloy was designed for welded structures requiring maximum joint strength and efficiency. Can be anodized for increased corrosion resistance, but does not lend itself to decorative applications. Not meant to be a machining alloy, but can be machined fairly well with proper preparations. Because of its relatively high magnesium content, the workability rating would only be fair. Non-heat treatable. Typical applications include large marine craft, containers, railroad cars, structurals and elevator cars.
5086 Aluminum Sheet
Sister alloy to 5083 with comparable characteristics but slightly less strength. Non-heat treatable.
5182 Aluminum Sheet
Controlled availability. Non-heat treatable. Typical applications include beverage can lids and automotive applications.
5454 Aluminum Sheet
Excellent corrosion resistance and, unlike the other magnesium alloys, it maintains that rating when functioning in the 150-300 degrees F range where the others would be prone to stress corrosion. Not a decorative alloy but well adapted to the applied finishing processes. High strength, excellent weldability, fair formability, and poor machinability. Non-heat treatable. Typical applications include dump bodies, exhaust stacks, marine components, and chemical handling vessels.
5456 Aluminum Sheet
Highest in strength of the commercially available non-heat treatable alloys with excellent corrosion resistance. Only fair workability and machinability, but excellent weldability. Not recommended for brazing or soldering. Non-heat treatable. Typical applications include high strength welded structures, marine components, pressure vessels, and storage tanks.
6013 Aluminum Sheet
6013 is a new medium strength aerospace alloy that provides improved corrosion resistance and formability for use in aerospace applications including primary aircraft structures. Alloy 6013 is an aluminum-magnesium-silicon-copper alloy that has yield strengths 12% higher than alclad 2024-T3 and is virtually immune to exfoliation and stress corrosion cracking. Industry use has demonstrated that 6013 in the T4 condition has better stretch forming characteristics than other aerospace aluminum alloys. Parts can be formed in the T4 condition and aged to the T6 condition without costly heat-treating or annealing operations. Heat treatable.
Applications
Uses for 6013 include primary structural applications including fuselage panels, leading and trailing edges and engine cowlings. Lockheed has chosen 6013-T6 for the fuselage of the Navy's P-7A aircraft. Canadair has specified 6013-T6 for the leading edges of the Regional Jet.
Questair has been producing the Questair kit aircraft since 1986 entirely from 6013. Major jet aircraft builders are considering 6013 for applications on large commercial aircraft.
Alloy 6013 is receiving consideration in most new programs taking advantage of the improved formability, lower density and corrosion resistance.
6061 Aluminum Sheet
This is the most versatile of the heat treatable aluminum alloys. It has most of the good qualities of aluminum, and it offers a wide range of mechanical properties and corrosion resistance. It can be fabricated by many of the commonly used techniques. In the annealed condition, it has good formability. In the T4 condition, fairly severe forming operations may be accomplished. The T6 properties may be obtained by artificial aging. It is welded by all methods and can be furnace brazed. Heat treatable.
- American Specifications: ASTM B209, AMS 4025, AMS 4026, AMS 4027, MIL-F-17132, QQ-A-250/11
- British Specifications: H20, HE 20
- Applications: This grade is used for a wide variety of products and applications from truck bodies and frames to screw machine parts and structural components. Alclad 6061 is used where appearance and better corrosion resistance with good strength are required.
- Size Range: .016" - .190" (.4 mm - 5 mm)
- Min 90 Cold-Bend: 0 1/2-11/2T 1-2T Ñ Ñ Ñ
- Weldability: Yes
Typical Chemical Analysis
| Cu | .15-.40% |
| Si | .4-.8% |
| Fe | 2.2-2.8% |
| Mn | 0.1% max |
| Mg | 0.45% max |
| Zn | 0.1 max |
| Cr | .04-.35 |
| Ti | .15 max |
7050 Aluminum Sheet
Alloy 7050 is the premier choice for aerospace applications requiring the best combination of strength, stress corrosion cracking (SCC) resistance and toughness. It is particularly suited for plate applications in the 3 to 6 inch (76.20 to 152.40mm) thickness range. Alloy 7050 exhibits better toughness/corrosion resistance characteristics than alloy 7075. Because it is less quench sensitive than most aerospace aluminum alloys, 7050 retains its strength properties in thicker sections while maintaining good stress corrosion cracking resistance and fracture toughness levels. Heat treatable
Alloy 7050 plate is available in two tempers: T7651 combines the highest strength with good exfoliation corrosion resistance and average SCC resistance; and T7451 (formerly T73651) provides better SCC resistance and excellent exfoliation resistance at slightly lower strength levels.
Alloy 7050 sheet is available bare and Alclad in the T76 temper.
Applications
Typical applications for alloy 7050 plate include fuselage frames and bulkheads where section thicknesses are 2 to 6 inches (50.8 to 152.40mm). Typical applications for alloy 7050 sheet include wing skins. The major usage is in plate applications requiring thicknesses over 2 inches (50.8mm) where 7050 has superior properties.
7075 Aluminum Sheet
Alloy 7075 has been the standard workhorse 7XXX series alloy within the aerospace industry ever since. It was the first successful Al-Zn-Mg-Cu high strength alloy using the beneficial effects of the alloying addition of chromium to develop good stress-corrosion cracking resistance in sheet products. Although other 7XXX alloys have since been developed with improved specific properties, alloy 7075 remains the baseline with a good balance of properties required for aerospace applications. This heat treatable alloy is considered high in strength. Corrosion resistance and machinability is fair. Rated low on workability and welded only by the resistance process. Heat treatable.
Alloy 7075 is available in bare and alclad sheet and plate product forms in the annealed state as well as several tempers of the T6, T73 and T76 types.
Applications
Alloy 7075 sheet and plate products have application throughout aircraft and aerospace structures where a combination of high strength with moderate toughness and corrosion resistance are required.
Typical applications are alclad skin sheet, structural plate components up to 4 inches in thickness and general aluminum aerospace applications.
7150 Aluminum Sheet
Alloy 7150 is the highest strength aluminum plate alloy/temper currently available for commercial aircraft applications. A controlled toughness alloy with guaranteed levels of fracture toughness, this alloy is a potential replacement for 7075-T651 since it provides 6 to 10 ksi (41.4 to 68.9 MPa) higher strength levels. Alloy 7150 is a second-generation version of alloy 7050, developed specifically for peak strength properties in 0.75 to 1.5 inch (19.1 to 38.1mm) thick plate. Heat treatable.
Alloy 7150-T6151 is recommended for applications, which can take advantage of its high tensile/ compressive properties where exfoliation and stress corrosion cracking (SCC) requirements are similar to 7075-T651.
Applications
Alloy 7150 is currently being used for upper wing skins on large commercial aircraft where high compressive yield strength is the major requirement.
This heat treatable alloy is considered the highest in strength. Corrosion resistance and machinability is fair. Rated low on workability and welded only by the resistance process.
7475 Aluminum Sheet
Alloy 7475 is a controlled toughness alloy developed by Alcoa for sheet and plate applications that require a combination of high strength, superior fracture toughness and resistance to fatigue crack propagation. Typical fracture toughness values for alloy 7475 plate are approximately 40 percent greater than alloy 7075 in the same tempers. Corrosion resistance and fatigue behavior of alloy 7475 are equal to and, in some cases, better than many of the current high strength aerospace alloys such as 7075, 7050 and 2024. Heat treatable.
Alloy 7475 sheet is available as bare and alclad in the T61 and T761 tempers. Plate is available in T651, T7651 and T7351 tempers. Alcoa guarantees a minimum fracture toughness level along with standard minimum tensile properties for alloy 7475 plate and sheet products in all available temper conditions except "0".
Applications
Alloy 7475 plate and sheet is currently being specified for fracture critical components of high performance aircraft...applications where high fracture toughness is a major design consideration. It should be considered for fuselage skins, wing skins, wing spars and fuselage bulkheads.
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