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Aluminum alloy 7075 is renowned for its exceptional strength-to-weight ratio, making it one of the highest-strength aluminum alloys available. Composed mainly of aluminum, with minor additions of zinc, copper, and magnesium, this alloy offers outstanding mechanical properties and high resistance to corrosion. It finds extensive use in aerospace, military, and high-performance applications, including aircraft structures, missile components, and high-stress machinery parts. Despite its remarkable strength, 7075 Aluminum Alloy can be challenging to weld but offers excellent machinability. Its combination of strength, lightweight nature, and durability makes it a top choice for critical applications where reliability and performance are crucial.

Characteristics

Very high strength, good machinability, poor workability, fair corrosion resistance

Typical Uses

Aircraft structures, ordinance, blow molds, injection molds

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Product Properties

Chemical

This table contains the chemical composition limits of wrought aluminum alloys in percent by weight maximum unless shown as a range or minimum. Except for “aluminum” and “others, ” analysis normally is made for elements for which specific limits are shown. For purposes of determining conformance to these limits, an observed value or a calculated value obtained from analysis is rounded off to the nearest unit in the last right-hand place of figures used in expressing the specified limit, in accordance with ASTM Recommended Practice E29.

Cr
0.18 – 0.28
Cu
1.2 – 2.0
Fe
0.5
Mg
2.1 – 2.9
Mn
0.3
Si
0.4
Ti
0.2
Zn
5.1 – 6.1
Aluminum Min.⁽⁴⁾
Remainder
Others⁽¹⁾, Each⁽²⁾
0.05
Others⁽¹⁾, Total⁽³⁾
0.15

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(1) Includes listed elements for which no specific limit is shown.
(2) A .0008 weight percent maximum beryllium is applicable to any alloy to be used as welding electrode or welding rod.
(3) The sum of those “others” metallic elements 0.010 percent or more each, expressed to the second decimal before determining the sum.
(4) The aluminum content for unalloyed aluminum not made by a refining process is the difference between 100.00 percent and the sum of all other metallic elements present in amounts of 0.010 percent or more each, expressed to the second decimal before determining the sum.
(5) Beryllium 0.0008 maximum for welding electrode and welding rod only.
(6) Also contains 0.20 to 0.6 percent each of lead and bismuth.
(9) Boron 0.06 percent maximum.
(10) Also contains 0.40 to 0.7 percent each of lead and bismuth.
(12) Also contains 0.08 to 0.15 percent of zirconium.

Mechanical

The following typical properties are not guaranteed since in most cases they are averages for various sizes, product forms, and methods of manufacture and may not be exactly representative of any particular product or size. These data are intended only as a basis for comparing alloys and tempers and should not be specified as engineering requirements or used for design purposes. The indicated typical mechanical properties for all except 0 temper material are higher than the specified minimum properties. For 0 temper products, typical ultimate and yield values are slightly lower than specified (maximum) values.

Alloy Attribute
Alclad
Alclad
-
-
Temper
Treatable
Tensile Strength (ksi), Ultimate
Tensile Strength (ksi), Yield
Elongation % of 2 in., 1/16 in. Thick
Elongation % of 2 in., 1/2 in. Thick
Brinell Hardness 500 kg Load 10 mm Ball
Ultimate Shearing Strength (ksi)
Fatigue Endurance⁽¹⁾ Limit (ksi)
Modulus⁽²⁾ of Elasticity (ksi x 10³)
0
Heat Treatable
32
14
17
-
-
22
-
10.4
T6, T651
Heat Treatable
76
67
11
46
-
10.4
T6, T651
Heat Treatable
83
73
11
11
150
48
23
10.4
0
Heat Treatable
33
15
17
16
60
22
-
10.4

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(1) Based on 500,000,000 cycles of completely reversed stress using the R.R. Moore type of machine and specimen.
(2) Average of tension and compression moduli. Compression modulus is about 2% greater than tension modulus.

Physical

The following typical properties are not guaranteed since in most cases they are averages for various sizes, product forms, and methods of manufacture and may not be exactly representative of any particular product or size. These data are intended only as a basis for comparing alloys and tempers and should not be specified as engineering requirements or used for design purposes.

Treatable
Heat Treatable
Density lb/In³
Average⁽¹⁾ Coefficient of Thermal Expansion 68 to 212°F x 10⁻⁶ per °F
Melting Range⁽²,³⁾ Approximate °F
Temper
Thermal Conductivity at 77°F Btu/Ft/Ft²/Hr/°F
Electrical Conductivity at 68°F Percent of International Annealed Copper Standard, Equal Volume
Electrical Conductivity at 68°F Percent of International Annealed Copper Standard, Equal Weight
Electrical Resistivity at 68°F Ohms-Cir Mil/Ft
0.101
13.1
890 – 1175⁽⁶⁾
T6
75
33
105
31

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Fabrication

Alloy Attribute
-
-
Plate
Plate
Plate
Plate
Plate
-
Temper
Treatable
General Resistance to Corrosion⁽¹⁾
Stress Corrosion Cracking ⁽²⁾
Workability (Cold) ⁽⁴⁾
Machinability ⁽⁴⁾
Brazeability⁽⁵⁾
Weldability ⁽⁵⁾: Gas
Weldability ⁽⁵⁾: Arc
Weldability ⁽⁵⁾: Resistance: Spot Seam
Description
Thickness (in)
UTS (ksi)
YTS (ksi)
Elongation (%)
Surface Hardness (Hb)
Thermal Conductivity (Btu/ft/hr/ft²/°F)
Specific Heat, 70°F (Btu/Lb)
Poission's Ratio
Plate General Resistance to Corrosion
Exfoliation
Plate Stress Corrosion Cracking
Weldability
Plate Machinability
Polishability
Avg. Coefficient of Thermal Expansion(x10⁻⁶/in/in/°F,68 - 212°F)
Modulus of Elasticity (x10⁶ lb/in²)
Density (lb/in ³)
0
Heat Treatable
–
–
–
D
D
D
D
B
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
T6, T651, T652, T6510, T6511
Heat Treated
C⁽³⁾
C
D
B
D
D
D
B
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
T651
Heat Treated
C
C
-
B
-
D
D
-
High Strength Wrought Aluminum
1
83
75
13
150
75
0.229
0.33
C
C
C
D
B 70%
Very Good
13.1
10.4
0.101
T651
Heat Treated
C
C
-
B
-
D
D
-
High Strength Wrought Aluminum
4
75
63
11
150
75
0.229
0.33
C
C
C
D
B 70%
Very Good
13.1
10.4
0.101
T651
Heat Treated
C
C
-
B
-
D
D
-
High Strength Wrought Aluminum
8
57
39
14
150
75
0.229
0.33
C
C
C
D
B 70%
Very Good
13.1
10.4
0.101
T651
Heat Treated
C
C
-
B
-
D
D
-
High Strength Wrought Aluminum
10
52
32
14
150
75
0.229
0.33
C
C
C
D
B 70%
Very Good
13.1
10.4
0.101
T651
Heat Treated
C
C
-
B
-
D
D
-
High Strength Wrought Aluminum
6
67
53
11
150
75
0.229
0.33
C
C
C
D
B 70%
Very Good
13.1
10.4
0.101
T73, T7351
Heat Treated
C
B
D
B
D
D
D
B
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-

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  1. Ratings A through E are relative ratings in decreasing order of merit, based on exposures to sodium chloride solution by intermittent spraying or immersion. Alloys with A and B ratings can be used in industrial and seacoast atmospheres without protection. Alloys with C, D, and E ratings generally should be protected at least on faying surfaces
  2. Stress corrosion cracking ratings are based on service experience and on laboratory tests of specimens exposed to the 3.5% sodium chloride alternate immersion test and are expressed as follows:
    • A = No known instance of failure in service or in laboratory tests.
    • B = No known instance of failure in service; limited failures in laboratory tests of short transverse specimens.
    • C = Service failures with sustained tension stress acting in short transverse direction relative to grain structure; limited failures in laboratory tests of long transverse specimens.
    • D = limited service failures with sustained longitudinal or long transverse stress.
  3. This rating may be different for material held at elevated temperature for long periods
  4. Ratings A through D for Workability (cold), and A through E for Machinability, are relative ratings in decreasing order of merit.
  5. Ratings A through D for Weldability and Brazeability are relative ratings defined as follows:
    • A = Generally weldable by all commercial procedures and methods.
    • B = Weldable with special techniques or for specific applications which justify preliminary trials or testing to develop welding procedure and weld performance.
    • C = Limited Weldability because of crack sensitivity or loss in resistance to corrosion and mechanical properties.
    • D = No commonly used welding methods have been developed.

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