MIL-HDBK-5: Chapter 3.7 — 7000 Series Wrought Alloys
Chapter 3.7 Contents
3.77000 Series Wrought Alloys 3.7.17010 Alloy 3.7.1.0Comments and Properties 3.7.1.1T7451 Temper 3.7.1.2T7651 Temper 3.7.27040 Alloy 3.7.2.0Comments and Properties 3.7.37049/7149 Alloy 3.7.3.0Comments and Properties 3.7.3.1T73 and T73511 Tempers 3.7.47050 Alloy 3.7.4.0Comments and Properties 3.7.4.1T73510 and T73511 Tempers 3.7.4.2T74, T7451, T7452 Tempers 3.7.4.3T76510 and T76511 Tempers 3.7.57055 Alloy 3.7.5.0Comments and Properties 3.7.67075 Alloy 3.7.6.0Comments and Properties 3.7.6.1T6, T651, T652, T6510, T6511 Tempers 3.7.6.2T73, T7351, T7352, T73510, T73511 Tempers 3.7.77150 Alloy 3.7.87175 Alloy 3.7.8.0Comments and Properties 3.7.8.1T73511 Temper 3.7.8.2T74 and T7452 Tempers 3.7.97249 Alloy 3.7.9.0Comments and Properties 3.7.9.1T7452 Temper 3.7.107475 Alloy 3.7.10.0Comments and Properties 3.7.10.1T61 and T651 Tempers 3.7.10.2T7351 Temper 3.7.10.3T761 and T7651 Tempers
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Chapter 1 — General Chapter 2 — Steel Chapter 3 — Aluminum 3.1 — General 3.2 — 2000 Series Wrought Alloys 3.5 — 5000 Series Wrought Alloys 3.6 — 6000 Series Wrought Alloys 3.7 — 7000 Series Wrought Alloys 3.8 — 200.0 Series Cast Alloys 3.9 — 300.0 Series Cast Alloys 3.10 — Element Properties Chapter 4 — Magnesium
Disclaimer

For reference use only. The formulas, graphs, and values herein are provided in good faith for general engineering guidance. Please verify all data against MIL-HDBK-5J or the applicable superseding document (MMPDS).

Figures and Tables
Table of Tables
Table of Figures
Fig 3.7.1.1.1Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of 7010-T7451 aluminum alloy plate. Fig 3.7.1.1.6(a)Typical tensile stress-strain curves for 7010-T7451 plate at room temperature (thickness 2.001–5.500 in.). Fig 3.7.1.1.6(b)Typical compressive stress-strain and compressive tangent-modulus curves for 7010-T7451 plate at room temperature (thickness 2.001–5.500 in.). Fig 3.7.1.1.6(c)Typical tensile stress-strain curves for 7010-T7451 aluminum alloy plate at room temperature (thickness 0.500–1.500 in.). Fig 3.7.1.1.6(d)Typical compressive stress-strain and compressive tangent-modulus curves for 7010-T7451 aluminum alloy plate at room temperature (thickness 0.500–1.500 in.). Fig 3.7.1.2.6(a)Typical tensile stress-strain curves for 7010-T7651 plate at room temperature (thickness 2.001–5.500 in.). Fig 3.7.1.2.6(b)Typical compressive stress-strain and compressive tangent-modulus curves for 7010-T7651 plate at room temperature (thickness 2.001–5.500 in.). Fig 3.7.1.2.6(c)Typical tensile stress-strain curves for 7010-T7651 aluminum alloy plate at room temperature (thickness 0.500–1.500 in.). Fig 3.7.1.2.6(d)Typical compressive stress-strain and compressive tangent-modulus curves for 7010-T7651 aluminum alloy plate at room temperature (thickness 0.500–1.500 in.). Fig 3.7.2.0Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of 7040-T7451 aluminum alloy plate, T/4 location. Fig 3.7.3.1.1Effect of temperature on the tensile ultimate strength (Ftu), the tensile yield strength (Fty), and the compressive yield strength (Fcy) of 7049-T7351 plate, 7049/7149-T73 hand forging, and 7049/7149-T73511 extrusion. Fig 3.7.3.1.6(a)Typical tensile stress-strain curves for 7049/7149-T73 aluminum alloy die forging at room temperature. Fig 3.7.3.1.6(b)Typical compressive stress-strain and compressive tangent-modulus curves for 7049/7149-T73 aluminum alloy die forging at room temperature. Fig 3.7.3.1.6(c)Typical tensile stress-strain curves for 7049/7149-T73 aluminum alloy hand forging at room temperature. Fig 3.7.3.1.6(d)Typical compressive stress-strain and compressive tangent-modulus curves for 7049/7149-T73 aluminum alloy hand forging at room temperature. Fig 3.7.3.1.6(e)Typical tensile stress-strain curves for 7049-T7351 aluminum alloy plate at room temperature. Fig 3.7.3.1.6(f)Typical compressive stress-strain and compressive tangent-modulus curves for 7049-T7351 aluminum alloy plate at room temperature. Fig 3.7.3.1.6(g)Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7049/7149-T73511 extrusion at room temperature. Fig 3.7.3.1.8(a)Best-fit S/N curves for unnotched 7049-T73 die and hand forgings, at room temperature, longitudinal and long-transverse directions. Fig 3.7.3.1.8(b)Best-fit curves for unnotched 7049-T73 die forging, at room temperature, short-transverse direction. Fig 3.7.3.1.8(c)Best-fit S/N curves for notched, Kt = 2.4, 7049-T73 die forging, at room temperature, longitudinal, long-transverse, and short-transverse directions. Fig 3.7.3.1.8(d)Best-fit S/N curves for unnotched 7049-T73 hand forging, longitudinal direction. Fig 3.7.3.1.8(e)Best-fit S/N curves for unnotched 7149-T73 hand forging, long-transverse direction. Fig 3.7.3.1.8(f)Best-fit S/N curves for notched, Kt = 3.0, 7049-T73 hand forging, longitudinal, long-transverse, and short-transverse directions. Fig 3.7.3.1.8(g)Best-fit S/N curves for notched, Kt = 3.0, 7149-T73 hand forging, long-transverse direction. Fig 3.7.4.1.6(a)Typical tensile stress-strain curves for 7050-T7351X aluminum alloy extrusion at room temperature. Thickness ≤ 1.999 in. Fig 3.7.4.1.6(b)Typical tensile stress-strain curves for 7050-T7351X aluminum alloy extrusion at room temperature. Thickness = 2.000–5.000 in. Fig 3.7.4.1.6(c)Typical compressive stress-strain and tangent-modulus curves for 7050-T7351X aluminum alloy extrusion at room temperature. Thickness ≤ 1.999 in. Fig 3.7.4.1.6(d)Typical compressive stress-strain and tangent-modulus curves for 7050-T7351X aluminum alloy extrusion at room temperature. Thickness = 2.000–5.000 in. Fig 3.7.4.1.8(a)Best-fit S/N curves for unnotched 7050-T7351X extruded shape, longitudinal and long-transverse directions. Fig 3.7.4.1.8(b)Best-fit S/N curves for notched, Kt = 3.0, 7050-T7351X extruded shape, longitudinal and long-transverse directions. Fig 3.7.4.2.1Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of 7050-T7451 aluminum alloy plate. Fig 3.7.4.2.6(a)Typical tensile stress-strain curves for 7050-T7451 aluminum alloy plate at room temperature. Thickness = 0.500–4.000 in. Fig 3.7.4.2.6(b)Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7451 aluminum alloy plate at room temperature. Thickness = 0.500–4.000 in. Fig 3.7.4.2.6(c)Typical tensile stress-strain curves for 7050-T7452 aluminum alloy hand forging at room temperature. Thickness ≤ 7.000 in. Fig 3.7.4.2.6(d)Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7452 aluminum alloy hand forging at room temperature. Thickness ≤ 7.000 in. Fig 3.7.4.2.6(e)Typical tensile stress-strain curves for 7050-T74 aluminum alloy die forging at room temperature. Thickness ≤ 3.000 in. Fig 3.7.4.2.6(f)Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T74 aluminum alloy die forging at room temperature. Thickness ≤ 3.000 in. Fig 3.7.4.2.6(g)Typical tensile stress-strain curves for 7050-T74511 aluminum alloy extrusion at room temperature. Thickness ≤ 1.750 in. Fig 3.7.4.2.6(h)Typical compressive stress-strain and tangent-modulus curves for 7050-T74511 aluminum alloy extrusion at room temperature. Thickness ≤ 1.750 in. Fig 3.7.4.2.6(i)Typical tensile stress-strain curves for 7050-T7452 aluminum alloy die forging at room temperature. Thickness ≤ 6.000 in. Fig 3.7.4.2.6(j)Typical compressive stress-strain and tangent-modulus curves for 7050-T7452 aluminum alloy die forging at room temperature. Thickness ≤ 6.000 in. Fig 3.7.4.2.8(a)Best-fit S/N curves for unnotched 7050-T7451 plate, longitudinal direction and T/2 specimen location. Fig 3.7.4.2.8(b)Best-fit S/N curves for unnotched 7050-T7451 plate, long-transverse direction, t/4 specimen location. Fig 3.7.4.2.8(c)Best-fit S/N curves for unnotched 7050-T7451 plate, long-transverse direction, t/2 specimen location. Fig 3.7.4.2.8(d)Best-fit strain-life curves, cyclic stress-strain curve, and mean-stress-relaxation curve for 7050-T7451 plate, long-transverse direction, t/4 specimen location. Fig 3.7.4.2.8(e)Best-fit S/N curves for unnotched 7050-T7451 plate, long-transverse direction, t/4 specimen location. Fig 3.7.4.2.8(f)Best-fit S/N curves for notched, Kt = 3.0, 7050-T7451 plate, longitudinal and long-transverse directions, t/4 specimen location. Fig 3.7.4.2.8(g)Best-fit S/N curves for notched, Kt = 2.6, 7050-T7451X extruded shape, longitudinal direction. Fig 3.7.4.2.8(h)Best-fit S/N curves for unnotched 7050-T7452 hand forgings, longitudinal direction. Fig 3.7.4.2.8(i)Best-fit S/N curves for unnotched 7050-T7452 hand forgings, long-transverse and short-transverse directions. Fig 3.7.4.2.8(j)Best-fit S/N curves for notched, Kt = 3.0, 7050-T7452 hand forgings, longitudinal, long-transverse, and short-transverse directions. Fig 3.7.4.2.8(k)Best-fit S/N curves for unnotched 7050-T74 die forging, longitudinal direction. Fig 3.7.4.2.8(l)Best-fit S/N curves for notched, Kt = 3.0, 7050-T74 die forging, longitudinal direction. Fig 3.7.4.2.9(a)Fatigue-crack-propagation data for 3.15-inch-thick 7050-T7451 aluminum plate. Fig 3.7.4.2.9(b)Fatigue-crack-propagation data for 1- and 6-inch-thick 7050-T7451 aluminum plate, dry air. Fig 3.7.4.2.9(c)Fatigue-crack-propagation data for 1- and 6-inch-thick 7050-T7451 aluminum plate, humid air. Fig 3.7.4.3.6(a)Typical tensile stress-strain curves for 7050-T7651X aluminum alloy extrusion at room temperature. Thickness < 1.999 in. Fig 3.7.4.3.6(b)Typical tensile stress-strain curves for 7050-T7651X aluminum alloy extrusion at room temperature. Thickness = 2.000–5.000 in. Fig 3.7.4.3.6(c)Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7651X aluminum alloy extrusion at room temperature. Thickness < 1.999 in. Fig 3.7.4.3.6(d)Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7651X aluminum alloy extrusion at room temperature. Thickness = 2.000–5.000 in. Fig 3.7.4.3.6(e)Typical tensile stress-strain curves for 7050-T7651 aluminum alloy plate at room temperature. Thickness ≤ 2.000 in. Fig 3.7.4.3.6(f)Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7651 aluminum alloy plate at room temperature. Thickness ≤ 2.000 in. Fig 3.7.4.3.8(a)Best-fit S/N curves for unnotched 7050-T7651X extruded shape, longitudinal and long-transverse directions. Fig 3.7.4.3.8(b)Best-fit S/N curves for notched, Kt = 3.0, 7050-T7651X extruded shape, longitudinal and long-transverse directions. Fig 3.7.6.0Effect of temperature on the physical properties of 7075 aluminum alloy. Fig 3.7.6.1.1(a)Effect of temperature on the tensile ultimate strength (Ftu) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products). Instructions for use of these curves are presented in Section 3.7.6.1. Fig 3.7.6.1.1(b)Effect of temperature on the tensile yield strength (Fty) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products). Instructions for use of these curves are presented in Section 3.7.6.1. Fig 3.7.6.1.1(c)Effect of temperature on the tensile ultimate strength (Ftu) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products). Fig 3.7.6.1.1(d)Effect of temperature on the tensile yield strength (Fty) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products). Fig 3.7.6.1.2(a)Effect of temperature on the compressive yield strength (Fcy) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products). Fig 3.7.6.1.2(b)Effect of temperature on the shear ultimate strength (Fsu) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products). Fig 3.7.6.1.3(a)Effect of temperature on the bearing ultimate strength (Fbru) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products). Fig 3.7.6.1.3(b)Effect of temperature on the bearing yield strength (Fbry) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).
Table of Figures (cont.)
Fig 3.7.6.1.4Effect of temperature on the tensile and compressive moduli (E and Ec) of 7075 aluminum alloy. Fig 3.7.6.1.5(a)Effect of temperature on the elongation of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products except thick extrusions). Fig 3.7.6.1.5(b)Effect of exposure at elevated temperatures on the elongation of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products except thick extrusions). Fig 3.7.6.1.8(a)Best-fit S/N curves for unnotched 7075-T6 aluminum alloy, various product forms, longitudinal direction. Fig 3.7.6.1.8(b)Best-fit S/N curve for notched, Kt = 1.6, 7075-T6 aluminum alloy rolled bar, longitudinal direction. Fig 3.7.6.1.8(c)Best-fit S/N curves for notched, Kt = 3.4, 7075-T6 aluminum alloy rolled bar, longitudinal direction. Fig 3.7.6.1.8(d)Best-fit S/N curves for unnotched 7075-T6 aluminum alloy sheet, longitudinal direction. Fig 3.7.6.1.8(e)Best-fit S/N curves for notched, Kt = 1.5, 7075-T6 aluminum alloy sheet, longitudinal direction. Fig 3.7.6.1.8(f)Best-fit S/N curves for notched, Kt = 2.0, 7075-T6 aluminum alloy sheet, longitudinal direction. Fig 3.7.6.1.8(g)Best-fit S/N curves for notched, Kt = 4.0, 7075-T6 aluminum alloy sheet, longitudinal direction. Fig 3.7.6.1.8(h)Best-fit S/N curves for notched, Kt = 5.0, 7075-T6 aluminum alloy sheet, longitudinal direction. Fig 3.7.6.1.9Fatigue-crack-propagation data for 0.090-inch-thick 7075-T6 aluminum alloy sheet with buckling restraint. Fig 3.7.6.1.10(a)Residual-strength behavior of 0.063-inch-thick 7075-T6 aluminum alloy sheet at room temperature. Crack orientation is T-L. Fig 3.7.6.1.10(b)Residual-strength behavior of 0.063-inch-thick 7075-T6 aluminum alloy sheet at room temperature. Crack orientation is T-L. Fig 3.7.6.1.10(c)Residual-strength behavior of 0.090- and 0.100-inch-thick 7075-T6 aluminum alloy sheet at room temperature. Crack orientation is L-T. Fig 3.7.6.1.10(d)Residual-strength behavior of 0.100-inch-thick 7075-T6 aluminum alloy sheet at room temperature. Crack orientation is L-T. Fig 3.7.6.1.10(e)Residual-strength behavior of 0.313-inch-thick 7075-T6 aluminum alloy plate at room temperature. Crack orientation is L-T. Fig 3.7.6.1.10(f)Residual-strength behavior of 0.040-inch-thick 7075-T6 clad aluminum alloy sheet at room temperature. Crack orientation is L-T. Fig 3.7.6.1.10(g)Residual-strength behavior of 0.080-inch-thick 7075-T6 clad aluminum alloy sheet at room temperature. Crack orientation is L-T. Fig 3.7.6.1.10(h)Residual-strength behavior of 0.090-inch-thick 7075-T6 clad aluminum alloy sheet at room temperature. Crack orientation is L-T. Fig 3.7.6.2.6(a)Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7075-T73 aluminum alloy extrusion at room temperature. Thickness = 0.250–1.499 in. Fig 3.7.6.2.6(b)Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7075-T7351X aluminum alloy extrusion at room temperature. Thickness = 0.500–0.749 in. Fig 3.7.6.2.6(c)Typical tensile stress-strain curves for 7075-T7352 aluminum alloy hand forging at room temperature. Thickness = 3.001–5.000 in. Fig 3.7.6.2.6(d)Typical compressive stress-strain and compressive tangent-modulus curves for 7075-T7352 aluminum alloy hand forging at room temperature. Thickness = 3.001–5.000 in. Fig 3.7.6.2.6(e)Typical tensile stress-strain curves (full range) for 7075-T7351X aluminum alloy extrusion at room temperature. Thickness = 0.500–0.749 in. Fig 3.7.6.2.6(f)Typical tensile stress-strain curves (full range) for 7075-T73 aluminum alloy extrusion at room temperature. Fig 3.7.6.2.9(a)Fatigue-crack-propagation data for 0.250-inch-thick 7075-T7351 aluminum alloy plate with buckling restraint. Fig 3.7.6.2.9(b)Fatigue-crack-propagation data for 0.500-inch-thick 7075-T7351 aluminum alloy plate with buckling restraint. Fig 3.7.6.2.9(c)Fatigue-crack-propagation data for 1.00-inch-thick 7075-T7351 aluminum alloy plate without buckling restraint. Fig 3.7.6.2.10(a)Residual-strength behavior of 0.600-inch-thick 7075-T7351 aluminum alloy plate at room temperature. Crack orientation is L-T. Fig 3.7.6.2.10(b)Residual-strength behavior of 1.00-inch-thick 7075-T7351 aluminum alloy plate at room temperature. Crack orientation is L-T. Fig 3.7.7.1.6(a)Typical tensile stress-strain curves for 7150-T6151 aluminum alloy plate at room temperature (thickness 0.750–1.000 in.). Fig 3.7.7.1.6(b)Typical compressive stress-strain and compressive tangent-modulus curves for 7150-T6151 aluminum alloy plate at room temperature (thickness 0.750–1.000 in.). Fig 3.7.7.1.6(c)Typical tensile stress-strain curves for 7150-T61511 aluminum alloy extrusion at room temperature (thickness 0.800–2.750 in.). Fig 3.7.7.1.6(d)Typical compressive stress-strain and compressive tangent-modulus curves for 7150-T61511 aluminum alloy extrusion at room temperature (thickness 0.800–2.750 in.). Fig 3.7.7.2.6(a)Typical tensile stress-strain curves for 7150-T7751 aluminum alloy plate at room temperature (thickness 0.340–1.875 in.). Fig 3.7.7.2.6(b)Typical compressive stress-strain and tangent-modulus curves for 7150-T7751 aluminum alloy plate at room temperature (thickness 0.340–1.875 in.). Fig 3.7.7.2.6(c)Typical tensile stress-strain curves for 7150-T77511 aluminum alloy extrusion at room temperature (thickness 0.700–1.145 in.). Fig 3.7.7.2.6(d)Typical compressive stress-strain and tangent-modulus curves for 7150-T77511 aluminum alloy extrusion (thickness 0.700–1.145 in.). Fig 3.7.7.2.8(a)Best-fit S/N curves for unnotched 7150-T77511 aluminum alloy extrusion, longitudinal orientation. Fig 3.7.7.2.8(b)Best-fit S/N curves for unnotched 7150-T77511 aluminum alloy extrusion, long transverse orientation. Fig 3.7.7.2.8(c)Best-fit S/N curves for notched, Kt = 3.0, 7150-T77511 aluminum alloy extrusion, longitudinal and long transverse orientations. Fig 3.7.8.1.6(a)Typical tensile stress-strain curves for aluminum alloy 7175-T73511 extrusion at room temperature. Fig 3.7.8.1.6(b)Typical compressive stress-strain and tangent-modulus curves for aluminum alloy 7175-T73511 extrusion at room temperature. Fig 3.7.8.1.8(a)Best-fit S/N curves for unnotched 7175-T73511 alloy extrusion, longitudinal direction. Fig 3.7.8.1.8(b)Best-fit S/N curves for notched, Kt = 3.0, 7175-T73511 alloy extrusion, longitudinal direction. Fig 3.7.8.1.8(c)Best-fit S/N curves for notched, Kt = 5.0, 7175-T73511 alloy extrusion, longitudinal direction. Fig 3.7.8.1.8(d)Best-fit S/N curves for notched, Kt = 7.0, 7175-T73511 alloy extrusion, longitudinal direction. Fig 3.7.8.2.6(a)Typical tensile stress-strain curves for 7175-T74 aluminum alloy die forging at room temperature. Fig 3.7.8.2.6(b)Typical compressive stress-strain and compressive tangent-modulus curves for 7175-T74 aluminum alloy die forging at room temperature. Fig 3.7.8.2.6(c)Typical tensile stress-strain curves for 7175-T74 aluminum alloy hand forging at room temperature. Fig 3.7.8.2.6(d)Typical compressive stress-strain and compressive tangent-modulus curves for 7175-T74 aluminum alloy hand forging at room temperature. Fig 3.7.8.2.6(e)Typical tensile stress-strain curves for aluminum alloy 7175-T7452 hand forging at room temperature. Fig 3.7.8.2.6(f)Typical compressive stress-strain and compressive tangent-modulus curves for aluminum alloy 7175-T7452 hand forging at room temperature. Fig 3.7.8.2.8(a)Best-fit S/N curves for notched, Kt = 3.0, 7175-T74 alloy die forging, longitudinal direction. Fig 3.7.8.2.8(b)Best-fit S/N curves for unnotched 7175-T74 alloy hand forging, longitudinal and transverse directions. Fig 3.7.9.1.6(a)Typical tensile stress-strain curves for 7249-T7452 aluminum alloy hand forging at room temperature. Fig 3.7.9.1.6(b)Typical compressive stress-strain and compressive tangent-modulus curves for 7249-T7452 aluminum alloy hand forging at room temperature. Fig 3.7.9.1.6(c)Typical tensile stress-strain curves (full range) for 7249-T7452 aluminum alloy hand forging at room temperature. Fig 3.7.10.1.6(a)Typical tensile stress-strain curves for 7475-T61 aluminum alloy sheet at room temperature. Fig 3.7.10.1.6(c)Typical tensile stress-strain curves for clad 7475-T61 aluminum alloy sheet at room temperature. Fig 3.7.10.1.6(e)Typical tensile stress-strain curves for 7475-T651 aluminum alloy plate at room temperature. Fig 3.7.10.1.8(a)Best-fit S/N curve for unnotched 7475-T61 and T761 sheet, thickness 0.125 inch, longitudinal and long transverse directions. Fig 3.7.10.1.8(b)Best-fit S/N curve for unnotched 7475-T61 and T761 sheet, thickness > 0.125 inch, longitudinal and long transverse directions. Fig 3.7.10.1.8(c)Best-fit S/N curve for notched, Kt = 3.0, 7475-T61 and T761 sheet, longitudinal and long transverse directions. Fig 3.7.10.2.6(a)Typical tensile stress-strain curves for 7475-T7351 aluminum alloy plate at room temperature. Fig 3.7.10.2.6(b)Typical compressive stress-strain and compressive tangent-modulus curves for 7475-T7351 aluminum alloy plate at room temperature. Fig 3.7.10.2.8(a)Best-fit S/N curves for unnotched 7475-T7351 plate, longitudinal and long transverse orientation. Fig 3.7.10.2.8(b)Best-fit S/N curves for notched, Kt = 3.0, 7475-T7351 and T7651 plate, longitudinal and long transverse direction. Fig 3.7.10.3.6(a)Typical tensile stress-strain curves for 7475-T761 aluminum alloy sheet at room temperature. Fig 3.7.10.3.6(i)Typical tensile stress-strain curves for 7475-T7651 aluminum alloy plate at room temperature. Fig 3.7.10.3.10(a)Residual strength behavior of 0.063-inch-thick 7475-T761 aluminum alloy sheet at room temperature. Crack orientation is L-T. Fig 3.7.10.3.10(b)Residual strength behavior of 0.063-inch-thick 7475-T761 aluminum alloy sheet at room temperature. Crack orientation is T-L.
3.77000 Series Wrought Alloys

The 7000 series of wrought alloys contain zinc as the principal alloying element and magnesium and copper as other major elements. They are available in a wide variety of product forms. They are strengthened principally by solution heat treatment and precipitation hardening and are among the highest-strength aluminum alloys.

The T6-type tempers of these alloys are susceptible to stress-corrosion cracking under certain conditions while the T7-type tempers are more resistant; these alloys should be considered in light of the corrosion resistance discussed in Sections 3.1.2.3 and 3.1.3.

3.7.17010 Alloy
3.7.1.0Comments and Properties

7010 is an Al-Zn-Mg-Cu-Zr alloy developed to have a combination of high strength, high resistance to stress-corrosion cracking, and good fracture toughness, particularly in thick sections. The use of zirconium in lieu of chromium provides a low sensitivity to quench, which results in high strength in thick sections. The alloy is available only in plate. Plate, greater than 2 inches in thickness in the T7451 temper, has static strength equal to or greater than 7075-T651 plate with greater toughness.

Plate in the T7451 temper has a stress-corrosion resistance higher than 7075-T7651. The T73-type temper provides the highest resistance to stress-corrosion for this alloy. The T76-type temper provides for good exfoliation resistance and higher stress-corrosion resistance than T6-type tempers of 7075 and 7178. The T74-type temper provides stress-corrosion and strength characteristics intermediate to those of T76 and T73. Refer to Section 3.1.2.3 for information regarding the resistance of the alloy to stress-corrosion cracking.

Refer to Section 3.1.3.4 for comments regarding the weldability of the alloy.

Material specifications for 7010 are shown in Table 3.7.1.0(a). Room-temperature mechanical properties are shown in Tables 3.7.1.0(b1) and (b2).

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Table 3.7.1.0(a). Material Specifications for 7010 Aluminum Alloy
SpecificationForm
AMS 4205Plate
AMS 4204Plate
Temper Index for 7010 Alloy
SectionTemper
3.7.1.1T7451
3.7.1.2T7651
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Table 3.7.1.0(b1). Design Mechanical and Physical Properties of 7010 Aluminum Alloy Plate
Specification AMS 4205
Form Plate
Temper T7451
Thickness, in. 0.250-1.0001.001-2.0002.001-3.0003.001-4.0004.001-5.0005.001-6.000
Basis SSABABABAB
Mechanical Properties:
Ftu, ksi:
L71717072707168a716870
LT72727172707269a7167a71
ST······6668666865a6763a67
Fty, ksi:
L626260626062596157a61
LT626260625961586057a60
ST······5557545653555254
Fcy, ksi:
L61615961586057595659
LT63636264616360625963
ST······6163606259615861
Fsu, ksi41414242424342434143
Fbrub, ksi:
(e/D = 1.5)10010110110210010310010397103
(e/D = 2.0)127129130132130134129133126133
Fbryb, ksi:
(e/D = 1.5)81828184818481848084
(e/D = 2.0)949797100981019810197102
e, percent (S-basis):
L999···9···9···8···
LT666···6···5···5···
ST······2.5···2···2···2···
E, 103 ksi10.2
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.21 (at 214°F)
K, Btu/[(hr)(ft2)(°F)/ft]95 (at 99°F)
α, 10-6 in./in./°F13.0 (68-212°F)
a S-basis values. The rounded T99 values are as follows: for 4.001-5.000-inch thickness, Ftu(L) = 69, Ftu(LT) = 70, and Ftu(ST) = 66; for 5.001-6.000-inch thickness, Ftu(LT) = 69, Ftu(ST) = 65, Fty(L) = 59, and Fty(LT) = 58.
b See Table 3.1.2.1.1. Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.1.0(b2). Design Mechanical Properties of 7010 Aluminum Alloy Plate—Continued
Specification AMS 4204
Form Plate
Temper T7651
Thickness, in. 0.250-1.0001.001-2.0002.001-2.5002.501-3.0003.001-4.0004.001-5.0005.001-5.500
Basis SSSSSSS
Mechanical Properties:
Ftu, ksi:
L76767573727271
LT76767574737272
ST······7170696866
Fty, ksi:
L66666564646362
LT66666564636261
ST······5958565553
Fcy, ksi:
L65656463626160
LT67686767666564
ST······6867656462
Fsu, ksi42444444444546
Fbrua, ksi:
(e/D = 1.5)105106106105105105105
(e/D = 2.0)135137137136135134134
Fbrya, ksi:
(e/D = 1.5)85868787868686
(e/D = 2.0)10310410310210110099
e, percent:
L8887776
LT6665554
ST······2.52.5222
E, 103 ksi10.2
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.21 (at 214°F)
K, Btu/[(hr)(ft2)(°F)/ft]95 (at 104°F)
α, 10-6 in./in./°F12.9 (68 to 212°F)
a See Table 3.1.2.1.1. Bearing values are “dry pin” values per Section 1.4.7.1.
3.7.1.1T7451 Temper

Elevated-temperature curves for plate are presented in Figure 3.7.1.1.1. Figures 3.7.1.1.6(a) through (d) present stress-strain and tangent-modulus curves for plate.

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Figure 3.7.1.1.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of 7010-T7451 aluminum alloy plate.

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Figure 3.7.1.1.6(a). Typical tensile stress-strain curves for 7010-T7451 plate at room temperature (thickness 2.001–5.500 in.).

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Figure 3.7.1.1.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7010-T7451 plate at room temperature (thickness 2.001–5.500 in.).

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Figure 3.7.1.1.6(c). Typical tensile stress-strain curves for 7010-T7451 aluminum alloy plate at room temperature (thickness 0.500–1.500 in.).

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Figure 3.7.1.1.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 7010-T7451 aluminum alloy plate at room temperature (thickness 0.500–1.500 in.).

3.7.1.2T7651 Temper

Figures 3.7.1.2.6(a) through (d) present stress-strain and tangent-modulus curves for plate.

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Figure 3.7.1.2.6(a). Typical tensile stress-strain curves for 7010-T7651 plate at room temperature (thickness 2.001–5.500 in.).

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Figure 3.7.1.2.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7010-T7651 plate at room temperature (thickness 2.001–5.500 in.).

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Figure 3.7.1.2.6(c). Typical tensile stress-strain curves for 7010-T7651 aluminum alloy plate at room temperature (thickness 0.500–1.500 in.).

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Figure 3.7.1.2.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 7010-T7651 aluminum alloy plate at room temperature (thickness 0.500–1.500 in.).

3.7.27040 Alloy
3.7.2.0Comments and Properties

7040 alloy is an Al-Mg-Zn-Cu-Zr alloy developed to provide a higher strength and toughness compromise than the currently available 7010 and 7050 alloys, particularly in heavy gauge plates up to 8.5 inch thickness. The use of a desaturated chemical composition in Mg and Cu together with a very close control of the Zr content and impurities provides 7040 with a much lower quench sensitivity than that of 7050, resulting in high strength and toughness properties in very thick sections.

7040-T7451 plates are particularly suited for structures in which high strength, high toughness, and good corrosion resistance are the major requirements. Parts such as integrally machined spars, ribs, and main fuselage frames can benefit from this outstanding property combination.

7040 is available in the form of plates, ranging in thickness from 3.0 to 8.5 inches.

Manufacturing Considerations — Due to tight control of residual stress level, the 7040 plates exhibit a superior dimensional stability, thus offering a cost-efficient alternative to rolled or forged parts, which require distortion corrections after machining. Refer to Section 3.1.3.4 for comments regarding the weldability of this alloy.

Specifications and Properties — Material specifications are shown in Table 3.7.2.0(a). Room-temperature properties are shown in Table 3.7.2.0(b1). Figure 3.7.2.0 shows the effect of temperature on tensile properties.

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Table 3.7.2.0(a). Material Specifications for 7040-T7451 Alloy Plate
SpecificationForm
AMS 4211Plate
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Table 3.7.2.0(b1). Design Mechanical and Physical Properties of 7040-T7451 Aluminum Alloy Plate
Specification AMS 4211
Form Plate
Temper T7451
Thickness, in. 3.001-4.0004.001-5.0005.001-6.0006.001-7.0007.001-8.0008.001-8.500
Basis ABABABABABAB
Mechanical Properties:
Ftu, ksi:
L7272717270a71697068b7068c70
LT72d7471e7370a72697068b696869
ST697068e706869666766676667
Fty, ksi:
L62d6562e6462a64626261626163
LT62d6562e6561a63606260615961
ST59d6158e6158a61575857585658
Fcy, ksi:
L606360625961586059605961
LT646764676366626462646163
ST636663666265616361636063
Fsu, ksi454744464445434443444344
Fbruf, ksi:
(e/D = 1.5)114117112115110114108110105108105106
(e/D = 2.0)145150143147140145137140134136133134
Fbryf, ksi:
(e/D = 1.5)939793979296909390928891
(e/D = 2.0)114119114119112117110113110113108112
e, percent (S-basis):
L9···9···8···7···6···6···
LT6···5···4···4···4···4···
ST3···3···3···3···3···3···
E, 103 ksi10.4
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23
K, Btu/[(hr)(ft2)(°F)/ft]91
α, 10-6 in./in./°F12.8
a S-basis values. Rounded T99 values are as follows: Ftu(L) = 71 ksi; Ftu(LT) = 71 ksi; Fty(L) = 63 ksi; Fty(LT) = 62 ksi; and Fty(ST) = 59 ksi.
b S-basis values. Rounded T99 values are as follows: Ftu(L) = 69 ksi; Ftu(LT) = 69 ksi.
c S-basis values. Rounded T99 values are as follows: Ftu(L) = 69 ksi.
d S-basis values. Rounded T99 values are as follows: Ftu(LT) = 73 ksi; Fty(L) = 64 ksi; Fty(LT) = 64 ksi; and Fty(ST) = 60 ksi.
e S-basis values. Rounded T99 values are as follows: Ftu(LT) = 72 ksi; Ftu(ST) = 69 ksi; Fty(L) = 63 ksi; and Fty(LT) = 63 ksi, Fty(ST) = 59 ksi.
f See Table 3.1.2.1.1. Bearing values are “dry pin” values per Section 1.4.7.1.
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Figure 3.7.2.0. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of 7040-T7451 aluminum alloy plate, T/4 location.

3.7.37049/7149 Alloy
3.7.3.0Comments and Properties

Alloy 7049/7149 is available in the form of die forging, hand forging, plate, and extrusion. Alloy 7149 contains lower residual iron and silicon content than 7049. The T73XX temper provides good static strength with high resistance to stress-corrosion cracking. The fatigue strength of the T73XX temper is about equal to that of 7075-T6, while the toughness is somewhat higher. Refer to Section 3.1.2.3 for comments regarding the resistance of the alloys to stress-corrosion cracking and to Section 3.1.3.4 for comments regarding the weldability of the alloys.

The properties of extrusions should be based upon the thickness at the time of quenching prior to machining. Selection of the mechanical properties based upon its final machined thickness may be unconservative; therefore, the thickness at the time of quenching to achieve properties is an important factor in the selection of the proper thickness column. For extrusions having sections with various thicknesses, consideration should be given to the properties as a function of thickness.

Material specifications for 7049/7149 aluminum alloy are presented in Table 3.7.3.0(a). Room-temperature mechanical and physical properties are shown in Tables 3.7.3.0(b) through (e).

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Table 3.7.3.0(a). Material Specifications for 7049/7149 Aluminum Alloy
SpecificationForm
AMS-QQ-A-367 (7049)Forging
AMS 4111 (7049)Forging
AMS 4320 (7149)Forging
AMS 4157 (7049)Extrusion
AMS-A-22771Forging
AMS 4200 (7049)Plate
AMS 4343 (7149)Extrusion

The temper index for 7049/7149 is: Section 3.7.3.1 covers the T73 and T73511 tempers, applicable to plate, die forging, hand forging, and extrusion products.

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Table 3.7.3.0(b). Design Mechanical and Physical Properties of 7049 Aluminum Alloy Plate
Specification AMS 4200
Form Plate
Temper T7351
Thickness, in. 0.750-1.0001.001-1.5001.501-2.0002.001-2.5002.501-3.0003.001-4.0004.001-4.5004.501-5.000
Basis SSSSSSSS
Mechanical Properties:
Ftu, ksi:
L······727271706868
LT7473737372706868
ST······696968656363
Fty, ksi:
L······646362605858
LT6564646362605858
ST······595857565454
Fcy, ksi:
L······6463626058···
LT······6968676462···
ST······6968676462···
Fsu, ksi······4141413938···
Fbrua, ksi:
(e/D = 1.5)·········114112109106···
(e/D = 2.0)·········146144140136···
Fbrya, ksi:
(e/D = 1.5)·········91898683···
(e/D = 2.0)·········10610410197···
e, percent:
L···············665
LT88766555
ST···············222
E, 103 ksi10.1
Ec, 103 ksi10.4
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.103
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]89 (at 77°F)
α, 10-6 in./in./°F13.0 (RT to 212°F)
a Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
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Table 3.7.3.0(c). Design Mechanical and Physical Properties of 7049/7149 Aluminum Alloy Die Forging
Specification AMS-QQ-A-367, AMS 4111, AMS 4320, and AMS-A-22771
Form Die forging
Temper T73a
Thicknessb, in. ≤1.0001.001-2.0002.001-3.0003.001-4.0004.001-5.000
Basis ABABABABAB
Mechanical Properties:
Ftu, ksi:
L71747073697268716770
Tc (S-basis)71d···70d···70d···70d···68d···
Fty, ksi:
L60645963586157605559
Tc (S-basis)61d···60d···60d···60d···58d···
Fcy, ksi:
L62666165606359625761
ST56605559545753565155
Fsu, ksi40413941394038403739
Fbrue, ksi:
(e/D = 1.5)1001059910398102961009599
(e/D = 2.0)132138130136128134126132125130
Fbrye, ksi:
(e/D = 1.5)76827580747873767075
(e/D = 2.0)93999197909488938591
e, percent (S-basis):
L7···7···7···7···7···
Tc3···3···3···2···2···
E, 103 ksi10.2
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.103
C, Btu/(lb)(°F)0.25 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]89 (at 77°F)
α, 10-6 in./in./°F13.0 (RT to 212°F)
a Design values were based upon data obtained from testing T73 die forgings, heat treated by suppliers and supplied in T73 temper.
b Thickness at the time of heat treatment. When die forgings are machined before heat treatment, the mechanical properties are applicable provided the as-forged thickness is not greater than twice the thickness at the time of heat treatment.
c T indicates any grain direction not within ±15° of being parallel to the forging flow lines. Fcy(T) values are based upon short transverse (ST) test data.
d Specification value. T tensile properties are presented on an S-basis only.
e Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.3.0(d). Design Mechanical and Physical Properties of 7049/7149 Aluminum Alloy Hand Forging
Specification AMS-QQ-A-367, AMS 4111, AMS 4320, and AMS-A-22771
Form Hand forging
Temper T73
Thicknessa, in. 2.001-3.0003.001-4.0004.001-5.000
Basis SSS
Mechanical Properties:
Ftu, ksi:
L716967
LT716967
ST696766
Fty, ksi:
L615956
LT595756
ST585655
Fcy, ksi:
L605857
LT615957
ST615958
Fsu, ksi:
L424139
LT413938
ST414039
Fbrub, ksi:
(e/D = 1.5)10210097
(e/D = 2.0)134130126
Fbryb, ksi:
(e/D = 1.5)817977
(e/D = 2.0)969291
e, percent:
L987
LT433
ST322
E, 103 ksi10.2
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb./in.30.103
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]89 (at 77°F)
α, 10-6 in./in./°F13.0 (RT to 212°F)
a When hand forgings are machined before heat treatment, section thickness at time of heat treatment will determine minimum mechanical properties as long as original (as-forged) thickness does not exceed maximum thickness for the alloy as shown in the table. The maximum cross-section area of hand forgings is 256 sq. in.
b Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.3.0(e). Design Mechanical and Physical Properties of 7049/7149 Aluminum Alloy Extrusion
Specification AMS 4157 and AMS 4343
Form Extrusion
Temper T73511
Thickness,a in. ≤2.4992.500-2.9993.000-5.000
Basis SSS
Mechanical Properties:
Ftu, ksi:
L747472
LT707068
ST···7068
Fty, ksi:
L646462
LT606058
ST···6058
Fcy, ksi:
L656563
LT·········
ST·········
Fsu, ksi404039
Fbrub, ksi:
(e/D = 1.5)110110107
(e/D = 2.0)144144140
Fbryb, ksi:
(e/D = 1.5)858583
(e/D = 2.0)105105101
e, percent:
L777
LT555
ST···55
E, 103 ksi10.5
Ec, 103 ksi11.0
G, 103 ksi4.0
μ0.33
Physical Properties:
ω, lb/in.30.103
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]89 (at 77°F)
α, 10-6 in./in./°F13.0 (RT to 212°F)
a The mechanical properties are to be based upon the thickness at the time of quench.
b Bearing values are “dry pin” values per Section 1.4.7.1.
3.7.3.1T73 and T73511 Tempers

Figure 3.7.3.1.1 presents elevated-temperature curves for various products. Figures 3.7.3.1.6(a) through (g) present tensile and compressive stress-strain and tangent-modulus curves. Fatigue data for 7049-T73 die and hand forgings are shown in Figures 3.7.3.1.8(a) through (g).

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Figure 3.7.3.1.1. Effect of temperature on the tensile ultimate strength (Ftu), the tensile yield strength (Fty), and the compressive yield strength (Fcy) of 7049-T7351 plate, 7049/7149-T73 hand forging, and 7049/7149-T73511 extrusion.

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Figure 3.7.3.1.6(a). Typical tensile stress-strain curves for 7049/7149-T73 aluminum alloy die forging at room temperature.

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Figure 3.7.3.1.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7049/7149-T73 aluminum alloy die forging at room temperature.

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Figure 3.7.3.1.6(c). Typical tensile stress-strain curves for 7049/7149-T73 aluminum alloy hand forging at room temperature.

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Figure 3.7.3.1.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 7049/7149-T73 aluminum alloy hand forging at room temperature.

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Figure 3.7.3.1.6(e). Typical tensile stress-strain curves for 7049-T7351 aluminum alloy plate at room temperature.

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Figure 3.7.3.1.6(f). Typical compressive stress-strain and compressive tangent-modulus curves for 7049-T7351 aluminum alloy plate at room temperature.

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Figure 3.7.3.1.6(g). Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7049/7149-T73511 extrusion at room temperature.

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Figure 3.7.3.1.8(a). Best-fit S/N curves for unnotched 7049-T73 die and hand forgings, at room temperature, longitudinal and long-transverse directions.

Stresses are based on net section.

Correlative Information for Figure 3.7.3.1.8(a)

Product Form: Die forging, 3 and 4.5 inches thick; hand forging, 2, 3, 4, and 5 inches thick

Properties: (L) TUS 78 ksi, TYS 70 ksi, RT; (LT) TUS 74 ksi, TYS 65 ksi, RT

Specimen Details: Unnotched
Uniform gage, 0.200 inch net diameter
Hourglass, 0.225 inch net diameter, 3.00 inch test-section radius
Hourglass, 0.300 inch net diameter, 9.875 inch test-section radius

Surface Condition: Longitudinally polished to 4 RMS finish or better; unspecified

Reference: 3.7.3.1.8(a), (b), and 3.2.6.1.9(d)

Test Parameters:
Loading – Axial
Frequency – 1800 cpm
Temperature – RT
Environment – Lab air

No. of Heats/Lots: 6

Stress Life Equation:
Log Nf = 9.95 − 3.62 log (Seq − 24.2)
Seq = Smax(1−R)0.57
Std. Error of Estimate, Log (Life) = 0.346
Standard Deviation, Log (Life) = 0.736
R2 = 78%

Sample Size: 50

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.3.1.8(b). Best-fit curves for unnotched 7049-T73 die forging, at room temperature, short-transverse direction.

Correlative Information for Figure 3.7.3.1.8(b)

Product Form: Die forging, 3 inches thick

Properties: TUS 73 ksi, TYS 64 ksi, RT

Specimen Details: Unnotched, 0.200 inch net diameter

Surface Condition: Longitudinally polished to 4 µin. finish with no circumferential marks

Reference: 3.7.3.1.8(a)

Test Parameters:
Loading – Axial
Frequency – 1800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 1

Maximum Stress Equation:
Log Nf = 16.55 − 6.92 log (Smax)
Std. Error of Estimate, Log (Life) = 0.371
Standard Deviation, Log (Life) = 0.917
R2 = 84%

Sample Size: 23
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Figure 3.7.3.1.8(c). Best-fit S/N curves for notched, Kt = 2.4, 7049-T73 die forging, at room temperature, longitudinal, long-transverse, and short-transverse directions.

Correlative Information for Figure 3.7.3.1.8(c)

Product Form: Die forging, 3 and 4.5 inches thick

Properties:
(L) Unnotched: TUS 77 ksi, TYS 68 ksi, RT; Notched: TUS 95 ksi, RT
(LT) Unnotched: TUS 73 ksi, TYS 64 ksi, RT; Notched: TUS 77 ksi, RT
(ST) Unnotched: TUS 75 ksi, TYS 66 ksi, RT; Notched: TUS 87 ksi, RT

Specimen Details: Circumferentially notched, Kt = 2.4
0.150 or 2.00 inch gross diameter
0.350 inch net diameter
0.500 inch gross diameter
0.032 inch notch root radius, r
60° flank angle

Surface Condition: Machined notch

References: 3.7.3.1.8(a) and (c)

Test Parameters:
Loading – Axial
Frequency – 1800 cpm
Temperature – RT
Environment – Lab air

No. of Heats/Lots: 2

Stress Life Equation:
Log Nf = 10.6 − 4.18 log (Seq)
Seq = Smax(1−R)0.80
Std. Error of Estimate, Log (Life) = 0.320
Standard Deviation, Log (Life) = 0.500
R2 = 59%

Sample Size: 69

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.3.1.8(d). Best-fit S/N curves for unnotched 7049-T73 hand forging, longitudinal direction.

Correlative Information for Figure 3.7.3.1.8(d)

Product Form: Hand forging, 2.0 to 5.0 inches thick

Properties: TUS 70–80 ksi, TYS 60–73 ksi, RT

Specimen Details: Unnotched, 0.125 and 0.300 inch diameter

Surface Condition: Polished with increasingly finer grits of emery paper to surface roughness of 10 rms with polishing marks longitudinal, or not specified

References: 3.2.6.1.9(d) and 3.7.3.1.8(e)

Test Parameters:
Loading – Axial
Frequency – 800, 1500, or 1725 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 6

Equivalent Stress Equation:
Log Nf = 10.6 − 4.31 log (Seq − 30)
Seq = Smax(1−R)0.31
Std. Error of Estimate, Log (Life) = 0.348
Standard Deviation, Log (Life) = 0.944
R2 = 86%

Sample Size: 28

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.3.1.8(e). Best-fit S/N curves for unnotched 7149-T73 hand forging, long-transverse direction.

Correlative Information for Figure 3.7.3.1.8(e)

Product Form: Hand forging, 4.00 to 4.75 inches thick

Properties: TUS 73 ksi, TYS 64 ksi, RT

Specimen Details: Unnotched, 0.250 inch diameter

Surface Condition: Not specified

Reference: 3.7.3.1.8(e)

Test Parameters:
Loading – Axial
Frequency – Not specified
Temperature – RT
Environment – Air

No. of Heats/Lots: 3

Equivalent Stress Equation:
Log Nf = 9.9 − 3.46 log (Seq − 25)
Seq = Smax(1−R)0.39
Std. Error of Estimate, Log (Life) = 0.689
Standard Deviation, Log (Life) = 0.845
R2 = 34%

Sample Size: 20

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.3.1.8(f). Best-fit S/N curves for notched, Kt = 3.0, 7049-T73 hand forging, longitudinal, long-transverse, and short-transverse directions.

Correlative Information for Figure 3.7.3.1.8(f)

Product Form: Hand forging, 2.0 to 5.0 inches thick

Properties: TUS 71–80 ksi, TYS 62–73 ksi, RT

Specimen Details: Circumferentially notched, Kt = 3.0
0.200, 0.300, and 0.306 inch gross diameter
0.175, 0.200, and 0.253 inch net diameter
0.006, 0.010, and 0.013 inch notch root radius, r
60° flank angle

Surface Condition: Polished with oil and alumdum grit applied to a rotating wire, or not specified

References: 3.2.6.1.9(d), 3.7.3.1.8(d), and (e)

Test Parameters:
Loading – Axial
Frequency – 800, 1500, or 1725 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 8

Equivalent Stress Equation:
Log Nf = 9.57 − 3.63 log (Seq)
Seq = Smax(1−R)0.49
Std. Error of Estimate, Log (Life) = 0.344
Standard Deviation, Log (Life) = 0.562
R2 = 63%

Sample Size: 151

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.3.1.8(g). Best-fit S/N curves for notched, Kt = 3.0, 7149-T73 hand forging, long-transverse direction.

Correlative Information for Figure 3.7.3.1.8(g)

Product Form: Hand forging, 4.00 to 4.75 inches thick

Properties: TUS 73 ksi, TYS 64 ksi, RT

Specimen Details: Circumferentially notched, Kt = 3.0
0.375 inch gross diameter
0.253 inch net diameter
0.013 inch notch root radius, r
60° flank angle

Surface Condition: Not specified

Reference: 3.7.3.1.8(e)

Test Parameters:
Loading – Axial
Frequency – Not specified
Temperature – RT
Environment – Air

No. of Heats/Lots: 3

Equivalent Stress Equation:
Log Nf = 10.1 − 4.10 log (Seq − 5)
Seq = Smax(1−R)0.42
Std. Error of Estimate, Log (Life) = 0.450
Standard Deviation, Log (Life) = 0.797
R2 = 68%

Sample Size: 25

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
3.7.47050 Alloy
3.7.4.0Comments and Properties

7050 is an Al-Zn-Mg-Cu-Zr alloy developed to have a combination of high strength, high resistance to stress-corrosion cracking, and good fracture toughness, particularly in thick sections. The use of zirconium in lieu of chromium provides a low sensitivity to quench, which results in high strengths in thick sections. Plate, hand, and die forgings in the T74 temper have static strengths about equivalent to those of corresponding products of 7079 in the T6 tempers and toughness levels equal to or higher than other conventional high-strength alloys.

The properties of extrusions should be based upon the thickness at the time of quenching prior to machining. Selection of the mechanical properties based upon its final machined thickness may be unconservative; therefore, the thickness at the time of quenching to achieve properties is an important factor in the selection of the proper thickness column. For extrusions having sections with various thicknesses, consideration should be given to the properties as a function of thickness.

Plate in the T7451 temper has stress-corrosion resistance higher than 7075-T7651, and hand and die forgings in the T7452 and T74 tempers, respectively, have stress-corrosion resistance similar to 7175-T74 forgings. The T73 temper provides the highest resistance to stress corrosion for this alloy. The T76 temper provides for good exfoliation resistance and higher stress-corrosion resistance than T6 tempers of 7075 and 7178. The T74 temper provides stress-corrosion and strength characteristics intermediate to those of T76 and T73. Refer to Section 3.1.2.3 for further comments regarding the resistance of the alloy to stress-corrosion cracking. Refer to Section 3.1.3.4 for comments regarding the weldability of this alloy.

Material specifications for 7050 are shown in Table 3.7.4.0(a). Room-temperature properties are shown in Tables 3.7.4.0(b1) through (e3).

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Table 3.7.4.0(a). Material Specifications for 7050 Aluminum Alloy
SpecificationForm
AMS 4050Bare plate
AMS 4108Hand forging
AMS 4107Die forging
AMS 4333Die forging
AMS 4340Extruded shape
AMS 4341Extruded shape
AMS 4342Extruded shape
AMS 4201Bare plate
AMS-A-22771Forging

The temper index for 7050 is: Section 3.7.4.1 covers the T73510 and T73511 tempers; Section 3.7.4.2 covers the T74, T7451, and T7452 tempers (formerly designated T736, T73651, and T73652); Section 3.7.4.3 covers the T76510 and T76511 tempers.

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Table 3.7.4.0(b1). Design Mechanical and Physical Properties of 7050 Aluminum Alloy Plate
Specification AMS 4050
Form Plate
Temper T7451
Thickness, in. 0.250-1.5001.501-2.0002.001-3.0003.001-4.0004.001-5.0005.001-6.0006.001-7.0007.001-8.000
Basis ABABABABABABABAB
Mechanical Properties:
Ftu, ksi:
L74a76747673a75727471a7370a7269726871
LT747674a7673a75727571a74707369726871
ST············687268a716770666966686567
Fty, ksi:
L64b6764b6663b6662b6561b656063596258b63
LT6466646663b6662656164606259625861
ST············5961576057b605759565855b58
Fcy, ksi:
L63646264616460635861575956595557
LT66686769666965686467636660635962
ST············636663666366626460635962
Fsu, ksi42434344434443454345434544464446
Fbruc, ksi:
(e/D = 1.5)107110109112108111107111107111105110107112103108
(e/D = 2.0)140144142146141144140144138144137142136143132138
Fbryc, ksi:
(e/D = 1.5)86898992899390949095919484898387
(e/D = 2.0)1011041041071041091041091051101051089910598102
e, percent (S-basis):
L10···10···9···9···9···8···7···6···
LT9···9···8···6···5···4···4···4···
ST············3···3···3···3···3···3···
E, 103 ksi10.3
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]91 (at 77°F)
α, 10-6 in./in./°F12.8 (68 to 212°F)
a S-basis values. Rounded T99 values for Ftu are as follows: for 0.250-1.500 (L) = 75 ksi, for 1.502-2.000 (LT) = 75 ksi, for 2.001-3.000 (L) and (LT) = 74 ksi, for 3.001-4.000 (ST) = 69 ksi, for 4.001-5.000 (L) and (LT) = 72 ksi, for 5.001-6.000 (L) = 71 ksi.
b S-basis values. Rounded T99 values for Fty are as follows: for 0.250-1.500 (L) = 65 ksi, for 1.502-2.000 (L) = 65 ksi, for 2.001-3.000 (L) = 65 ksi, (LT) = 64 ksi, for 3.001-4.000 (L) = 63 ksi, for 4.001-5.000 (L) = 62 ksi, (ST) = 58 ksi, for 7.001-8.000 (L) = 59 ksi, (ST) = 56 ksi.
c See Table 3.1.2.1.1. Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.4.0(b2). Design Mechanical and Physical Properties of 7050 Aluminum Alloy Plate
Specification AMS 4201
Form Plate
Temper T7651
Thickness, in. 0.250-1.0001.001-1.5001.501-2.0002.001-2.5002.501-3.000
Basis SABABABS
Mechanical Properties:
Ftu, ksi:
L7677797678757876
LT7676797578757876
ST·········7275707370
Fty, ksi:
L6666716670667066
LT6666706569656966
ST·········5963606260
Fcy, ksi:
L6464686467646764
LT6868736872687269
ST·········6771677168
Fsu, ksi4344464446454746
Fbrua, ksi:
(e/D = 1.5)110112117112117114118116
(e/D = 2.0)142144150144150146151149
Fbrya, ksi:
(e/D = 1.5)8790969196939896
(e/D = 2.0)102105111105112107114110
e, percent (S-basis):
L99···9···8···8
LT88···8···7···7
ST···············1.5···1.5
E, 103 ksi10.3
Ec, 103 ksi10.8
G, 103 ksi4.0
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]89 (at 77°F)
α, 10-6 in./in./°F12.8 (68 to 212°F)
a See Table 3.1.2.1.1. Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.4.0(c1). Design Mechanical and Physical Properties of 7050 Aluminum Alloy Die Forging
Specification AMS 4107 and AMS-A-22771
Form Die forging
Temper T74a
Thicknessb, in. ≤2.0002.001-4.0004.001-5.0005.001-6.000
Basis SSSS
Mechanical Properties:
Ftu, ksi:
L72717070
Tc68676666
Fty, ksi:
L62616059
Tc56555454
Fcy, ksi:
L63636362
ST60595857
Fsu, ksi42424141
Fbrud, ksi:
(e/D = 1.5)99989797
(e/D = 2.0)131129127127
Fbryd, ksi:
(e/D = 1.5)82817878
(e/D = 2.0)96959292
e, percent:
L7777
Tc5433
E, 103 ksi10.2
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]91 (at 77°F)
α, 10-6 in./in./°F12.8 (68 to 212°F)
a Design values were based upon data obtained from testing T74 die forgings, heat treated by suppliers and supplied in T74 temper.
b Thickness at the time of heat treatment. When die forgings are machined before heat treatment, the mechanical properties are applicable provided the as-forged thickness is not greater than twice the thickness at the time of heat treatment.
c T indicates any grain direction not within ±15° of being parallel to the forging flow lines. Fcy(T) values are based upon short transverse (ST) test data.
d Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.4.0(c2). Design Mechanical and Physical Properties of 7050-T7452 Aluminum Alloy Die Forging
Specification AMS 4333
Form Die forgings
Temper T7452
Thicknessb, in. ≤2.0002.001-4.000
Basis ABAB
Mechanical Properties:
Ftu, ksi:
L71737172
Ta68b7367c71
Fty, ksi:
L60635961
Ta55b6153c61
Fcy, ksi:
L63666264
ST63666264
Fsu, ksi43444343
Fbrud, ksi:
(e/D = 1.5)101104101103
(e/D = 2.0)135139135137
Fbryd, ksi:
(e/D = 1.5)87928689
(e/D = 2.0)105110103106
e, percent (S-basis):
L9···8···
Ta5···4···
E, 103 ksi10.2
Ec, 103 ksi10.5
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]91 (at 77°F)
α, 10-6 in./in./°F12.8 (68 to 212°F)
a T indicates any grain direction not within ±15° of being perpendicular to the forging flow lines. Fcy(T) values are based on short transverse (ST) test data.
b S-basis. The T99 values are higher than the specification minimum values as follows: Ftu(T) = 70.10 ksi, Fty(T) = 57.50 ksi.
c S-basis. The T99 values are higher than the specification minimum values as follows: Ftu(T) = 69.36 ksi, Fty(T) = 57.38 ksi.
d Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.4.0(d). Design Mechanical and Physical Properties of 7050 Aluminum Alloy Hand Forging
Specification AMS 4108 and AMS-A-22771
Form Hand Forging
Temper T7452
Thickness, in. ≤2.0002.001-3.0003.001-4.0004.001-5.0005.001-6.0006.001-7.0007.001-8.000
Basis SSSSSABS
Mechanical Properties:
Ftu, ksi:
L7272717069687167
LT7170706968677066
ST···67676666656964
Fty, ksi:
L6362616059566157
LT616059585654a5952
ST···5555545351a5650
Fcy, ksi:
L6362616058566154
LT6463626159576255
ST···63616058566154
Fsu, ksi4241414140404139
Fbrub, ksi:
(e/D = 1.5)9897979694939791
(e/D = 2.0)131129129127125123129121
Fbryb, ksi:
(e/D = 1.5)8684838279768373
(e/D = 2.0)101100989693909886
e, percent (S-basis):
L999999···9
LT555444···4
ST···44333···3
E, 103 ksi10.2
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]91 (at 77°F)
α, 10-6 in./in./°F12.8 (68 to 212°F)
a S-basis values. The rounded T99 values for Fty(LT) = 56 ksi and Fty(ST) = 52 ksi.
b Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.4.0(e1). Design Mechanical and Physical Properties of 7050 Aluminum Alloy Extrusion
Specification AMS 4341
Form Extrusion
Temper T73511
Cross-Sectional Area, in.2 ≤32
Thickness or Diameter,a in. ≤1.0001.001-2.0002.001-3.0003.001-4.0004.001-5.000
Basis SSSSS
Mechanical Properties:
Ftu, ksi:
L7070707070
LT6866656362
Fty, ksi:
L6060606060
LT5756555352
Fcy, ksi:
L6060606161
LT6059585655
Fsu, ksi3939383736
Fbrub, ksi:
(e/D = 1.5)103100969187
(e/D = 2.0)133129124120115
Fbryb, ksi:
(e/D = 1.5)8280787674
(e/D = 2.0)9795939188
e, percent:
L88888
E, 103 ksi10.3
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]93 (at 77°F)
α, 10-6 in./in./°F12.8 (68 to 212°F)
a The mechanical properties are to be based upon the thickness at the time of quench.
b Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.4.0(e2). Design Mechanical and Physical Properties of 7050 Aluminum Alloy Extrusion
Specification AMS 4342
Form Extrusiona
Temper T74511
Cross-Sectional Area, in.2 ≤32
Thickness or Diameter,b in. ≤1.0001.001-2.0002.001-3.0003.001-4.0004.001-5.000
Basis SSSSS
Mechanical Properties:
Ftu, ksi:
L7373737373
LT7169686464
Fty, ksi:
L6363636363
LT6059585654
Fcy, ksi:
L6363636464
LT6362615957
Fsu, ksi4140403938
Fbruc, ksi:
(e/D = 1.5)1071041009591
(e/D = 2.0)139135130125121
Fbryc, ksi:
(e/D = 1.5)8684828078
(e/D = 2.0)106100989592
e, percent:
L77777
E, 103 ksi10.3
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]93 (at 77°F)
α, 10-6 in./in./°F12.8 (68 to 212°F)
a Excluding tubing.
b The mechanical properties are to be based upon the thickness at the time of quench.
c Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.4.0(e3). Design Mechanical and Physical Properties of 7050 Aluminum Alloy Extrusion
Specification AMS 4340
Form Extrusion
Temper T76511
Thickness,a in. ≤0.4990.500-1.0001.001-2.0002.001-3.0003.001-4.0004.001-5.000
Basis ABSSSSS
Mechanical Properties:
Ftu, ksi:
L77797979797979
LT76787775737168
Fty, ksi:
L68716969696969
LT67696765636159
Fcy, ksi:
L68716969696969
LT70737069676664
Fsu, ksi42444343424140
Fbrub, ksi:
(e/D = 1.5)113116115114110107103
(e/D = 2.0)147151150148144140136
Fbryb, ksi:
(e/D = 1.5)94989492898682
(e/D = 2.0)1091141101081049893
e, percent (S-basis):
L7···77777
E, 103 ksi10.3
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]89 (at 77°F)
α, 10-6 in./in./°F12.8 (68 to 212°F)
a The mechanical properties are to be based upon the thickness at the time of quench.
b Bearing values are “dry pin” values per Section 1.4.7.1.
3.7.4.1T73510 and T73511 Tempers

Figures 3.7.4.1.6(a) through (d) present stress-strain and tangent-modulus curves for extrusions. Fatigue data are presented in Figures 3.7.4.1.8(a) and (b).

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Figure 3.7.4.1.6(a). Typical tensile stress-strain curves for 7050-T7351X aluminum alloy extrusion at room temperature.

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Figure 3.7.4.1.6(b). Typical tensile stress-strain curves for 7050-T7351X aluminum alloy extrusion at room temperature.

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Figure 3.7.4.1.6(c). Typical compressive stress-strain and tangent-modulus curves for 7050-T7351X aluminum alloy extrusion at room temperature.

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Figure 3.7.4.1.6(d). Typical compressive stress-strain and tangent-modulus curves for 7050-T7351X aluminum alloy extrusion at room temperature.

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Figure 3.7.4.1.8(a). Best-fit S/N curves for unnotched 7050-T7351X extruded shape, longitudinal and long-transverse directions.

Correlative Information for Figure 3.7.4.1.8(a)

Product Form: Extruded shape, 0.5 to 5.0 inch thick

Properties: TUS 72–79 ksi, TYS 62–69 ksi, RT

Specimen Details: Unnotched, 0.300 inch diameter

Surface Condition: Not specified

References: 3.7.4.2.9(b) and 3.7.7.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: Not specified

Equivalent Stress Equation:
Log Nf = 10.5 − 3.79 log (Seq − 16)
Seq = Smax(1−R)0.55
Std. Error of Estimate, Log (Life) = 0.516
Standard Deviation, Log (Life) = 1.10
R2 = 78%

Sample Size: 128

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.1.8(b). Best-fit S/N curves for notched, Kt = 3.0, 7050-T7351X extruded shape, longitudinal and long-transverse directions.

Correlative Information for Figure 3.7.4.1.8(b)

Product Form: Extruded shape, 0.5 to 5.0 inch thick

Properties: TUS 72–79 ksi, TYS 62–69 ksi, RT

Specimen Details: Circumferentially notched, Kt = 3.0
0.359 inch gross diameter
0.253 inch net diameter
0.013 inch root radius, r
60° flank angle

Surface Condition: Not specified

References: 3.7.4.2.9(b) and 3.7.7.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: Not specified

Equivalent Stress Equation:
Log Nf = 7.73 − 2.58 log (Seq − 5.0)
Seq = Smax(1−R)0.56
Std. Error of Estimate, Log (Life) = 0.268
Standard Deviation, Log (Life) = 0.733
R2 = 87%

Sample Size: 103

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
3.7.4.2T74, T7451, and T7452 Tempers

Elevated-temperature curves for T7451 plate are presented in Figure 3.7.4.2.1. Figures 3.7.4.2.6(a) through (j) present stress-strain and tangent-modulus curves for various products and tempers. Fatigue data are presented in Figures 3.7.4.2.8(a) through (l). Fatigue-crack-propagation data for T7451 plate are presented in Figures 3.7.4.2.9(a) through (c).

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Figure 3.7.4.2.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of 7050-T7451 aluminum alloy plate.

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Figure 3.7.4.2.6(a). Typical tensile stress-strain curves for 7050-T7451 aluminum alloy plate at room temperature.

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Figure 3.7.4.2.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7451 aluminum alloy plate at room temperature.

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Figure 3.7.4.2.6(c). Typical tensile stress-strain curves for 7050-T7452 aluminum alloy hand forging at room temperature.

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Figure 3.7.4.2.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7452 aluminum alloy hand forging at room temperature.

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Figure 3.7.4.2.6(e). Typical tensile stress-strain curves for 7050-T74 aluminum alloy die forging at room temperature.

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Figure 3.7.4.2.6(f). Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T74 aluminum alloy die forging at room temperature.

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Figure 3.7.4.2.6(g). Typical tensile stress-strain curves for 7050-T74511 aluminum alloy extrusion at room temperature.

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Figure 3.7.4.2.6(h). Typical compressive stress-strain and tangent-modulus curves for 7050-T74511 aluminum alloy extrusion at room temperature.

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Figure 3.7.4.2.6(i). Typical tensile stress-strain curves for 7050-T7452 aluminum alloy die forging at room temperature.

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Figure 3.7.4.2.6(j). Typical compressive stress-strain and tangent-modulus curves for 7050-T7452 aluminum alloy die forging at room temperature.

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Figure 3.7.4.2.8(a). Best-fit S/N curves for unnotched 7050-T7451 plate, longitudinal direction and T/2 specimen location.

Correlative Information for Figure 3.7.4.2.8(a)

Product Form: Plate, 1.0 inch thick

Properties: TUS 79 ksi, TYS 72 ksi, RT

Specimen Details: Unnotched, 0.30 inch diameter

Surface Condition: Not specified

References: 3.7.4.2.9(b) and 3.7.8.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 10

Equivalent Stress Equation:
Log Nf = 9.73 − 3.24 log (Seq − 15.5)
Seq = Smax(1−R)0.63
Std. Error of Estimate, Log (Life) = 0.490
Standard Deviation, Log (Life) = 0.942
R2 = 73%

Sample Size: 35

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(b). Best-fit S/N curves for unnotched 7050-T7451 plate, long-transverse direction, t/4 specimen location.

Correlative Information for Figure 3.7.4.2.8(b)

Product Form: Plate, 4.25 to 8.50 inches thick

Properties: TYS 62–67 ksi, RT (TUS not applicable)

Specimen Details: Unnotched, 0.250 inch diameter

Surface Condition: Polished, final surface finish unspecified

References: 3.7.4.2.8(d) and (e)

Test Parameters:
Loading – Axial
Frequency – 20 Hz
Temperature – RT
Environment – Air

Equivalent Stress Equation:
Log (Nf) = 16.410 − 6.624 log (Seq − 5.0)
Seq = Smax(1−R)0.65
Std. Error of Estimate, Log (Life) = 0.183
Standard Deviation, Log (Life) = 0.814
R2 = 95.0%

Sample Size: 57

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(c). Best-fit S/N curves for unnotched 7050-T7451 plate, long-transverse direction, t/2 specimen location.

Correlative Information for Figure 3.7.4.2.8(c)

Product Form: Plate, 4.25 to 8.50 inches thick

Properties: TYS 62–67 ksi, RT (TUS not applicable)

Specimen Details: Unnotched, 0.250 inch diameter

Surface Condition: Polished, final surface finish unspecified

References: 3.7.3.2.8(d) and (e)

Test Parameters:
Loading – Axial
Frequency – 20 Hz
Temperature – RT
Environment – Air

Equivalent Stress Equation:
Log (Nf) = 12.484 − 4.878 log (Seq − 60/t)
Seq = Smax(1−R)0.42, t = plate thickness in inches
Std. Error of Estimate, Log (Life) = 0.204
Standard Deviation, Log (Life) = 0.594
R2 = 88.2%

Sample Size: 36

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios and plate thicknesses beyond those represented above.]
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Cyclic stress-strain curve.

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Figure 3.7.4.2.8(d). Best-fit strain-life curves, cyclic stress-strain curve, and mean-stress-relaxation curve for 7050-T7451 plate, long-transverse direction, t/4 specimen location.

Correlative Information for Figure 3.7.4.2.8(d)

Product Form: Plate, 4.25 to 8.50 inches thick

Properties: TYS 62–67 ksi, RT (TUS not applicable)

Specimen Details: Unnotched, 0.250 inch diameter

Surface Condition: Polished, final surface finish unspecified

References: 3.7.3.2.8(d) and (e)

Test Parameters:
Loading – Axial, triangular waveform
Frequency – 0.50 Hz
Temperature – RT
Environment – Air

Sample Size: 53

[Caution: The equivalent strain model may provide unrealistic life predictions for strain ratios beyond those represented above.]

The cyclic stress-strain and mean-stress-relaxation equations for this figure were not transcribed: the OCR text extracted from MIL-HDBK-5J pp. 3-345–3-346 is corrupted (Greek-letter strain/stress symbols and exponents did not survive extraction) and could not be reconstructed with confidence. Refer to the original PDF for the equation set.
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Figure 3.7.4.2.8(e). Best-fit S/N curves for unnotched 7050-T7451 plate, long-transverse direction, t/4 specimen location.

Correlative Information for Figure 3.7.4.2.8(e)

Product Form: Plate, 1.0 to 6.0 inches thick

Properties: TUS 73–81 ksi, TYS 62–72 ksi, RT

Specimen Details: Unnotched, 0.250 and 0.300 inch diameter

Surface Condition: Not specified

References: 3.7.4.2.9(b), 3.7.8.2.8(b), and (e)

Test Parameters:
Loading – Axial
Frequency – 800 cpm and unspecified
Temperature – RT
Environment – Air

No. of Heats/Lots: 15

Equivalent Stress Equation:
Log Nf = 10.7 − 3.81 log (Seq − 10)
Seq = Smax(1−R)0.59
Std. Error of Estimate, Log (Life) = 0.507
Standard Deviation, Log (Life) = 0.794
R2 = 59%

Sample Size: 85

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(f). Best-fit S/N curves for notched, Kt = 3.0, 7050-T7451 plate, longitudinal and long-transverse directions, t/4 specimen location.

Correlative Information for Figure 3.7.4.2.8(f)

Product Form: Plate, 1.0 to 6.0 inches thick

Properties: TUS 75–81 ksi, TYS 65–72 ksi, RT

Specimen Details: Circumferentially notched, Kt = 3.0
0.306 and 0.373 inch gross diameter
0.253 inch net diameter
0.013 inch notch-tip radius, r
60° flank angle

Surface Condition: Not specified

References: 3.7.4.2.9(b), 3.7.8.2.8(b), and (c)

Test Parameters:
Loading – Axial
Frequency – 800 cpm and unspecified
Temperature – RT
Environment – Air

No. of Heats/Lots: 11

Equivalent Stress Equation:
Log Nf = 10.0 − 3.96 log (Seq)
Seq = Smax(1−R)0.64
Std. Error of Estimate, Log (Life) = 0.248
Standard Deviation, Log (Life) = 0.728
R2 = 88%

Sample Size: 79

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(g). Best-fit S/N curves for notched, Kt = 2.6, 7050-T7451X extruded shape, longitudinal direction.

Correlative Information for Figure 3.7.4.2.8(g)

Product Form: Extruded shape, 0.5 to 5.0 inch thick

Properties: TUS 76–77 ksi, TYS 67–68 ksi, RT

Specimen Details: Notched, center hole, Kt = 2.6
0.150 inch diameter
0.250 inch thick
1.00 inch wide

Surface Condition: Not specified

Reference: 3.7.4.2.8(a)

Test Parameters:
Loading – Axial
Frequency – Not specified
Temperature – RT
Environment – Air

No. of Heats/Lots: 6

Equivalent Stress Equation:
Log Nf = 8.23 − 2.82 log (Seq − 10)
Seq = Smax(1−R)0.30
Std. Error of Estimate, Log (Life) = 0.243
Standard Deviation, Log (Life) = 0.724
R2 = 89%

Sample Size: 34

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(h). Best-fit S/N curves for unnotched 7050-T7452 hand forgings, longitudinal direction.

Correlative Information for Figure 3.7.4.2.8(h)

Product Form: Hand forgings, 2.0 to 8.0 inch thick

Properties: TUS 76–81 ksi, TYS 66–72 ksi, RT

Specimen Details: Unnotched, 0.300 inch diameter

Surface Condition: Not specified

References: 3.7.4.2.9(b) and 3.7.7.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 10

Equivalent Stress Equation:
Log Nf = 7.06 − 1.89 log (Seq − 30)
Seq = Smax(1−R)0.60
Std. Error of Estimate, Log (Life) = 0.400
Standard Deviation, Log (Life) = 0.982
R2 = 83%

Sample Size: 25

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(i). Best-fit S/N curves for unnotched 7050-T7452 hand forgings, long-transverse and short-transverse directions.

Correlative Information for Figure 3.7.4.2.8(i)

Product Form: Hand forgings, 2.0 to 8.0 inch thick

Properties: TUS 73–80 ksi, TYS 59–70 ksi, RT

Specimen Details: Unnotched, 0.300 inch diameter

Surface Condition: Not specified

References: 3.7.4.2.9(b) and 3.7.8.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm and unspecified
Temperature – RT
Environment – Air

No. of Heats/Lots: 10

Equivalent Stress Equation:
Log Nf = 7.58 − 2.14 log (Seq − 21)
Seq = Smax(1−R)0.57
Std. Error of Estimate, Log (Life) = 0.400
Standard Deviation, Log (Life) = 0.803
R2 = 75%

Sample Size: 55

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(j). Best-fit S/N curves for notched, Kt = 3.0, 7050-T7452 hand forgings, longitudinal, long-transverse, and short-transverse directions.

Correlative Information for Figure 3.7.4.2.8(j)

Product Form: Hand forgings, 2.0 to 8.0 inch thick

Properties: TUS 73–81 ksi, TYS 59–72 ksi, RT

Specimen Details: Circumferentially notched, Kt = 3.0
0.306 inch gross diameter
0.253 inch net diameter
0.013 inch root radius, r
60° flank angle

Surface Condition: Not specified

References: 3.7.4.2.9(b) and 3.7.8.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 10

Equivalent Stress Equation:
Log Nf = 8.21 − 2.96 log (Seq − 5)
Seq = Smax(1−R)0.68
Std. Error of Estimate, Log (Life) = 0.307
Standard Deviation, Log (Life) = 0.735
R2 = 83%

Sample Size: 80

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(k). Best-fit S/N curves for unnotched 7050-T74 die forging, longitudinal direction.

Correlative Information for Figure 3.7.4.2.8(k)

Product Form: Die forging

Properties: TUS 74–81 ksi, TYS 68–71 ksi, RT

Specimen Details: Unnotched, 0.300 inch diameter

Surface Condition: Not specified

References: 3.7.4.2.9(b) and 3.7.8.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 4

Equivalent Stress Equation:
Log Nf = 16.8 − 6.97 log (Smax)
Std. Error of Estimate, Log (Life) = 0.381
Standard Deviation, Log (Life) = 0.820
R2 = 78%

Sample Size: 20

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.8(l). Best-fit S/N curves for notched, Kt = 3.0, 7050-T74 die forging, longitudinal direction.

Correlative Information for Figure 3.7.4.2.8(l)

Product Form: Die forging

Properties: TUS 77–81 ksi, TYS 68–71 ksi, RT

Specimen Details: Circumferentially notched, Kt = 3.0
0.306 and 0.305 inch gross diameter
0.253 or 0.222 inch net diameter
0.013 or 0.012 inch root radius, r
60° flank angle

Surface Condition: Not specified

References: 3.7.4.2.8(b), 3.7.4.2.9(b), and 3.7.8.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800, 1800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 6

Equivalent Stress Equation:
Log Nf = 10.5 − 4.14 log (Seq)
Seq = Smax(1−R)0.629
Std. Error of Estimate, Log (Life) = 0.506
Standard Deviation, Log (Life) = 0.896
R2 = 68%

Sample Size: 73

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.2.9(a). Fatigue-crack-propagation data for 3.15-inch-thick 7050-T7451 aluminum plate.

Specimen and Test Details for Figure 3.7.4.2.9(a)

Specimen Thickness: 0.499–0.500 inch

Specimen Width: 2.989–3.000 inches

Specimen Type: C(T)

Stress Ratio, R: 0.1

Environment: Lab air (~50% humidity) and humid air (100% humidity)

Temperature: RT

Frequency, f: 10–20 Hz

Reference: 3.7.4.2.9(a)
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Figure 3.7.4.2.9(b). Fatigue-crack-propagation data for 1and 6-inch-thick 7050-T7451 aluminum plate, dry air.

Specimen and Test Details for Figure 3.7.4.2.9(b)

Specimen Thickness: 0.999–1.000 inch

Specimen Width: 3.805 inches

Specimen Type: C(T)

Stress Ratio, R: 0.33

Environment: Dry air (< 10% humidity)

Temperature: RT

Frequency, f: 18.3 Hz

Reference: 3.7.4.2.9(b)
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Figure 3.7.4.2.9(c). Fatigue-crack-propagation data for 1and 6-inch-thick 7050-T7451 aluminum plate, humid air.

Specimen and Test Details for Figure 3.7.4.2.9(c)

Specimen Thickness: 0.998–1.000 inch

Specimen Width: 3.805 inches

Specimen Type: C(T)

Stress Ratio, R: 0.33

Environment: Humid air (>90% humidity)

Temperature: RT

Frequency, f: 18.3 Hz

Reference: 3.7.4.2.9(b)
3.7.4.3T76510 and T76511 Tempers

Figures 3.7.4.3.6(a) through (f) present stress-strain and tangent-modulus curves for extruded shapes and plate. Fatigue data are presented in Figures 3.7.4.3.8(a) and (b).

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Figure 3.7.4.3.6(a). Typical tensile stress-strain curves for 7050-T7651X aluminum alloy extrusion at room temperature.

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Figure 3.7.4.3.6(b). Typical tensile stress-strain curves for 7050-T7651X aluminum alloy extrusion at room temperature.

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Figure 3.7.4.3.6(c). Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7651X aluminum alloy extrusion at room temperature.

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Figure 3.7.4.3.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7651X aluminum alloy extrusion at room temperature.

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Figure 3.7.4.3.6(e). Typical tensile stress-strain curves for 7050-T7651 aluminum alloy plate at room temperature.

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Figure 3.7.4.3.6(f). Typical compressive stress-strain and compressive tangent-modulus curves for 7050-T7651 aluminum alloy plate at room temperature.

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Figure 3.7.4.3.8(a). Best-fit S/N curves for unnotched 7050-T7651X extruded shape, longitudinal and long-transverse directions.

Correlative Information for Figure 3.7.4.3.8(a)

Product Form: Extruded shape, 0.5 to 5.0 inch thick

Properties: TUS 84–90 ksi, TYS 75–81 ksi, RT

Specimen Details: Unnotched, 0.300 inch diameter

Surface Condition: Not specified

References: 3.7.4.3.8(b), 3.7.4.2.9(b), and 3.7.7.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 10

Equivalent Stress Equation:
Log Nf = 11.8 − 4.38 log (Seq − 12)
Seq = Smax(1−R)0.61
Std. Error of Estimate, Log (Life) = 0.493
Standard Deviation, Log (Life) = 1.01
R2 = 76%

Sample Size: 161

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.4.3.8(b). Best-fit S/N curves for notched, Kt = 3.0, 7050-T7651X extruded shape, longitudinal and long-transverse directions.

Correlative Information for Figure 3.7.4.3.8(b)

Product Form: Extruded shape, 0.5 to 5.0 inch thick

Properties: TUS 78–90 ksi, TYS 68–81 ksi, RT

Specimen Details: Circumferentially notched, Kt = 3.0
0.359 inch gross diameter
0.253 inch net diameter
0.013 inch root radius, r
60° flank angle

Surface Condition: Not specified

References: 3.7.4.2.9(b), 3.7.4.3.8(a), and 3.7.7.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 10

Equivalent Stress Equation:
Log Nf = 10.38 − 4.26 log (Seq)
Seq = Smax(1−R)0.563
Std. Error of Estimate, Log (Life) = 0.398
Standard Deviation, Log (Life) = 0.778
R2 = 74%

Sample Size: 179

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
3.7.57055 Alloy
3.7.5.0Comments and Properties

7055 is an Al-Zn-Mg-Cu-Zr alloy and provides higher strength properties than 7150. 7055 is available in the form of plate and extrusions. The T77-type temper provides high tensile and compressive strength with guaranteed toughness (plate only) and exfoliation corrosion resistance. The T77-type temper has exfoliation corrosion resistance comparable to the T76-type temper of other 7XXX series aluminum alloys.

The properties of extrusions should be based upon the thickness at the time of extrusion, solution heat treatment, and quenching prior to machining. Selection of the mechanical properties based upon final machined thickness may be overstated; therefore, the thickness at the time of extrusion, solution heat treatment, and quenching to achieve properties is an important factor in the selection of the proper thickness column. For extrusions having sections with various thicknesses, consideration should be given to the properties as a function of thickness.

Material specifications for 7055 are shown in Table 3.7.5.0(a). Room-temperature mechanical properties are presented in Tables 3.7.5.0(b) through (e).

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Table 3.7.5.0(a). Material Specifications for 7055 Aluminum Alloy
SpecificationForm
AMS 4206 (T7751)Plate
AMS 4324 (T74511)Extrusion
AMS 4336 (T76511)Extrusion
AMS 4337 (T77511)Extrusion
Temper Index for 7055 Alloy
SectionTemper
3.7.5.1T74511
3.7.5.2T76511
3.7.5.3T7751 and T77511
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Table 3.7.5.0(b). Design Mechanical and Physical Properties of 7055-T74511 Aluminum Alloy Extrusions
SpecificationAMS 4324
FormExtrusion
TemperT74511
Thickness, in.≤0.2490.250-0.4990.500-3.000
BasisABABAB
Mechanical Properties:
Ftu, ksi:
L8384848585a87
LT787979808082
Fty, ksi:
L7678777978a80
LT727473757476
Fcy, ksi:
L767877797880
LT777978807981
Fsub, ksi434446454546
Fbruc, ksi:
(e/D = 1.5)115116116117117120
(e/D = 2.0)151152152154154158
Fbryc, ksi:
(e/D = 1.5)96999710099101
(e/D = 2.0)114117116119117120
e, percent (S-basis):
L8···8···8···
LT··················
E, 103 ksi10.3
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.103
C, Btu/(lb)(°F)···
K, Btu/[(hr)(ft2)(°F)/ft]···
α, 10-6 in./in./°F···
a Rounded T99 values for Ftu = 86 ksi, for Fty = 79 ksi.
b Determined in accordance with ASTM B769.
c Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.5.0(c). Design Mechanical and Physical Properties of 7055-T76511 Aluminum Alloy Extrusions
SpecificationAMS 4336
FormExtrusion
TemperT76511
Thickness, in.≤0.2490.250-0.499
BasisABAB
Mechanical Properties:
Ftu, ksi:
L89a919094
LT83858487
Fty, ksi:
L85878591
LT79817985
Fcy, ksi:
L84868591
LT86888692
Fsub, ksi46474749
Fbruc, ksi:
(e/D = 1.5)122125124129
(e/D = 2.0)160163161169
Fbryc, ksi:
(e/D = 1.5)105107105112
(e/D = 2.0)124127124132
e, percent (S-basis):
L7···9···
LT············
E, 103 ksi10.4
Ec, 103 ksi10.8
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.103
C, Btu/(lb)(°F)···
K, Btu/[(hr)(ft2)(°F)/ft]···
α, 10-6 in./in./°F···
a Rounded T99 values for Ftu = 90 ksi.
b Determined in accordance with ASTM B769.
c Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.5.0(d). Design Mechanical and Physical Properties of 7055-T7751 Aluminum Alloy Plate
SpecificationAMS 4206
FormPlate
TemperT7751
Thickness, in.0.500 - 1.500
BasisAB
Mechanical Properties:
Ftu, ksi:
L8991
LT8991
Fty, ksi:
L8688
LT8587
Fcy, ksi:
L8688
LT8991
Fsua, ksi4849
Fbrub, ksi:
(e/D = 1.5)128131
(e/D = 2.0)167170
Fbryb, ksi:
(e/D = 1.5)112115
(e/D = 2.0)130133
e, percent (S-basis):
L7···
LT8···
E, 103 ksi10.4
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.32
Physical Properties:
ω, lb/in.30.103
C, Btu/(lb)(°F)···
K, Btu/[(hr)(ft2)(°F)/ft]···
α, 10-6 in./in./°F···
a Determined in accordance with ASTM B769.
b Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.5.0(e). Design Mechanical and Physical Properties of 7055-T77511 Aluminum Alloy Extrusion
SpecificationAMS 4337
FormExtrusion
Cross-sectional area, in.2···
TemperT77511
Thickness, in.0.500 - 1.500
BasisAB
Mechanical Properties:
Ftu, ksi:
L9495
LT8890
Fty, ksi:
L9093
LT84a88
Fcy, ksi:
L9294
LT8992
Fsub, ksi4849
Fbruc, ksi:
(e/D = 1.5)128131
(e/D = 2.0)167169
Fbryc, ksi:
(e/D = 1.5)109113
(e/D = 2.0)131135
e, percent (S-basis):
L9···
LT5···
E, 103 ksi10.4
Ec, 103 ksi11.0
G, 103 ksi···
μ0.33
Physical Properties:
ω, lb/in.30.103
C, Btu/(lb)(°F)···
K, Btu/[(hr)(ft2)(°F)/ft]···
α, 10-6 in./in./°F···
a S-basis. The T99 value is 85.86 ksi.
b Determined in accordance with ASTM B769.
c Bearing values are “dry pin” values per Section 1.4.7.1.
3.7.67075 Alloy
3.7.6.0Comments and Properties

7075 is a high-strength Al-Zn-Mg-Cu alloy and is available in a wide variety of product forms. It is also available in several types of tempers, the T6, T73, and T76 type. The T6 temper has the highest strength but lowest toughness and resistance to stress-corrosion cracking. Since toughness decreases with a decrease in temperature, the T6 temper is not generally recommended for cryogenic applications. As shown in Table 3.1.2.3.1(a), 7075-T6 rolled plate, rod and bar, extruded shapes, and forgings have a “D” SCC rating. This is the lowest rating and means that SCC failures have occurred in service or would be anticipated if there is any sustained stress. In-service failures are caused by stresses produced by any combination of sources including solution heat treatment, straightening, forming, fit-up, clamping, sustained service loads, or high service compression stresses that produce residual tensile stresses. These stresses may be tension or compression as well as the stresses due to the Poisson effect, because the actual failures are caused by the resulting sustained shear stresses. Pin-hole flaws in corrosion protection are sufficient for SCC. The T73 temper provides for much improved stress-corrosion resistance over T6 temper with a decrease in strength. The T76 temper provides for improved exfoliation resistance and limited stress-corrosion resistance over T6 temper with some decrease in strength. Refer to Section 3.1.2.3 for comments regarding the resistance of the alloy to stress-corrosion cracking and to Section 3.1.3.4 for comments regarding the weldability of this alloy.

The properties of extrusions should be based upon the thickness at the time of quenching prior to machining. Selection of the mechanical properties based upon its final machined thickness may be unconservative; therefore, the thickness at the time of quenching to achieve properties is an important factor in the selection of the proper thickness column. For extrusions having sections with various thicknesses, consideration should be given to the properties as a function of thickness.

Material specifications for 7075 aluminum alloy are presented in Table 3.7.6.0(a). Room-temperature mechanical and physical properties are shown in Tables 3.7.6.0(b1) through (g3). The effect of temperature on the physical properties of this alloy is presented in Figure 3.7.6.0.

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Table 3.7.6.0(a). Material Specifications for 7075 Aluminum Alloy
SpecificationForm
AMS 4044Bare sheet and plate
AMS 4045Bare sheet and plate
AMS 4078Bare plate
AMS-QQ-A-250/12, 24Bare sheet and plate
AMS-QQ-A-250/13, 25Clad sheet and plate
AMS 4049Clad sheet and plate
AMS 4122Bar and rod, rolled or cold-finished
AMS 4123Bar and rod, rolled or cold-finished
AMS 4124Bar and rod, rolled or cold-finished
AMS 4186Bar and rod, rolled or cold-finished
AMS 4187Bar and rod, rolled or cold-finished
AMS-QQ-A-225/9Rolled or drawn bar and rod
AMS-QQ-A-200/11, 15Extruded bar, rod, and shapes
AMS 4126Forging
AMS 4141Die forging
AMS 4147Forging
AMS-A-22771Forging
AMS-QQ-A-367Forging
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Table 3.7.6.0(b1). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Sheet and Plate
SpecificationAMS 4045 and AMS-QQ-A-250/12
FormSheetPlate
TemperT6 and T62aT651
Thickness, in.0.008-
0.011		0.012-
0.039		0.040-
0.125		0.126-
0.249		0.250-
0.499		0.500-
1.000		1.001-
2.000		2.001-
2.500		2.501-
3.000		3.001-
3.500		3.501-
4.000
BasisSABABABABABABABABABAB
Mechanical Properties:
Ftu, ksi:
L···7678788078807779777976787577717370b71b6668
LT7476787880788078807880767966b68b65b67b61b63b58···
ST·······································70b71b66b68b65b67b61b63
Fty, ksi:
L···6972707271736971707269716668636656585152
LT636770687069716870687067696466616359b61b56b58b
ST·······································59b61b56b58b54b55b50b52b
Fcy, ksi:
L···6871697170726769687066686264586055575152
LT···7174727473757173687471736770616457595759
ST·······································6770646661635759
Fsu, ksi···4647474847484344444544454445424342433941
Fbruc, ksi:
(e/D = 1.5)···118121121124121124117120117120116119114117108111107110101104
(e/D = 2.0)···152156156160156160145148145148143147141145134137132135124128
Fbryc, ksi:
(e/D = 1.5)···1001051021051031069710097100981019497899389938487
(e/D = 2.0)···11712211912212112410011811712010111710911210410893978487
e, percent (S-basis):
LT57···8···8···9···7···6···5···5·········3···
E, 103 ksi10.310.3
Ec, 103 ksi10.510.6
G, 103 ksi3.93.9
μ0.330.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a Design allowables were based upon data obtained from testing T6 temper sheet and from testing samples of sheet, supplied in the O or F temper, which were heat treated to demonstrate response to heat treatment by suppliers. Properties obtained by the user may be lower than those listed if the material has been formed or otherwise cold worked, particularly in the annealed temper, prior to solution heat treatment.
b Caution: This specific alloy, temper, and product form exhibits poor stress-corrosion cracking resistance in this grain direction. It corresponds to an SCC resistance rating of D, as indicated in Table 3.1.2.3.1(a).
c Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(b2). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Plate—Continued
SpecificationAMS 4044 and AMS-QQ-A-250/12AMS-QQ-A-250/12
FormPlate
TemperT62a
Thickness, in.0.250-
0.499		0.500-
1.000		1.001-
2.000		2.001-
2.500		2.501-
3.000		3.001-
3.500		3.501-
4.000
BasisABABABABABABAB
Mechanical Properties:
Ftu, ksi:
L7476747673757274697168706466
LT78807880777970b71b66b68b65b67b61b63b
ST··················70b71b66b68b65b67b61b63b
Fty, ksi:
L6567666864676062565852544849
LT6769687067696466616358605456
ST··················59b61b56b58b54b55b50b52b
Fcy, ksi:
L7072707268706365596155575052
LT7072717368686567616357595254
ST··················6365606257595355
Fsu, ksi4344444544454445424342433941
Fbruc, ksi:
(e/D = 1.5)117120117120116119114117108111107110101104
(e/D = 2.0)145148145148143147141145134137132135124128
Fbryc, ksi:
(e/D = 1.5)9710010010310010398101949789938487
(e/D = 2.0)11411811712011712011311710911210410898103
e, percent (S-basis):
LT9···7···6···5···5···5···3···
E, 103 ksi10.3
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a Design allowables were based upon data obtained from testing samples of plate, supplied in O or F temper, which were heat treated to demonstrate response to heat treatment by suppliers. Properties obtained by the user may be lower than those listed if the material has been formed or otherwise cold worked, particularly in the annealed temper, prior to solution heat treatment.
b Caution: This specific alloy, temper, and product form exhibits poor stress-corrosion cracking resistance in this grain direction. It corresponds to an SCC resistance rating of D, as indicated in Table 3.1.2.3.1(a).
c Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(b3). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Sheet and Plate—Continued
SpecificationAMS-QQ-A-250/12AMS 4078 and AMS-QQ-A-250/12
FormSheetPlate
TemperT73T7351
Thickness, in.0.040-
0.249		0.250-
0.499		0.500-
1.000		1.001-
1.500		1.501-
2.000		2.001-
2.500		2.501-
3.000		3.001-
3.500		3.501-4.000
BasisSSABABABABABSS
Mechanical Properties:
Ftu, ksi:
L6768687067696668656763656260
LT6769697168706769666864a666361
ST··················6365626460625957
Fty, ksi:
L5657575957595557525549534948
LT565757595759555752b5549a534948
ST··················5254495247504746
Fcy, ksi:
L5556565856585355505347514745
LT5859596159615759545751555150
ST··················5961555851555048
Fsu, ksi3838383938403940394038393837
Fbruc, ksi:
(e/D = 1.5)1051021031061031061021061021051001039996
(e/D = 2.0)134131132136132136132136131135128132127124
Fbryc, ksi:
(e/D = 1.5)8479818383868285798376817676
(e/D = 2.0)10295971009910297101939989968988
e, percent (S-basis):
LT877···6···6···6···6···66
E, 103 ksi10.310.3
Ec, 103 ksi10.510.6
G, 103 ksi3.93.9
μ0.330.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a S-basis. The rounded T99 values are as follows: Ftu(LT) = 65 ksi and Fty(LT) = 52 ksi.
b S-basis. The rounded T99 value is as follows: Fty(LT) = 53 ksi.
c Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(b4). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Sheet and Plate—Concluded
SpecificationAMS-QQ-A-250/24
FormSheet and plate
TemperT76T7651
Thickness, in.0.063-0.2490.250-0.4990.500-1.0001.001-1.5001.501-2.000
BasisSSSSS
Mechanical Properties:
Ftu, ksi:
L7271707070
LT7372717171
ST············65
Fty, ksi:
L6260595959
LT6261606060
ST············56
Fcy, ksi:
L6160595959
LT6564636363
ST············63
Fsu, ksi4240414243
Fbrua, ksi:
(e/D = 1.5)112109108108108
(e/D = 2.0)145141140140140
Fbrya, ksi:
(e/D = 1.5)8886868687
(e/D = 2.0)102999999100
e, percent:
LT88655
E, 103 ksi10.310.3
Ec, 103 ksi10.510.6
G, 103 ksi3.93.9
μ0.330.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(c1). Design Mechanical and Physical Properties of Clad 7075 Aluminum Alloy Sheet
SpecificationAMS 4049
FormSheet
TemperT6
Thickness, in.0.008-
0.011		0.012-
0.039		0.040-
0.062		0.063-
0.187		0.188-
0.249
BasisSABABABAB
Mechanical Properties:
Ftu, ksi:
L···7174717574777577
LT687174717574a777577
Fty, ksi:
L···6265636666696668
LT586063616464676466
Fcy, ksi:
L···6164626565686567
LT···6467656868716870
Fsu, ksi···4244424544464546
Fbrub, ksi:
(e/D = 1.5)···110115110116115119116119
(e/D = 2.0)···142148142150148154150154
Fbryb, ksi:
(e/D = 1.5)···90949196961009699
(e/D = 2.0)···105110106112112117112115
e, percent (S-basis):
LT58···9···9···9···
E, 103 ksi:
Primary10.310.310.3
Secondary9.59.810.0
Ec, 103 ksi:
Primary10.510.510.5
Secondary9.710.010.2
G, 103 ksi·········
μ0.330.330.33
Physical Properties:
ω, lb/in.30.101
C, K, and α···
a S-Basis. The rounded T99 value is 75 ksi.
b Bearing values are “dry pin” values per Section 1.4.7.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(c2). Design Mechanical and Physical Properties of Clad 7075 Aluminum Alloy Sheet—Continued
SpecificationAMS-QQ-A-250/13
FormSheet
TemperT6 and T62a
Thickness, in.0.008-
0.011		0.012-
0.039		0.040-
0.062		0.063-
0.187		0.188-
0.249
BasisSABABABAB
Mechanical Properties:
Ftu, ksi:
L···7074717573777577
LT6870b74717573c777577
Fty, ksi:
L···6265636665696668
LT586063616463d676466
Fcy, ksi:
L···6164626564686567
LT···6467656867716870
Fsu, ksi···4244424544464546
Fbrue, ksi:
(e/D = 1.5)···108115110116113119116119
(e/D = 2.0)···140148142150146154150154
Fbrye, ksi:
(e/D = 1.5)···90949196941009699
(e/D = 2.0)···105110106112110117112115
e, percent (S-basis):
LT57···8···8···8···
E, 103 ksi:
Primary10.310.310.3
Secondary9.59.810.0
Ec, 103 ksi:
Primary10.510.510.5
Secondary9.710.010.2
G, 103 ksi·········
μ0.330.330.33
Physical Properties:
ω, lb/in.30.101
C, K, and α···
a Design allowables were based upon data obtained from testing T6 temper sheet and from testing samples of sheet, supplied in the O or F temper, which were heat treated to demonstrate response to heat treatment by suppliers. Properties obtained may be lower than those listed if the material has been formed or otherwise cold worked, particularly in the annealed temper, prior to solution heat treatment.
b S-Basis. The rounded T99 value is 71 ksi.
c S-Basis. The rounded T99 value is 75 ksi.
d S-Basis. The rounded T99 value is 64 ksi.
e Bearing values are “dry pin” values per Section 1.4.7.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(c3). Design Mechanical and Physical Properties of Clad 7075 Aluminum Alloy Plate—Continued
SpecificationAMS 4049 and AMS-QQ-A-250/13
FormPlate
TemperT651
Thickness, in.0.250-
0.499		0.500-
1.000a		1.001-
2.000a		2.001-
2.500a		2.501-
3.000a		3.001-
3.500a		3.501-
4.000a
BasisABABABABABABAB
Mechanical Properties:
Ftu, ksi:
L7476757774767375697168706466
LT75777678757774b76b66b68b65b67b61b63b
ST··················70b71b66b68b65b67b61b63b
Fty, ksi:
L6769687067696466616358605456
LT65676668656762b64b59b61b56b58b52b54b
ST··················59b61b56b58b54b55b50b52b
Fcy, ksi:
L6567666864666062575853554951
LT6971707269716568626459615557
ST··················6770646661635759
Fsu, ksi4243424442444344414240423839
Fbruc, ksi:
(e/D = 1.5)11311611411711311611111410510810410798101
(e/D = 2.0)139143141145139143137141130134128132121124
Fbryc, ksi:
(e/D = 1.5)949797100971009598909486898084
(e/D = 2.0)1111141131161131171101131051091001049397
e, percent (S-basis):
LT9···7···6···5···5···5···3···
E, 103 ksi:
Primary10.3
Secondary10.0
Ec, 103 ksi:
Primary10.6
Secondary10.3
G, 103 ksi···
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and α···
a These values, except in the ST direction, have been adjusted to represent the average properties across the whole section, including the 1-1/2 percent per side nominal cladding thickness.
b Caution: This specific alloy, temper, and product form exhibits poor stress-corrosion cracking resistance in this grain direction. It corresponds to an SCC resistance rating of D, as indicated in Table 3.1.2.3.1(a).
c Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(c4). Design Mechanical and Physical Properties of Clad 7075 Aluminum Alloy Plate—Continued
SpecificationAMS-QQ-A-250/13
FormPlate
TemperT62a
Thickness, in.0.250-
0.499		0.500-
1.000b		1.001-
2.000b		2.001-
2.500b		2.501-
3.000b		3.001-
3.500b		3.501-
4.000b
BasisABABABABABABAB
Mechanical Properties:
Ftu, ksi:
L7273727472737172676966696265
LT75777678757774c76c70c71c66c68c61c63c
ST··················70c71c66c68c65c67c61c63c
Fty, ksi:
L6365646662645860545650524648
LT65676668656762c64c59c61c56c58c52c54c
ST··················59c61c56c58c54c55c50c52c
Fcy, ksi:
L6870687066686263575953554850
LT6870697166686265596155575255
ST··················6365606257595355
Fsu, ksi4243424442444344414240423839
Fbrud, ksi:
(e/D = 1.5)11311611411711311611111410510810410798101
(e/D = 2.0)139143141145139143137141130134128132121124
Fbryd, ksi:
(e/D = 1.5)949797100971009598909486898084
(e/D = 2.0)1111141131161131171101131051091001049397
e, percent (S-basis):
LT9···7···6···5···5···5···3···
E, 103 ksi:
Primary10.3
Secondary10.0
Ec, 103 ksi:
Primary10.6
Secondary10.3
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and α···
a Design allowables were based upon data obtained from testing samples of plate, supplied in the O or F temper, which were heat treated to demonstrate response to heat treatment by suppliers. Properties obtained may be lower than those listed if the material has been formed or otherwise cold worked, particularly in the annealed temper, prior to solution heat treatment.
b These values, except in the ST direction, have been adjusted to represent the average properties across the whole section.
c Caution: This specific alloy, temper, and product form exhibits poor stress-corrosion cracking resistance in this grain direction. It corresponds to an SCC resistance rating of D, as indicated in Table 3.1.2.3.1(a).
d Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(c5). Design Mechanical and Physical Properties of Clad 7075 Aluminum Alloy Sheet and Plate—Continued
SpecificationAMS-QQ-A-250/25
FormSheetPlate
TemperT76T7651
Thickness, in.0.040-0.0620.063-0.1870.188-0.2490.250-0.4990.500-1.000a
BasisSSSSS
Mechanical Properties:
Ftu, ksi:
L6667696868
LT6768706968
Fty, ksi:
L5657595857
LT5657595857
Fcy, ksi:
L5556585756
LT5960626059
Fsu, ksi4140404040
Fbrub, ksi:
(e/D = 1.5)103104107105103
(e/D = 2.0)133135139133131
Fbryb, ksi:
(e/D = 1.5)8081848787
(e/D = 2.0)929497104103
e, percent:
LT88886
E, 103 ksi:
Primary10.310.310.3
Secondary9.810.010.0
Ec, 103 ksi:
Primary10.510.510.6
Secondary10.010.210.3
G, 103 ksi·········
μ0.330.330.33
Physical Properties:
ω, lb/in.30.101
C, K, and α···
a These values have been adjusted to represent the average properties across the whole section, including the 1-1/2 percent per side nominal cladding thickness.
b Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(d). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Bar, Rod, and Shapes: Rolled, Drawn, or Cold-Finished
SpecificationAMS 4122, AMS 4123, AMS 4186, AMS 4187, and AMS-QQ-A-225/9AMS 4124 and AMS-QQ-A-225/9
FormBar, rod, and shapes: rolled, drawn, or cold-finished
TemperT6, T651, and T62aT73b or T7351
Thicknessc, in.<1.0001.001-
2.000		2.001-
3.000		3.001-
4.000		0.375-
2.000		2.001-
3.000
BasisABABABABSS
Mechanical Properties:
Ftu, ksi:
L77797779777977796868
LT77d79d75d77d72d74d69d71d···65e
Fty, ksi:
L66686668666866685656
LT66d68d66d68d63d65d60d62d···52e
Fcy, ksi:
L64666466646664665454
LT···························55e
Fsu, ksi46474647464746474240
Fbruf, ksi:
(e/D = 1.5)100103100103100103100103101101
(e/D = 2.0)123126123126123126123126131131
Fbryf, ksi:
(e/D = 1.5)86888688868886888181
(e/D = 2.0)929592959295929595100
e, percent (S-basis):
L7···7···7···7···1010
E, 103 ksi10.3
Ec, 103 ksi10.5
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a Design allowables were based upon data obtained from testing of T6 and T651 material and from samples of material, supplied in the O or F temper, which were heat treated to T62 temper to demonstrate response to heat treatment by suppliers.
b Design allowables were based upon data obtained from testing T73 and T7351 temper material and from testing samples of material, supplied in the O or F temper, which were heat treated to T73 temper to demonstrate response to heat treatment by suppliers.
c For rounds (rod) maximum diameter is 4 inches; for square bar, maximum size is 3½ inches; for rectangular bar, maximum thickness is 3 inches with corresponding width of 6 inches; for rectangular bar less than 3 inches in thickness, maximum width is 10 inches.
d Caution: This specific alloy, temper, and product form exhibits poor stress-corrosion cracking resistance in this grain direction. It corresponds to an SCC resistance rating of D, as indicated in Table 3.1.2.3.1(a). ST grain direction.
e ST grain direction.
f Bearing values are “dry pin” values per Section 1.4.7.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(e1). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Die Forging
SpecificationAMS 4126, MIL-A-22771, and QQ-A-367MIL-A-22771 and QQ-A-367
FormDie forging
TemperT6aT652
Thicknessb, in.<1.0001.001-
2.000		2.001-
3.000		3.001-
4.000		<1.0001.001-
2.000		2.001-
3.000		3.001-
4.000
BasisABABABSABABABS
Mechanical Properties:
Ftu, ksi:
L7578747774767375787477747673
Tc71d···71d···70d···7071d···71d···70d···70
Fty, ksi:
L6467636663656264676366636562
Tc61d···61d···60d···6060d···60d···59d···59
Fcy, ksi:
L6770666966686564676366636562
ST6468646763666365696568646764
Fsu, ksi4345434442434243454344424342
Fbrue, ksi:
(e/D = 1.5)105109104108104106102105109104108104106102
(e/D = 2.0)135140133138133136131135140133138133136131
Fbry, ksi:
(e/D = 1.5)8387828682848183878286828481
(e/D = 2.0)961009499949793961009499949793
e, percent (S-basis):
L7···7···7···77···7···7···7
Tc3···3···3···23···3···3···2
E, 103 ksi10.0
Ec, 103 ksi10.4
G, 103 ksi3.8
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a When die forgings are machined before heat treatment, the mechanical properties are applicable provided the as-forged thickness is not greater than twice the thickness at time of heat treatment.
b Thickness at the time of heat treatment.
c T indicates any grain direction not within ±15° of being parallel to the forging flow lines. Fcy(T) values are based upon short transverse (ST) test data.
d Specification value. T tensile properties are presented on an S basis only.
e Bearing values are “dry pin” values per Section 1.4.7.1.
Open this page of MIL-HDBK-5
Table 3.7.6.0(e2). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Die Forging—Continued
SpecificationAMS 4141, AMS-A-22771, and AMS-QQ-A-367AMS 4141AMS 4147, AMS-A-22771, and AMS-QQ-A-367
FormDie forging
TemperT73a,bT7352
Thicknesse, in.<1.0001.001-
2.000		2.001-
3.000		3.001-
4.000		4.001-
5.000		5.001-
6.000		<3.0003.001-
4.000
BasisABABABABSSABS
Mechanical Propertiesd:
Ftu, ksi:
L66d7166d71666964d69626166e6964
Tf62g···62g···62g···61g···595862g···61
Fty, ksi:
L56d6156d61565955d595351565953
Tf53g···53g···53g···52g···515051g···49
Fcy, ksi:
L5863586158615761······565953
Tf5560555955595458······556053
Fsu, ksi3942394239413841······394138
Fbruh, ksi:
(e/D = 1.5)96103961039610093100······9610093
(e/D = 2.0)125135125135125131122131······125131122
Fbryh, ksi:
(e/D = 1.5)7885788378837783······788374
(e/D = 2.0)9098909490948894······909485
e, percent (S-basis):
L7···7···7···7···767···7
Tf3···3···3···2···2···3···2
E, 103 ksi10.0
Ec, 103 ksi10.4
G, 103 ksi3.8
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a When die forgings are machined before heat treatment, the mechanical properties are applicable, provided the as-forged thickness is not greater than twice the thickness at time of heat treatment.
b Design allowables were based upon data obtained from testing die forgings, heat treated by suppliers, and supplied in T73 temper.
c Thickness at the time of heat treatment.
d Rounded T99 values for T73 temper ≤1.000 in., Ftu=68 ksi, for Fty=57 ksi; 1.001-2.000 in., Ftu=68 ksi; 3.001-4.000 in., Ftu=66 ksi, for Fty=56 ksi.
e Rounded T99 for T7352 temper, Ftu<1.000 inch=67 ksi.
f When AMS-A-22771 or AMS-QQ-A-367 apply, T indicates any grain direction not within ±15° of being parallel to the forging flow lines. Fcy(T) values are based upon short transverse (ST) test data. When AMS 4141 applies, T indicates any grain direction within ±15° of being perpendicular to the forging flow lines.
g Specification value. T tensile properties are presented on an S basis only.
h Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.6.0(f1). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Hand Forging
SpecificationAMS 4126, AMS-A-22771, and AMS-QQ-A-367AMS-A-22771 and AMS-QQ-A-367
FormHand forging
TemperT6aT652
Thickness, in.≤2.0002.001-
3.000		3.001-
4.000		4.001-
5.000		5.001-
6.000		≤2.0002.001-
3.000		3.001-
4.000		4.001-
5.000		5.001-
6.000
BasisSSSSSSSSSS
Mechanical Properties:
Ftu, ksi:
L74737169687473716968
LT73717068667371706866
ST···69b68b66b65b···69b68b66b65b
Fty, ksi:
L63616058566361605856
LT61595856556159585655
ST···58b57b56b55b···57b56b55b54b
Fcy, ksi:
L6361·········6361·········
LT6159·········6159·········
Fsu, ksi44444341414444434141
Fbru, ksi:
(e/D = 1.5)······························
(e/D = 2.0)······························
Fbry, ksi:
(e/D = 1.5)······························
(e/D = 2.0)······························
e, percent:
L9987699876
LT4433344333
ST···3222···2111
E, 103 ksi10.0
Ec, 103 ksi10.4
G, 103 ksi3.8
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a When hand forgings are machined before heat treatment, the section thickness at time of heat treatment will determine the minimum mechanical properties as long as the original (as-forged) thickness does not exceed the maximum thickness of the alloy as shown in the table. The maximum cross-sectional area of hand forgings is 256 sq in.
b Caution: This specific alloy, temper, and product form exhibits poor stress-corrosion cracking resistance in this grain direction. It corresponds to an SCC resistance rating of D, as indicated in Table 3.1.2.3.1(a).
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Table 3.7.6.0(f2). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Hand Forging—Continued
SpecificationAMS-A-22771 and AMS-QQ-A-367AMS 4147, AMS-A-22771, and AMS-QQ-A-367
FormHand forging
TemperT73aT7352
Thickness, in.≤2.0002.001-
3.000		3.001-
4.000		4.001-
5.000		5.001-
6.000		≤2.0002.001-
3.000		3.001-
4.000		4.001-
5.000		5.001-
6.000
BasisSSSSSSSABSS
Mechanical Properties:
Ftu, ksi:
L6666646261666664676261
LT6464636159646463666159
ST···61605857···6160635857
Fty, ksi:
L5656555351545453555149
LT5454535150525250534846
ST···52515049···5048514644
Fcy, ksi:
L5656·········555552554946
LT5252·········555552554946
ST···············555553565149
Fsu, ksi:
L3939·········393938403736
LT3939·········363637383635
ST···············383837393635
Fbrub, ksi:
(e/D = 1.5)···············868889938684
(e/D = 2.0)···············120120118123114110
Fbryb, ksi:
(e/D = 1.5)···············717373777168
(e/D = 2.0)···············909087928380
e, percent (S-basis):
L77776777···76
LT44333443···33
ST···3222···2·········2
E, 103 ksi10.2
Ec, 103 ksi10.4
G, 103 ksi3.8
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a When hand forgings are machined before heat treatment, the section thickness at time of heat treatment will determine the minimum mechanical properties as long as the original (as-forged) thickness does not exceed the maximum thickness for the alloy as shown in the table. The maximum cross-sectional area of hand forgings is 256 sq in.
b Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.6.0(g1). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Extrusion
SpecificationAMS-QQ-A-200/11
FormExtrusion (rod, bar, and shapes)
TemperT6, T6510, T6511, and T62a
Cross-Sectional Area, in.2≤20>20, ≤32≤32
Thickness, in.b≤0.249≤0.2490.250-0.4990.250-0.4990.500-0.7490.500-0.7490.750-1.4990.750-1.4991.500-2.9991.500-2.9993.000-4.4993.000-4.4993.000-4.4994.500-5.0004.500-5.000
BasisABABABABABABSAB
Mechanical Properties:
Ftu, ksi:
L788281858185818581858184787881
LT757978827781757971756769646365
ST························67c71c67c69c64c63c65c
Fty, ksi:
L707473777276727672767174706871
LT667069726771656961655659555255
ST························56c59c55c58c55c52c55c
Fcy, ksi:
L707473777276727672767174706871
LT727674787377717567716264615760
ST························62666264615760
Fsu, ksi414443454345434542444042393840
Fbrud, ksi:
(e/D = 1.5)111117115121115120113119110115106110102101105
(e/D = 2.0)140148146153145152144151141148137142132131136
Fbryd, ksi:
(e/D = 1.5)9297961019499939889948488837983
(e/D = 2.0)10811411311911111711011610611210110510095100
e, percent (S-basis):
L7···7···7···7···7···7···66···
E, 103 ksi10.4
Ec, 103 ksi10.7
G, 103 ksi4.0
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a Design allowables were based upon data obtained from testing T6, T6510, and T6511 temper extrusions and from testing samples of extrusion supplied in the O or F temper, which were heat treated to T62 temper to demonstrate response to heat treatment by suppliers. Properties obtained by the user may be lower than those listed if the material has been formed or otherwise cold worked, particularly in the annealed temper, prior to solution heat treatment.
b The mechanical properties are to be based upon the thickness at the time of quench.
c Caution: This specific alloy, temper, and product form exhibits poor stress-corrosion cracking resistance in this grain direction. It corresponds to an SCC resistance rating of D, as indicated in Table 3.1.2.3.1(a).
d Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.6.0(g2). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Extrusion—Continued
SpecificationAMS-QQ-A-200/11
FormExtrusion (rod, bars, and shapes)
TemperT73a, T73510, T73511
Cross-Sectional Area, in.2≤20≤25≤20>20, <32
Thickness, in.b0.062-0.2490.062-0.2490.250-0.4990.250-0.4990.500-0.7490.500-0.7490.750-1.4990.750-1.4991.500-2.9991.500-2.9993.000-4.4993.000-4.4993.000-4.4993.000-4.499
BasisABABABABABABAB
Mechanical Properties:
Ftu, ksi:
L68c7270d7470d7370d7369d7468c7165e70
LT6670687267706669626758615660
Fty, ksi:
L586160636063606359d6557c6255c60
LT5659576057605658515646504448
Fcy, ksi:
L5861606060606063596557625560
LT5962636363635861545949534751
Fsu, ksi3739384038393839374037383538
Fbruf, ksi:
(e/D = 1.5)1011071041101031081031079910695999198
(e/D = 2.0)129137133141133139132138128138124130119128
Fbryf, ksi:
(e/D = 1.5)8286848984888387798772797076
(e/D = 2.0)97102100105100105981039310386948391
e, percent (S-basis):
L7···8···8···8···8···7···7···
E, 103 ksi10.4
Ec, 103 ksi10.7
G, 103 ksi4.0
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a Design allowables were based upon data obtained from testing T7351X temper extrusions and from testing samples of extrusions supplied in the O or F temper, which were heat treated to T73 temper to demonstrate response to treatment by suppliers. Properties obtained by the user may be lower than those listed if the material has been formed or otherwise cold worked, particularly in the annealed temper.
b The mechanical properties are to be based upon the thickness at the time of quench.
c S-basis. Rounded T99 values for cross sectional area <20 are as follows: for 0.062-0.249 Ftu(L) = 69 ksi, 3.000-4.499 Ftu(L) = 69 ksi, Fty(L) = 59 ksi.
d S-basis. Rounded T99 values for cross sectional area <25 are as follows: 0.250-1.499 Ftu(L) = 71, 1.500-2.999 Ftu(L) = 72 ksi and Fty(L) = 62 ksi.
e S-basis. Rounded T99 values for cross sectional area >20 and <32 are as follows: Ftu(L) = 68 ksi and Fty(L) = 57 ksi.
f Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.6.0(g3). Design Mechanical and Physical Properties of 7075 Aluminum Alloy Extrusion—Continued
SpecificationAMS-QQ-A-200/15
FormExtrusion (rod, bar, and shapes)
TemperT76, T76510, T76511
Cross-Sectional Area, in.2≤20
Thickness, in.a0.062-0.2490.250-0.4990.500-0.7490.750-1.000
BasisABSABAB
Mechanical Properties:
Ftu, ksi:
L71747575767576
LT68717271737071
Fty, ksi:
L61656565676567
LT57616160625961
Fcy, ksi:
L61656565676567
LT62666665676466
Fsu, ksi38404141424041
Fbrub, ksi:
(e/D = 1.5)103107109109110109110
(e/D = 2.0)131137139139141139141
Fbryb, ksi:
(e/D = 1.5)82888888908890
(e/D = 2.0)98104104104107104107
e, percent (S-basis):
L7···77···7···
E, 103 ksi10.4
Ec, 103 ksi10.7
G, 103 ksi4.0
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and αSee Figure 3.7.6.0
a The mechanical properties are to be based upon the thickness at the time of quench.
b Bearing values are “dry pin” values per Section 1.4.7.1.

The temper index for 7075 is: Section 3.7.6.1 covers the T6, T651, T652, T6510, and T6511 tempers; Section 3.7.6.2 covers the T73, T7351, T7352, T73510, and T73511 tempers.

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K

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α

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Figure 3.7.6.0. Effect of temperature on the physical properties of 7075 aluminum alloy.

3.7.6.1T6, T651, T652, T6510, T6511 Tempers

Figures 3.7.6.1.1(a) and (b) permit calculation of residual tensile strengths for complex thermal exposure conditions. They are based upon the rate parameter T(C + log t), in which T is exposure temperature in degrees Rankine, t is exposure time in hours, and C is a constant evaluated for each material. These curves have been verified for use only within the ranges of temperatures and exposure times covered in the figures. The following example illustrates their use.

Sample problem: Find Ftu at 250°F following a complex exposure of 300°F, 8 hours plus 350°F, 1 hour.

  1. Reduce given complex exposure by converting the 350°F exposure to an equivalent exposure time at 300°F.
    1. On the 350°F single-exposure-temperature line, find 350°F, 1 hour.
    2. From this point move vertically to the 300°F exposure-temperature line and then read right, 12 hours exposure.
    3. Total equivalent exposure time at 300°F is therefore 8 hours + 12 hours, or 20 hours.
  2. Find Ftu at 250°F following 300°F, 20 hours exposure:
    1. On the 300°F exposure-temperature line, find 300°F, 20 hours.
    2. From this point move vertically to the 250°F test-temperature curve and then read left, 76 percent Ftu.

Solution: Ftu is 76 percent of the original room-temperature Ftu. Fty is determined in like manner. Fcy can be closely estimated by using the percent reduction factor determined for Fty. For specific data, see Reference 3.7.6.1.

Stressed Thermal Exposure — Stress applied during simple and complex thermal exposure of 7075-T6 can have an additional effect in reducing material strength. However, the effect becomes significant only when exposure strains exceed 0.2 percent. For specific data, see Reference 3.7.6.1.

Figures 3.7.6.1.1(c) through 3.7.6.1.5(b) present elevated-temperature curves for various mechanical properties. Figures 3.7.6.1.6(a) through (m) present tensile and compressive stress-strain and tangent-modulus curves at several temperatures. Figures 3.7.6.1.6(n) through (q) are full-range stress-strain curves for various products. Figures 3.7.6.1.8(a) through (h) provide room-temperature fatigue curves for T6-temper products. Fatigue-crack-propagation data for sheet are presented in Figure 3.7.6.1.9. Graphical displays of the residual-strength behavior of middle-tension panels are presented in Figures 3.7.6.1.10(a) through (h).

Figure 3.7.6.1.1(a) Not digitized — see the usage notes in Section 3.7.6.1 (this figure carries no standalone plottable curve); skipped.

Figure 3.7.6.1.1(a). Effect of temperature on the tensile ultimate strength (Ftu) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).

Figure 3.7.6.1.1(b) Not digitized — see the usage notes in Section 3.7.6.1 (this figure carries no standalone plottable curve); skipped.

Figure 3.7.6.1.1(b). Effect of temperature on the tensile yield strength (Fty) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).

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Figure 3.7.6.1.1(c). Effect of temperature on the tensile ultimate strength (Ftu) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).

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Figure 3.7.6.1.1(d). Effect of temperature on the tensile yield strength (Fty) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).

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Figure 3.7.6.1.2(a). Effect of temperature on the compressive yield strength (Fcy) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).

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Figure 3.7.6.1.2(b). Effect of temperature on the shear ultimate strength (Fsu) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).

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Figure 3.7.6.1.3(a). Effect of temperature on the bearing ultimate strength (Fbru) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).

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Figure 3.7.6.1.3(b). Effect of temperature on the bearing yield strength (Fbry) of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products).

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Figure 3.7.6.1.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of 7075 aluminum alloy.

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Figure 3.7.6.1.5(a). Effect of temperature on the elongation of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products except thick extrusions).

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Figure 3.7.6.1.5(b). Effect of exposure at elevated temperatures on the elongation of 7075-T6, T651, T6510, and T6511 aluminum alloy (all products except thick extrusions).

Figures 3.7.6.1.6(a) through (q) present typical stress-strain and tangent-modulus curves for T6-family products and are not individually reproduced here; each figure corresponds to a specific product form, temper, test temperature, and (where applicable) thermal-exposure time. The run covers: clad 7075-T6 sheet, tensile and compressive stress-strain and tangent-modulus curves at room temperature through 600°F with exposures of 1/2, 2, 10, 100, and 1000 hours [(a) through (f)]; 7075-T651 and -T62 plate at room temperature [(g) through (i)]; 7075-T6/T651 rolled bar, rod, and shape at room temperature [(j)]; 7075-T651X and -T62 extrusion at room temperature [(k) through (m)]; and full-range (to-fracture) tensile stress-strain curves for clad T6 sheet, T6/T651 rolled bar, and T651X/T62 extrusion at room temperature [(n) through (q)]. See MIL-HDBK-5J pp. 3-395–3-405 for the individual curves.

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Figure 3.7.6.1.8(a). Best-fit S/N curves for unnotched 7075-T6 aluminum alloy, various product forms, longitudinal direction.

Correlative Information for Figure 3.7.6.1.8(a)

Product Form: 0.75 inch diam. drawn rod, 1.25 inch diam. rolled rod, 1 x 7.5 inch bar, extruded 1.25 inch bar and 1.25 inch rod

Properties: TUS 82 ksi, TYS 72 ksi, RT

Specimen Details: Unnotched, minimum diameter 0.200 inch

Surface Condition: Unspecified

Reference: 3.7.6.1.8

Test Parameters:
Loading – Axial
Frequency – 30 Hz
Temperature – RT
Environment – Air

No. of Heats/Lots: 8

Equivalent Stress Equation:
Log Nf = 18.22 − 7.77 log (Seq − 10.15)
Seq = Smax(1−R)0.62
Std. Error of Estimate, Log (Life) = 0.626
Standard Deviation, Log (Life) = 1.435
R2 = 81%

Sample Size: 130

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.6.1.8(b). Best-fit S/N curve for notched, Kt = 1.6, 7075-T6 aluminum alloy rolled bar, longitudinal direction.

Correlative Information for Figure 3.7.6.1.8(b)

Product Form: 1.125 inch diam. rolled bar

Properties: TUS 99.2 ksi, RT

Specimen Details: Notched, Kt = 1.6
Notch-root radius = 0.100 inch
Net test-section diameter = 0.400 inch
Gross diameter = 0.450 inch
60° groove

Surface Condition: Polished to 10 micro-inches

Reference: 3.2.1.1.8(b)

Test Parameters:
Loading – Axial
Frequency – 60 Hz
Temperature – RT
Atmosphere – Air

No. of Heats/Lots: 1

Equivalent Stress Equation:
Log Nf = 8.26 − 2.62 log (Seq − 15.3)
Seq = Smax(1−R)0.525
Std. Error of Estimate, Log (Life) = 0.418
Standard Deviation, Log (Life) = 0.985
R2 = 82%

Sample Size: 34

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.6.1.8(c). Best-fit S/N curves for notched, Kt = 3.4, 7075-T6 aluminum alloy rolled bar, longitudinal direction.

Correlative Information for Figure 3.7.6.1.8(c)

Product Form: 1.125 inch diam. rolled bar

Properties: TUS 96.5 ksi, RT

Specimen Details: Notched, Kt = 3.4
Notch-root radius = 0.010 inch
Net test-section diameter = 0.400 inch
Gross diameter = 0.450 inch
60° groove

Surface Condition: Polished to 10 micro-inches

Reference: 3.2.1.1.8(b)

Test Parameters:
Loading – Axial
Frequency – 60 Hz
Temperature – RT
Atmosphere – Air

No. of Heats/Lots: 1

Equivalent Stress Equation:
Log Nf = 9.19 − 3.646 log (Seq − 5.36)
Seq = Smax(1−R)0.386
Std. Error of Estimate, Log (Life) = 0.282
Standard Deviation, Log (Life) = 0.782
R2 = 87%

Sample Size: 48

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.6.1.8(d). Best-fit S/N curves for unnotched 7075-T6 aluminum alloy sheet, longitudinal direction.

Stresses are based on net section.

Correlative Information for Figure 3.7.6.1.8(d)

Product Form: Bare sheet, 0.090 inch

Properties: TUS 82 ksi, TYS 76 ksi, RT

Specimen Details: Unnotched, 0.5 to 1.0 inch width

Surface Condition: Electropolished, 150 grit emery paper

References: 3.2.3.1.8(a) and (f)

Test Parameters:
Loading – Axial
Frequency – 300 to 1800 cpm
Environment – Air

No. of Heats/Lots: Not specified

Equivalent Stress Equation:
Log Nf = 14.86 − 5.80 log (Seq)
Seq = Smax(1−R)0.49
Std. Error of Estimate, Log (Life) = 0.41
Standard Deviation, Log (Life) = 0.92
R2 = 80%

Sample Size: 176

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.6.1.8(e). Best-fit S/N curves for notched, Kt = 1.5, 7075-T6 aluminum alloy sheet, longitudinal direction.

Correlative Information for Figure 3.7.6.1.8(e)

Product Form: Bare sheet, 0.090 inch

Properties: Unnotched TUS 82 ksi, TYS 76 ksi, RT; Notched TUS 87 ksi, RT

Specimen Details: Edge notched
3.000 inch gross width
1.500 inch net width
0.760 inch notch radius
60° flank angle

Surface Condition: Electropolished

Reference: 3.2.3.1.8(d)

Test Parameters:
Loading – Axial
Frequency – 1100 to 1500 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: Not specified

Equivalent Stress Equation:
Log Nf = 9.54 − 3.52 log (Seq − 18.7)
Seq = Smax(1−R)0.49
Std. Error of Estimate, Log (Life) = 0.41
Standard Deviation, Log (Life) = 1.00
R2 = 83%

Sample Size: 30

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.6.1.8(f). Best-fit S/N curves for notched, Kt = 2.0, 7075-T6 aluminum alloy sheet, longitudinal direction.

Correlative Information for Figure 3.7.6.1.8(f)

Product Form: Bare sheet, 0.090 inch

Properties: Unnotched TUS 82 ksi, TYS 76 ksi, RT; Notched TUS 88 ksi, RT

Specimen Details: Notched – center (4.50 in. gross / 1.50 in. net / 1.50 in. notch radius), edge (2.25 in. gross / 1.50 in. net / 0.3175 in. notch radius), and fillet (2.25 in. gross / 1.50 in. net / 0.1736 in. notch radius)

Surface Condition: Electropolished

References: 3.2.3.1.8(b) and (f)

Test Parameters:
Loading – Axial
Frequency – 1100 to 1500 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: Not specified

Equivalent Stress Equation:
Log Nf = 7.50 − 2.46 log (Seq − 18.6)
Seq = Smax(1−R)0.54
Std. Error of Estimate, Log (Life) = 0.31
Standard Deviation, Log (Life) = 0.85
R2 = 87%

Sample Size: 112

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.6.1.8(g). Best-fit S/N curves for notched, Kt = 4.0, 7075-T6 aluminum alloy sheet, longitudinal direction.

Correlative Information for Figure 3.7.6.1.8(g)

Product Form: Bare sheet, 0.090 inch

Properties: Unnotched TUS 82 ksi, TYS 76 ksi, RT; Notched TUS 82 ksi, RT

Specimen Details: Notched – edge (2.25 in. gross / 1.500 in. net / 0.057 in. notch radius; 4.10 in. gross / 1.500 in. net / 0.070 in. notch radius) and fillet (2.25 in. gross / 1.500 in. net / 0.0195 in. notch radius)

Surface Condition: Electropolished

References: 3.2.3.1.8(b), (f), (g), and (h)

Test Parameters:
Loading – Axial
Frequency – 1100 to 1800 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: Not specified

Equivalent Stress Equation:
Log Nf = 10.2 − 4.63 log (Seq − 5.3)
Seq = Smax(1−R)0.51
Std. Error of Estimate, Log (Life) = 0.51
Standard Deviation, Log (Life) = 1.08
R2 = 78%

Sample Size: 126

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.6.1.8(h). Best-fit S/N curves for notched, Kt = 5.0, 7075-T6 aluminum alloy sheet, longitudinal direction.

Stresses are based on net section.

Correlative Information for Figure 3.7.6.1.8(h)

Product Form: Bare sheet, 0.090 inch

Properties: Unnotched TUS 82 ksi, TYS 76 ksi, RT; Notched TUS 77 ksi, RT

Specimen Details: Edge notched
2.25 inch gross width
1.500 inch net width
0.03125 inch notch radius

Surface Condition: Electropolished

Reference: 3.2.3.1.8(c)

Test Parameters:
Loading – Axial
Frequency – 1100 to 1500 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: Not specified

Equivalent Stress Equation:
Log Nf = 7.51 − 2.92 log (Seq − 6.7)
Seq = Smax(1−R)0.58
Std. Error of Estimate, Log (Life) = 0.23
Standard Deviation, Log (Life) = 1.08
R2 = 95%

Sample Size: 37

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.6.1.9. Fatigue-crack-propagation data for 0.090-inch-thick 7075-T6 aluminum alloy sheet with buckling restraint.

Specimen and Test Details for Figure 3.7.6.1.9

Specimen Thickness: 0.090 inch

Specimen Width: 1-1/2 to 12 inches

Specimen Type: M(T)

Environment: Lab air

Temperature: RT

Orientation: L-T

References: 3.7.6.1.9(a) through (e)

Figures 3.7.6.1.10(a) through (h) present the residual-strength behavior of 7075-T6 middle-tension panels for a range of sheet, clad-sheet, and plate thicknesses and crack orientations, summarized below.

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Figure 3.7.6.1.10(a). Residual-strength behavior of 0.063-inch-thick 7075-T6 aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.10(b). Residual-strength behavior of 0.063-inch-thick 7075-T6 aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.10(c). Residual-strength behavior of 0.090and 0.100-inch-thick 7075-T6 aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.10(d). Residual-strength behavior of 0.100-inch-thick 7075-T6 aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.10(e). Residual-strength behavior of 0.313-inch-thick 7075-T6 aluminum alloy plate at room temperature.

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Figure 3.7.6.1.10(f). Residual-strength behavior of 0.040-inch-thick 7075-T6 clad aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.10(g). Residual-strength behavior of 0.080-inch-thick 7075-T6 clad aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.10(h). Residual-strength behavior of 0.090-inch-thick 7075-T6 clad aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.6(a). Typical tensile and compressive stress-strain and compressive tangent-modulus curves for clad 7075-T6 aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7075-T6 aluminum alloy sheet at 200°F.

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Figure 3.7.6.1.6(c). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7075-T6 aluminum alloy sheet at 300°F.

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Figure 3.7.6.1.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7075-T6 aluminum alloy sheet at 400°F.

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Figure 3.7.6.1.6(e). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7075-T6 aluminum alloy sheet at 500°F.

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Figure 3.7.6.1.6(f). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7075-T6 aluminum alloy sheet at 600°F.

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Figure 3.7.6.1.6(g). Typical tensile stress-strain curves for 7075-T651 aluminum alloy plate at room temperature.

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Figure 3.7.6.1.6(h). Typical compressive stress-strain and compressive tangent-modulus curves for 7075-T651 aluminum alloy plate at room temperature.

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Figure 3.7.6.1.6(i). Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7075-T62 aluminum alloy plate at room temperature.

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Figure 3.7.6.1.6(j). Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7075-T6 and T651 aluminum alloy rolled-bar, rod, and shape at room temperature.

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Figure 3.7.6.1.6(k). Typical tensile stress-strain curves for 7075-T651X aluminum alloy extrusion at room temperature.

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Figure 3.7.6.1.6(l). Typical compressive stress-strain and compressive tangent-modulus curve for 7075-T651X aluminum alloy extrusion at room temperature.

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Figure 3.7.6.1.6(m). Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7075-T62 aluminum alloy extrusion at room temperature.

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Figure 3.7.6.1.6(n). Typical tensile stress-strain curve (full range) for clad 7075-T6 aluminum alloy sheet at room temperature.

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Figure 3.7.6.1.6(o). Typical tensile stress-strain curve (full range) for 7075-T6 and T651 aluminum alloy rolled or cold-finished bar at room temperature.

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Figure 3.7.6.1.6(p). Typical tensile stress-strain curves (full range) for 7075-T651X aluminum alloy extrusion at room temperature.

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Figure 3.7.6.1.6(q). Typical tensile stress-strain curves (full range) for 7075-T62 aluminum alloy extrusion at room temperature.

3.7.6.2T73, T7351, T7352, T73510, T73511 Tempers

Figures 3.7.6.2.6(a) through (d) present stress-strain and tangent-modulus curves for various products and tempers. Figures 3.7.6.2.6(e) and (f) are full-range stress-strain curves at room temperature for extrusion. Fatigue-crack-propagation data for plate are presented in Figures 3.7.6.2.9(a) through (c). Graphical displays of the residual-strength behavior of middle-tension panels are presented in Figures 3.7.6.2.10(a) and (b).

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Figure 3.7.6.2.6(a). Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7075-T73 aluminum alloy extrusion at room temperature.

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Figure 3.7.6.2.6(b). Typical tensile and compressive stress-strain and compressive tangent-modulus curves for 7075-T7351X aluminum alloy extrusion at room temperature.

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Figure 3.7.6.2.6(c). Typical tensile stress-strain curves for 7075-T7352 aluminum alloy hand forging at room temperature.

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Figure 3.7.6.2.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 7075-T7352 aluminum alloy hand forging at room temperature.

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Figure 3.7.6.2.6(e). Typical tensile stress-strain curves (full range) for 7075-T7351X aluminum alloy extrusion at room temperature.

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Figure 3.7.6.2.6(f). Typical tensile stress-strain curves (full range) for 7075-T73 aluminum alloy extrusion at room temperature.

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Figure 3.7.6.2.9(a). Fatigue-crack-propagation data for 0.250-inch-thick 7075-T7351 aluminum alloy plate with buckling restraint.

Specimen and Test Details for Figure 3.7.6.2.9(a)

Specimen Thickness: 0.250 inch

Specimen Width: 8, 16, 36 inches

Specimen Type: M(T)

Environment: 50% R.H.

Temperature: RT

Orientation: L-T

References: 3.2.5.1.9(d) and 3.7.6.2.9(a)
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Figure 3.7.6.2.9(b). Fatigue-crack-propagation data for 0.500-inch-thick 7075-T7351 aluminum alloy plate with buckling restraint.

Specimen and Test Details for Figure 3.7.6.2.9(b)

Specimen Thickness: 0.475 to 0.500 inch

Specimen Width: 6, 8, 16, 36 inches

Specimen Type: M(T)

Environment: 50–95% R.H.

Temperature: RT

Orientation: L-T

References: 3.1.2.1.6(j) and 3.7.6.2.9(a) through (c)
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Figure 3.7.6.2.9(c). Fatigue-crack-propagation data for 1.00-inch-thick 7075-T7351 aluminum alloy plate without buckling restraint.

Specimen and Test Details for Figure 3.7.6.2.9(c)

Specimen Thickness: 1.00 inch

Specimen Width: 6, 8, 16, 36 inches

Specimen Type: M(T), C(T)

Environment: 50% R.H.

Temperature: RT

Orientation: L-T

References: 3.2.5.1.9(d) and 3.7.6.2.9(a) and (b)
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Figure 3.7.6.2.10(a). Residual-strength behavior of 0.600-inch-thick 7075-T7351 aluminum alloy plate at room temperature.

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Figure 3.7.6.2.10(b). Residual-strength behavior of 1.00-inch-thick 7075-T7351 aluminum alloy plate at room temperature.

3.7.77150 Alloy
3.7.7.0Comments and Properties

7150, a second-generation version of 7050, is an Al-Zn-Mg-Cu-Zr alloy developed to provide higher strength properties than 7050 in thicknesses through 3 inches. 7150 is available in the form of plate and extrusion. The T61-type temper provides high strength with guaranteed levels of fracture toughness for plate. The T77-type temper provides high strength with guaranteed toughness and corrosion resistance. The T77-type temper has exfoliation and stress-corrosion resistance comparable to the T76-type temper of the other 7000 series aluminum alloys. Refer to Section 3.1.2.3 for further comments regarding resistance of the alloy to stress-corrosion cracking.

The properties of extrusions should be based upon the thickness at the time of quenching prior to machining. Selection of the mechanical properties based upon its final machined thickness may be unconservative; therefore, the thickness at the time of quenching to achieve properties is an important factor in the selection of the proper thickness column. For extrusions having sections with various thicknesses, consideration should be given to the properties as a function of thickness.

Refer to Section 3.1.3.4 for comments regarding the weldability of the alloy.

Material specifications for 7150 are shown in Table 3.7.7.0(a). Room-temperature mechanical properties are presented in Tables 3.7.7.0(b1) through (c2).

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Table 3.7.7.0(a). Material Specifications for 7150 Aluminum Alloy
SpecificationForm
AMS 4306Bare plate
AMS 4252Bare plate
AMS 4307Extrusion
AMS 4345Extrusion
Temper Index for 7150 Alloy
SectionTemper
3.7.7.1T6151 and T61511
3.7.7.2T7751 and T77511
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Table 3.7.7.0(b1). Design Mechanical and Physical Properties of 7150 Plate
SpecificationAMS 4306
FormPlate
TemperT6151
Thickness, in.0.750-1.0001.001-1.500
BasisABAB
Mechanical Properties:
Ftu, ksi:
L85878687
LT84878586
Fty, ksi:
L79818081
LT77797678
Fcy, ksi:
L77807577
LT81838082
Fsu, ksi45474646
Fbrua, ksi:
(e/D = 1.5)121125123124
(e/D = 2.0)155160156158
Fbrya, ksi:
(e/D = 1.5)102105101104
(e/D = 2.0)119122118121
e, percent (S-basis):
L9···9···
LT9···9···
E, 103 ksi10.2
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, Btu/(lb)(°F)···
a Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
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Table 3.7.7.0(b2). Design Mechanical and Physical Properties of 7150 Plate
SpecificationAMS 4252
FormPlate
TemperT7751
Thickness, in.0.250-0.4990.500-0.7490.750-1.5001.501-3.000
BasisSSSAB
Mechanical Properties:
Ftu, ksi:
L8083848284
LT80838482a84
ST·········77a81
Fty, ksi:
L7477787678
LT74767775a77
ST·········67a71
Fcy, ksi:
L7476777577
LT7779817982
Fsu, ksi4647484748
Fbrub, ksi:
(e/D = 1.5)119124125122125
(e/D = 2.0)154160162158162
Fbryb, ksi:
(e/D = 1.5)102105106104108
(e/D = 2.0)117120121118123
e, percent: (S-basis)
L8887···
LT8886···
ST·········1···
E, 103 ksi10.3
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.102
C, K, and α···
a S-basis values. The rounded T99 values are as follows: Ftu(LT) = 83 ksi, Ftu(ST) = 78 ksi, Fty(LT) = 76 ksi, Fty(ST) = 68 ksi.
b Bearing values are “dry pin” values per Section 1.4.7.1. See Table 3.1.2.1.1.
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Table 3.7.7.0(c1). Design Mechanical and Physical Properties of 7150 Aluminum Alloy Extrusion
SpecificationAMS 4307
FormExtrusion
TemperT61511
Thickness or Diameter,a in0.250-
0.499		0.500-
0.749		0.750-
0.999		1.000-
1.499		1.500-
2.000
BasisSSSABS
Mechanical Properties:
Ftu, ksi:
L878889899489
LT807979858674
Fty, ksi:
L828384838884
LT737373777868
Fcy, ksi:
L808182828784
LT808080778175
Fsu, ksi444545444642
Fbrub, ksi:
(e/D = 1.5)119120120118125116
(e/D = 2.0)152153154152161150
Fbryb, ksi:
(e/D = 1.5)1001001009610294
(e/D = 2.0)118120120117124117
e, percent (S-basis):
L8988···8
E, 103 ksi10.4
Ec, 103 ksi11.0
G, 103 ksi4.0
μ0.33
Physical Properties:
ω, lb/in.30.102
C, K, and α···
a The mechanical properties are to be based upon the thickness at the time of quench.
b Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.7.0(c2). Design Mechanical and Physical Properties of 7150 Aluminum Alloy Extrusion
SpecificationAMS 4345
FormExtrusion
TemperT77511
Cross-Sectional Area, in2≤20
Thickness or Diameter,a in.≤0.2490.250-0.4990.500-0.7490.750-2.000
BasisABABSS
Mechanical Properties:
Ftu, ksi:
L85b8887c898889
LT818482c868383
Fty, ksi:
L78b8382c848384
LT747976c797978
Fcy, ksi:
L78b8282c858384
LT768180828182
Fsu, ksi444645464646
Fbrud, ksi:
(e/D = 1.5)122126124127125123
(e/D = 2.0)158163161165162159
Fbryd, ksi:
(e/D = 1.5)100106105108106108
(e/D = 2.0)118125124127125127
e, percent (S-Basis):
L7···8···98
E, 103 ksi10.4
Ec, 103 ksi10.9
G, 103 ksi4.0
μ0.33
Physical Properties:
ω, lb/in.30.102
C, K, and α···
a The mechanical properties are to be based upon the thickness at the time of quench.
b S basis. The rounded T99 values are Ftu(L) = 87 ksi, Fty(L) = 81 ksi, and for Fcy(L) = 79 ksi.
c S basis. The rounded T99 values are Ftu(L) = 88 ksi, Ftu(LT) = 84 ksi, Fty(L) = 82 ksi, Fty(LT) = 77 ksi, and for Fcy(L) = 82 ksi.
d Bearing values are “dry pin” values per Section 1.4.7.1.
3.7.7.1T6151 and T61511 Tempers

Figures 3.7.7.1.6(a) and (b) present stress-strain and tangent-modulus curves for bare plate. Figures 3.7.7.1.6(c) and (d) depict stress-strain and tangent-modulus curves for extrusion.

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Figure 3.7.7.1.6(a). Typical tensile stress-strain curves for 7150-T6151 aluminum alloy plate at room temperature (thickness 0.750–1.000 in.).

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Figure 3.7.7.1.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7150-T6151 aluminum alloy plate at room temperature (thickness 0.750–1.000 in.).

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Figure 3.7.7.1.6(c). Typical tensile stress-strain curves for 7150-T61511 aluminum alloy extrusion at room temperature (thickness 0.800–2.750 in.).

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Figure 3.7.7.1.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 7150-T61511 aluminum alloy extrusion at room temperature (thickness 0.800–2.750 in.).

3.7.7.2T7751 and T77511 Tempers

Figures 3.7.7.2.6(a) and (b) present stress-strain and tangent-modulus curves for bare plate. Figures 3.7.7.2.6(c) and (d) depict stress-strain and tangent-modulus curves for extrusion. Figures 3.7.7.2.8(a) through (c) present best-fit S/N fatigue curves for unnotched and notched (Kt = 3.0) 7150-T77511 extrusion.

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Figure 3.7.7.2.6(a). Typical tensile stress-strain curves for 7150-T7751 aluminum alloy plate at room temperature (thickness 0.340–1.875 in.).

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Figure 3.7.7.2.6(b). Typical compressive stress-strain and tangent-modulus curves for 7150-T7751 aluminum alloy plate at room temperature (thickness 0.340–1.875 in.).

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Figure 3.7.7.2.6(c). Typical tensile stress-strain curves for 7150-T77511 aluminum alloy extrusion at room temperature (thickness 0.700–1.145 in.).

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Figure 3.7.7.2.6(d). Typical compressive stress-strain and tangent-modulus curves for 7150-T77511 aluminum alloy extrusion (thickness 0.700–1.145 in.).

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Figure 3.7.7.2.8(a). Best-fit S/N curves for unnotched 7150-T77511 aluminum alloy extrusion, longitudinal orientation.

Correlative Information for Figure 3.7.7.2.8(a)

Product Forms: Extruded shape, 1.125 inch, 1.45 inch

Properties: TUS 89 ksi, TYS 84 ksi, RT

Specimen Details:
Unnotched
Round, 0.3 inch diameter, removed from center of section

Surface Condition: Polished to 10 micro-inch or better

Reference: 3.7.7.2.8

Test Parameters:
Loading – Axial
Frequency – 25 Hz
Temperature – RT
Environment – Air

No. of Heats/Lots: 2

Fatigue Life Equation:
Log Nf = 21.89 − 9.32 log (Smax)
Std. Error of Estimate, Log (Life) = 0.321
Standard Deviation, Log (Life) = 0.753
R2 = 81.8%

Sample Size: 16
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Figure 3.7.7.2.8(b). Best-fit S/N curves for unnotched 7150-T77511 aluminum alloy extrusion, long transverse orientation.

Correlative Information for Figure 3.7.7.2.8(b)

Product Forms: Extruded shape, 1.125 inch, 1.45 inch

Properties: TUS 83 ksi, TYS 78 ksi, RT

Specimen Details:
Unnotched
Round, 0.3 inch diameter, removed from center of section

Surface Condition: Polished to 10 micro-inch or better

Reference: 3.7.7.2.8

Test Parameters:
Loading – Axial
Frequency – 25 Hz
Temperature – RT
Environment – Air

No. of Heats/Lots: 2

Fatigue Life Equation:
Log Nf = 17.98 − 7.57 log (Smax)
Std. Error of Estimate, Log (Life) = 22.53(1/Smax)
Standard Deviation, Log (Life) = 0.977
R2 = 74.4%

Sample Size: 10
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Figure 3.7.7.2.8(c). Best-fit S/N curves for notched, Kt = 3.0, 7150-T77511 aluminum alloy extrusion, longitudinal and long transverse orientations.

Correlative Information for Figure 3.7.7.2.8(c)

Product Forms: Extruded shape, 1.125 inch, 1.45 inch

Properties: Longitudinal — TUS 89 ksi, TYS 84 ksi, RT; Long Transverse — TUS 83 ksi, TYS 78 ksi, RT

Specimen Details:
Circumferentially notched, Kt = 3.0 round
0.253 inch net diameter
0.013 inch root radius, removed from center of section

Surface Condition: Notch

Reference: 3.7.7.2.8

Test Parameters:
Loading – Axial
Frequency – 25 Hz
Temperature – RT
Environment – Air

No. of Heats/Lots: 2

Fatigue Life Equation:
Log Nf = 5.71 − 1.31 log (Smax − 16.92)
Std. Error of Estimate, Log (Life) = 4.51(1/Smax)
Standard Deviation, Log (Life) = 0.750
R2 = 92.4%

Sample Size: 25
3.7.87175 Alloy
3.7.8.0Comments and Properties

7175 is a high-purity, high-strength Al-Zn-Mg-Cu alloy. In the form of die forgings the alloy is available in the T66, T74, and T7452 tempers. Die forgings of 7175-T66 develop higher static strength than 7075-T6 forgings, with fatigue, fracture, and stress-corrosion properties about equivalent to those of 7075-T6 forgings. 7175-T74-type die and hand forgings develop static strengths about equivalent to those of 7075-T6 forgings, with toughness and fatigue properties equal or superior to those of 7075-T73 forgings. The T74-type temper provides stress-corrosion resistance and strength characteristics intermediate to those of T76 and T73 in 7075. Refer to Section 3.1.2.3 for comments regarding the resistance of the alloy to stress-corrosion cracking, and to Section 3.1.3.4 for comments regarding the weldability of the alloy.

The properties of extrusions should be based upon the thickness at the time of quenching prior to machining. Selection of the mechanical properties based upon final machined thickness may be unconservative; the thickness at the time of quenching to achieve properties is an important factor in the selection of the proper thickness column. For extrusions having sections with various thicknesses, consideration should be given to the properties as a function of thickness.

Material specifications for 7175 are presented in Table 3.7.8.0(a). Room-temperature mechanical and physical properties are shown in Tables 3.7.8.0(b) through (d).

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Table 3.7.8.0(a). Material Specifications for 7175 Aluminum Alloy
SpecificationForm
AMS 4148Die forging
AMS 4149Die and hand forging
AMS 4179Hand forging
AMS-A-22771Forging
AMS 4344Extrusion
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Table 3.7.8.0(b). Design Mechanical and Physical Properties of 7175 Aluminum Alloy Die Forging
SpecificationAMS 4148AMS 4149
FormDie forging
TemperT66T74a,b
Thickness, in.≤3.000<1.0001.001-
2.000		1.001-
2.000		2.001-
3.000		3.001-
4.000		4.001-
5.000		5.001-
6.000
BasisSSABSSSS
Mechanical Properties:
Ftu, ksi:
L8676747776737068
Tc777171d···71706865
Fty, ksi:
L7666646766636158
Tc666262d···62605855
Fcy, ksi:
L···6765686763······
ST···63616463·········
Fsu, ksi···43424443·········
Fbrue, ksi:
(e/D = 1.5)···106105109106·········
(e/D = 2.0)···140137142140·········
Fbrye, ksi:
(e/D = 1.5)···86848886·········
(e/D = 2.0)···10299103102·········
e, percent (S-basis):
L777···7777
Tc444···4444
E, 103 ksi10.2
Ec, 103 ksi10.7
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.101
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]76 (at 77°F for T66); 90 (at 77°F for T736)
α, 10-6 in./in./°F12.9 (68 to 212°F)
a When die forgings are machined before heat treatment, section thickness at time of heat treatment will determine minimum mechanical properties as long as original (as-forged) thickness does not exceed maximum thickness for the alloy as shown in the table.
b Design allowables were based upon data obtained from testing die forgings, heat treated by suppliers, and supplied in T74 temper.
c T indicates any grain direction not within ±15° of being parallel to the forging flow lines. Fcy(T) values are based upon short transverse (ST) test data.
d Specification value. T tensile properties are presented on an S basis only.
e Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.8.0(c1). Design Mechanical and Physical Properties of 7175 Aluminum Alloy Hand Forging
SpecificationAMS 4149 and AMS-A-22771
FormHand forging
TemperT74
Thickness or Diametera,b, in.1.001-
2.000		2.001-
3.000		3.001-
4.000		4.001-
5.000		5.001-
6.000
BasisSSSSS
Mechanical Properties:
Ftu, ksi:
L7373716865
LT7171706764
ST···69686663
Fty, ksi:
L6363615754
LT6060585652
ST···60575552
Fcy, ksi:
L6363615955
LT6263616056
ST6162605955
Fsu, ksi:
L4343434139
LT4242413938
ST4242413938
Fbruc, ksi:
(e/D = 1.5)10610610410095
(e/D = 2.0)138138136131125
Fbryc, ksi:
(e/D = 1.5)7378808176
(e/D = 2.0)8994959590
e, percent:
L99988
LT55555
ST···4444
E, 103 ksi10.2
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.101
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]90 (at 77°F)
α, 10-6 in./in./°F12.9 (68 to 212°F)
a When hand forgings are machined before heat treatment, the section thickness at time of heat treatment will determine the minimum mechanical properties as long as the original (as-forged) thickness does not exceed the maximum thickness for the alloy as shown in the table.
b The maximum cross-sectional area of hand forgings is 256 sq. in.
c Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.8.0(c2). Design Mechanical and Physical Properties of 7175 Aluminum Alloy Hand Forging
SpecificationAMS 4149 and AMS-A-22771
FormHand forging
TemperT7452
Thickness or Diametera, in.1.001-
2.000		2.001-
3.000		3.001-
4.000		4.001-
5.000		5.001-
6.000
BasisSSSSS
Mechanical Properties:
Ftu, ksi:
L7171686563
LT6969676461
ST···67656360
Fty, ksi:
L6161575451
LT5858555249
ST···54514946
Fcy, ksi:
L5858555249
LT6161575450
ST6060575451
Fsu, ksi:
L3839393837
LT3839383836
ST4041403938
Fbrub, ksi:
(e/D = 1.5)102102999590
(e/D = 2.0)133133130124118
Fbryb, ksi:
(e/D = 1.5)8082807672
(e/D = 2.0)9598959287
e, percent:
L99988
LT55555
ST···4444
E, 103 ksi10.2
Ec, 103 ksi10.5
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.101
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]90 (at 77°F)
α, 10-6 in./in./°F12.9 (68 to 212°F)
a The maximum cross-sectional area of hand forgings is 256 sq. in.
b Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.8.0(d). Design Mechanical and Physical Properties of 7175 Aluminum Alloy Extrusion
SpecificationAMS 4344
FormExtrusion
ConditionT73511
Cross-Sectional Area, in232-65
Thickness or Diameter,a in.0.250-0.9991.000-2.000
BasisSS
Mechanical Properties:
Ftu, ksi:
L6969
LT6363
Fty, ksi:
L5959
LT5252
Fcy, ksi:
L···59
LT···59
Fsu, ksi···40
Fbrub, ksi:
(e/D = 1.5)···97
(e/D = 2.0)···125
Fbryb, ksi:
(e/D = 1.5)···79
(e/D = 2.0)···95
e, percent:
L···8
LT···4
E, 103 ksi10.1
Ec, 103 ksi10.5
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.101
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]···
α, 10-6 in./in./°F12.9 (68 to 212°F)
a The mechanical properties are to be based upon the thickness at the time of quench.
b Bearing values are “dry pin” values per Section 1.4.7.1.

The temper index for 7175 is: Section 3.7.8.1 covers the T73511 temper (extrusion); Section 3.7.8.2 covers the T74 and T7452 tempers (formerly designated T736 and T73652, die and hand forging).

3.7.8.1T73511 Temper

Figures 3.7.8.1.6(a) and (b) show tensile and compressive stress-strain and tangent-modulus curves for 7175-T73511 extrusion at room temperature. Figures 3.7.8.1.8(a) through (d) present best-fit S/N fatigue curves — unnotched and notched (Kt = 3.0, 5.0, and 7.0) — for extrusion in the longitudinal direction.

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Figure 3.7.8.1.6(a). Typical tensile stress-strain curves for aluminum alloy 7175-T73511 extrusion at room temperature.

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Figure 3.7.8.1.6(b). Typical compressive stress-strain and tangent-modulus curves for aluminum alloy 7175-T73511 extrusion at room temperature.

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Figure 3.7.8.1.8(a). Best-fit S/N curves for unnotched 7175-T73511 alloy extrusion, longitudinal direction.

Correlative Information for Figure 3.7.8.1.8(a)

Product Form: Extrusion 1.8 inch thick, extruded round, 3.75 inch diameter, extruded rectangle, 2.5 × 5 inch thick, extrusion, unspecified size

Properties: TUS 76 ksi, TYS 67 ksi, 70°F

Specimen Details:
0.25 inch minimum diameter hourglass gage section
30 inch diameter

Surface Condition: 32 RMS gage section specified

References: 3.7.8.1.8(a), (b), and (c)

Test Parameters:
Loading – Axial
Frequency – Not specified
Temperature – 70°F
Environment – Air

No. of Heats/Lots: 11

Equivalent Stress Equation:
Log Nf = 12.01 − 5.26 log (Seq)
Seq = Sa + 0.32Sm − 15.04
Std. Error of Estimate, Log (Life) = 18.44(1/Seq)
Standard Deviation, Log (Life) = 1.35
R2 = 58%

Sample Size: 96

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.8.1.8(b). Best-fit S/N curves for notched, Kt = 3.0, 7175-T73511 alloy extrusion, longitudinal direction.

Correlative Information for Figure 3.7.8.1.8(b)

Product Form: Extrusion 1.8 inch thick, extruded round, 3.75 inch diameter, extruded rectangle, 2.5 × 5 inch thick, extrusion, unspecified size

Properties: TUS 76 ksi, TYS 67 ksi, 70°F

Specimen Details:
Circumferential notch, Kt = 3
0.50 inch gross diameter
0.36 inch net diameter
0.0005 inch notch radius
Circumferential 60° V notch

References: 3.7.8.1.8(a), (b), and (c)

Test Parameters:
Loading – Axial
Frequency – Not specified
Temperature – 70°F
Environment – Air

No. of Heats/Lots: 11

Equivalent Stress Equation:
Log Nf = 6.50 − 2.25 log (Seq)
Seq = Sa + 0.20Sm − 7.21
Std. Error of Estimate, Log (Life) = 3.92(1/Seq)
Standard Deviation, Log (Life) = 1.51
R2 = 91%

Sample Size: 86

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.8.1.8(c). Best-fit S/N curves for notched, Kt = 5.0, 7175-T73511 alloy extrusion, longitudinal direction.

Correlative Information for Figure 3.7.8.1.8(c)

Product Form: Extrusion 1.8 inch thick

Properties: TUS 76 ksi, TYS 67 ksi, 70°F

Specimen Details:
Circumferential notch, Kt = 5
0.50 inch gross diameter
0.36 inch net diameter
0.0005 inch notch radius

References: 3.7.8.1.8(a) and (b)

Test Parameters:
Loading – Axial
Frequency – Not specified
Temperature – 70°F
Environment – Air

No. of Heats/Lots: 10

Equivalent Stress Equation:
Log Nf = 7.63 − 2.78 log (Seq − 7.3)
Seq = Smax(1−R)0.56
Std. Error of Estimate, Log (Life) = 3.71(1/Seq)
Standard Deviation, Log (Life) = 1.45
R2 = 90%

Sample Size: 136

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.8.1.8(d). Best-fit S/N curves for notched, Kt = 7.0, 7175-T73511 alloy extrusion, longitudinal direction.

Correlative Information for Figure 3.7.8.1.8(d)

Product Form: Extrusion 1.8 inch thick

Properties: TUS 76 ksi, TYS 67 ksi, 70°F

Specimen Details:
Circumferential notch, Kt = 7
0.50 inch gross diameter
0.36 inch net diameter
0.0005 inch notch radius

References: 3.7.8.1.8(a) and (b)

Test Parameters:
Loading – Axial
Frequency – Not specified
Temperature – 70°F
Environment – Air

No. of Heats/Lots: 9

Equivalent Stress Equation:
Log Nf = 7.15 − 2.78 log (Seq)
Seq = Sa + 0.27Sm − 2.88
Std. Error of Estimate, Log (Life) = 0.11 + 1.60(1/Seq)
Standard Deviation, Log (Life) = 1.55
R2 = 92%

Sample Size: 63

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
3.7.8.2T74 and T7452 Tempers

Figures 3.7.8.2.6(a) through (f) present tensile and compressive stress-strain and tangent-modulus curves for 7175-T74 die forging and 7175-T74/T7452 hand forging at room temperature, for thicknesses ranging up to 6 inches. Figures 3.7.8.2.8(a) and (b) present best-fit S/N fatigue curves for die and hand forging.

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Figure 3.7.8.2.6(a). Typical tensile stress-strain curves for 7175-T74 aluminum alloy die forging at room temperature.

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Figure 3.7.8.2.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7175-T74 aluminum alloy die forging at room temperature.

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Figure 3.7.8.2.6(c). Typical tensile stress-strain curves for 7175-T74 aluminum alloy hand forging at room temperature.

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Figure 3.7.8.2.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for 7175-T74 aluminum alloy hand forging at room temperature.

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Figure 3.7.8.2.6(e). Typical tensile stress-strain curves for aluminum alloy 7175-T7452 hand forging at room temperature.

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Figure 3.7.8.2.6(f). Typical compressive stress-strain and compressive tangent-modulus curves for aluminum alloy 7175-T7452 hand forging at room temperature.

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Figure 3.7.8.2.8(a). Best-fit S/N curves for notched, Kt = 3.0, 7175-T74 alloy die forging, longitudinal direction.

Correlative Information for Figure 3.7.8.2.8(a)

Product Form: Die forging, 2.0 to 3.0 inch thick, unspecified thickness

Properties: TUS 77–82 ksi, TYS 69–75 ksi

Specimen Details:
Circumferential notch, Kt = 3
0.30 inch gross diameter
0.25 inch net diameter
Rectangular notched 0.10 × 0.20 inch

Surface Condition: Not specified

References: 3.2.5.1.9(d), 3.7.2.1.8(c), (d), 3.7.8.2.8(a), (b), and (c)

Test Parameters:
Loading – Axial
Frequency – 1200 cpm unspecified
Temperature – 70°F
Environment – Air

No. of Heats/Lots: 13

Equivalent Stress Equation:
Log Nf = 7.88 − 3.09 log (Seq − 7.15)
Seq = Sa + 0.37Sm
Std. Error of Estimate, Log (Life) = 7.38(1/Seq)
Standard Deviation, Log (Life) = 1.95
R2 = 83%

Sample Size: 137

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.8.2.8(b). Best-fit S/N curves for unnotched 7175-T74 alloy hand forging, longitudinal and transverse directions.

Correlative Information for Figure 3.7.8.2.8(b)

Product Form: Hand forging, 2.0 to 6.25 inch thick

Properties: TUS 71–77 ksi, TYS 60–68 ksi, 70°F

Specimen Details:
Uniform gage length
3.0 inch diameter
Hourglass gage section
0.25 inch minimum diameter

References: 3.2.5.1.9(d) 3.7.2.1.8(c) and (d)

Test Parameters:
Loading – Axial
Frequency – 1200 cpm
Temperature – 20°F
Environment – Air

No. of Heats/Lots: Not Specified

Equivalent Stress Equation:
Log Nf = 21.15 − 9.49 log (Seq)
Seq = Smax(1−R)
Std. Error of Estimate, Log (Life) = 23.33(1/Seq)
Standard Deviation, Log (Life) = 1.55
R2 = 76%

Sample Size: 50

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
3.7.97249 Alloy
3.7.9.0Comments and Properties

7249 is an Al-Zn-Mg-Cu-Cr alloy developed as a derivative from alloy 7149. Alloy 7249 has tighter compositional tolerances on its major constituents and lowered maximums on the interstitials such as Si, Fe, Mn, and Ti than alloy 7149.

7249-T7452 was developed as a replacement material for 7075-T6 forgings, which are susceptible to stress-corrosion cracking and exfoliation. 7249 also has higher strength at the higher thickness ranges and higher ductility than 7075-T6.

Material specifications for 7249 are shown in Table 3.7.9.0(a). Room-temperature mechanical properties are shown in Table 3.7.9.0(b).

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Table 3.7.9.0(a). Material Specification for 7249 Alloy
SpecificationForm
AMS 4334Hand forging
Temper Index for 7249 Alloy
SectionTemper
3.7.9.1T7452
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Table 3.7.9.0(b). Design Mechanical and Physical Properties of 7249 Aluminum Alloy Hand Forging
SpecificationAMS 4334
FormHand forging
TemperT7452
Thickness, in.<1.5001.501-
2.000		2.001-
2.500		2.501-
3.000		3.001-
3.500		3.501-
3.900		3.901-
4.500		4.501-
5.000		5.001-
5.500		5.501-
6.000
BasisSSSSSSSSSS
Mechanical Properties:
Ftu, ksi:
L76757473727169686766
LT76757473727169686766
ST············727169686766
Fty, ksi:
L68676664636159585655
LT68676664636159585655
ST············595857565453
Fcy, ksi:
L66656462615957565453
LT70696866656361605857
ST73727168676563626059
Fsua, ksi:
L49484747464644444342
LT47464645454443424141
Fbrub, ksi:
(e/D = 1.5)10710610410310110097969493
(e/D = 2.0)137135134132130128125123121119
Fbryb, ksi:
(e/D = 1.5)94939188878482807776
(e/D = 2.0)1091071061021019894939088
e, percent:
L12121212121212121212
LT10101010101010101010
ST············555555
E, 103 ksi10.1
Ec, 103 ksi10.4
G, 103 ksi3.8
μ0.33
Physical Properties:
ω, lb/in.3···
C, K, and α···
a Determined in accordance with ASTM B769.
b Bearing values are “dry pin” values per Section 1.4.7.1.
3.7.9.1T7452 Temper

Figures 3.7.9.1.6(a) and (b) presents the typical tensile and compressive stress-strain curves and compressive tangent-modulus curves at room temperature. Figure 3.7.9.1.6(c) presents the full-range stress-strain curves for hand-forged material at room temperature.

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Figure 3.7.9.1.6(a). Typical tensile stress-strain curves for 7249-T7452 aluminum alloy hand forging at room temperature.

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Figure 3.7.9.1.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7249-T7452 aluminum alloy hand forging at room temperature.

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Figure 3.7.9.1.6(c). Typical tensile stress-strain curves (full range) for 7249-T7452 aluminum alloy hand forging at room temperature.

3.7.107475 Alloy
3.7.10.0Comments and Properties

7475 is an Al-Zn-Mg-Cu alloy developed for applications requiring the high strength of 7075 but having fracture toughness superior to that of 7075. Sheet is available in the T61 and T761 tempers and plate in the T651 and T7651 tempers. Sheet has strength approximately the same as that of 7075 combined with toughness about the same as 2024-T3 at room temperature. Plate has strengths similar to those of corresponding tempers of 7075; the toughness of 7475-T651 equals or exceeds that of 7075-T7351.

Resistance to stress-corrosion cracking and exfoliation are comparable to that of 7075. The T73-type temper provides for much improved stress-corrosion resistance over T6-type temper with a decrease in strength. The T76-type temper provides for improved exfoliation resistance and stress-corrosion resistance over T6-type temper with some decrease in strength. Refer to Section 3.1.2.3.1 for information regarding resistance to stress-corrosion cracking, and to Section 3.1.3.4 for comments regarding the weldability of the alloy.

Material specifications are shown in Table 3.7.10.0(a). Room-temperature mechanical and physical properties are shown in Tables 3.7.10.0(b) through (d).

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Table 3.7.10.0(a). Material Specifications for 7475 Aluminum Alloy
SpecificationForm
AMS 4084Bare sheet
AMS 4085Bare sheet
AMS 4090Bare plate
AMS 4089Bare plate
AMS 4202Bare plate
AMS 4207Clad sheet
AMS 4100Clad sheet
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Table 3.7.10.0(b). Design Mechanical and Physical Properties of 7475 Aluminum Alloy Sheet and Plate
SpecificationAMS 4084AMS 4090AMS 4085AMS 4089
FormSheetPlateSheetPlate
TemperT61T651T761T7651
Thickness, in.0.040-0.2490.250-0.4990.500-1.0001.001-1.5000.040-0.0620.063-0.1870.188-0.2490.250-0.4990.500-1.0001.001-1.500
BasisSSSSSSSSSS
Mechanical Properties:
Ftu, ksi:
L75777777717171706969
LT75787878717171717070
Fty, ksi:
L66697070616161605959
LT64676868606060605959
Fcy, ksi:
L64676867605958605959
LT68707171616363636259
Fsu, ksi45444341434241413937
Fbrua, ksi:
(e/D = 1.5)120113113113112112111104103103
(e/D = 2.0)154144144144143143142136134134
Fbrya, ksi:
(e/D = 1.5)97919393909090828181
(e/D = 2.0)110106107107104104104979595
e, percent:
L91099999986
LT91099999986
E, 103 ksi10.010.210.010.2
Ec, 103 ksi10.510.610.510.6
G, 103 ksi3.83.93.83.9
μ0.330.330.330.33
Physical Properties:
ω, lb/in.30.101
C, Btu/(lb)(°F)0.23 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]80 (at 77°F) for T61 and T651; 90 (at 77°F) for T761 and T7651
α, 10-6 in./in./°F12.9 (68 to 212°F)
a See Table 3.1.2.1.1. Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.10.0(c). Design Mechanical and Physical Properties of 7475 Aluminum Alloy Plate
SpecificationAMS 4202
FormPlate
TemperT7351
Thickness, in.0.250-
1.500		1.501-
2.000		2.001-
2.500		2.501-
3.000		3.001-
3.500		3.501-
4.000
BasisABABABABABAB
Mechanical Properties:
Ftu, ksi:
L707270716870686964676466
LT717370726870686964686467
ST66a70a65696569656863676366
Fty, ksi:
L596258605659565852565254
LT606258b615659565852565254
ST54a57a53565356535550535052
Fcy, ksi:
L586056595457535549534951
LT616360635861586054585456
ST62a64a60635861586054585456
Fsu, ksi414242434142414239423941
Fbruc, ksi:
(e/D = 1.5)1021051031061011041011039710297101
(e/D = 2.0)132136134138131135131134125133125131
Fbryc, ksi:
(e/D = 1.5)818482868184818477827780
(e/D = 2.0)971019710295100959989968993
e, percent (S-basis):
L10···10···10···10···10···9···
LT9···8···8···8···8···7···
ST4b···4···4···3···3···3···
E, 103 ksi10.3
Ec, 103 ksi10.6
G, 103 ksi3.9
μ0.33
Physical Properties:
ω, lb/in.30.101
C, Btu/(lb)(°F)0.21 (at 212°F)
K, Btu/[(hr)(ft2)(°F)/ft]94 (at 77°F)
α, 10-6 in./in./°F13.0 (68 to 212°F)
a Values applicable to 1.500-inch thickness only.
b S-basis. The rounded T99 value for Fty(LT) = 59 ksi.
c See Table 3.1.2.1.1. Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 3.7.10.0(d). Design Mechanical and Physical Properties of Clad 7475 Aluminum Alloy Sheet
SpecificationAMS 4207AMS 4100
FormSheet
TemperT61T761
Thickness, in.0.040-0.0620.063-0.1870.188-0.2490.040-0.0620.063-0.1870.188-0.249
BasisSABSSABAB
Mechanical Properties:
Ftu, ksi:
L696973726667706871
LT697073726668707072
Fty, ksi:
L616467635658615963
LT5960a64615557606062
Fcy, ksi:
L606165625556595860
LT636468655859626163
Fsu, ksi424041394140414041
Fbrub, ksi:
(e/D = 1.5)110111116115104107110108111
(e/D = 2.0)140142148146133136140138142
Fbryb, ksi:
(e/D = 1.5)899096928386909093
(e/D = 2.0)10210411110697101106106110
e, percent (S-basis):
LT99···999···9···
E, 103 ksi:
Primary10.010.010.010.010.010.010.010.010.0
Secondary···9.29.49.7···9.29.49.79.7
Ec, 103 ksi:
Primary10.510.510.510.510.510.510.510.510.5
Secondary···9.49.710.0···9.49.710.010.0
G, 103 ksi3.8
μ0.33
Physical Properties:
ω, lb/in.30.101
C, K, and α···
a S-basis. The rounded T99 value is 61 ksi.
b Bearing values are “dry pin” values per Section 1.4.7.1.

The temper index for 7475 is: Section 3.7.10.1 covers the T61 and T651 tempers; Section 3.7.10.2 covers the T7351 temper; Section 3.7.10.3 covers the T761 and T7651 tempers.

3.7.10.1T61 and T651 Tempers

Figures 3.7.10.1.6(a) through (f) present tensile and compressive stress-strain and tangent-modulus curves for T61 bare sheet, clad T61 sheet, and T651 plate. Figure 3.7.10.1.6(g) contains full-range tensile stress-strain curves for T61 sheet. Fatigue data for sheet are shown in Figures 3.7.10.1.8(a) through (c). Graphical displays of the residual strength behavior of middle-tension panels for bare and clad T61 sheet, in both the L-T and T-L crack orientations, are presented in Figures 3.7.10.1.10(a) through (d).

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Figure 3.7.10.1.6(a). Typical tensile stress-strain curves for 7475-T61 aluminum alloy sheet at room temperature.

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Figure 3.7.10.1.6(c). Typical tensile stress-strain curves for clad 7475-T61 aluminum alloy sheet at room temperature.

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Figure 3.7.10.1.6(e). Typical tensile stress-strain curves for 7475-T651 aluminum alloy plate at room temperature.

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Figure 3.7.10.1.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7475-T61 aluminum alloy sheet at room temperature.

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Figure 3.7.10.1.6(d). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7475-T61 aluminum alloy sheet at room temperature.

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Figure 3.7.10.1.6(f). Typical compressive stress-strain and compressive tangent-modulus curves for 7475-T651 aluminum alloy plate at room temperature.

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Figure 3.7.10.1.6(g). Typical tensile stress-strain curves (full range) for 7475-T61 aluminum alloy sheet at room temperature.

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Figure 3.7.10.1.8(a). Best-fit S/N curve for unnotched 7475-T61 and T761 sheet, thickness 0.125 inch, longitudinal and long transverse directions.

Correlative Information for Figure 3.7.10.1.8(a)

Product Form: Sheet, 0.032 to 0.125 inch thick

Properties: T61 — TUS 81 ksi, TYS 73–75 ksi, RT; T761 — TUS 77 ksi, TYS 68–70 ksi, RT

Specimen Details:
Unnotched, hourglass
0.500 inch diameter
4.00 inch test section radius, r

Surface Condition: As machined

Reference: 3.2.6.1.9(d)

Test Parameters:
Loading – Axial
Frequency – 798, 1500, or 1728 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 2

Maximum Stress Equation:
Log Nf = 16.9 − 7.03 log (Smax)
Std. Error of Estimate, Log (Life) = 0.545
Standard Deviation, Log (Life) = 0.988
R2 = 70%

Sample Size: 67
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Figure 3.7.10.1.8(b). Best-fit S/N curve for unnotched 7475-T61 and T761 sheet, thickness > 0.125 inch, longitudinal and long transverse directions.

Correlative Information for Figure 3.7.10.1.8(b)

Product Form: Sheet, > 0.125 inch through 0.249 inch thick

Properties: T61 — TUS 80–81 ksi, TYS 73–76 ksi, RT; T761 — TUS 75 ksi, TYS 66–67 ksi, RT

Specimen Details:
Unnotched, hourglass
0.500 inch diameter
4.000 inch test section radius, R

Surface Condition: As machined

Reference: 3.2.6.1.9(d)

Test Parameters:
Loading – Axial
Frequency – 798, 1500, or 1728 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 2

Maximum Stress Equation:
Log Nf = 22.7 − 10.1 log (Smax)
Std. Error of Estimate, Log (Life) = 0.657
Standard Deviation, Log (Life) = 1.380
R2 = 77%

Sample Size: 24
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Figure 3.7.10.1.8(c). Best-fit S/N curve for notched, Kt = 3.0, 7475-T61 and T761 sheet, longitudinal and long transverse directions.

Correlative Information for Figure 3.7.10.1.8(c)

Product Form: Sheet, 0.032 to 0.249 inch thick

Properties: T61 — TUS 81–82 ksi, TYS 73–76 ksi, RT; T761 — TUS 75–77 ksi, TYS 67–70 ksi, RT

Specimen Details:
Notched, edge notched
Kt = 3.0
1.000 inch gross width
0.700 inch net width
0.050 inch root radius, r
60° flank angle

Surface Condition: As machined

Reference: 3.2.6.1.9(d)

Test Parameters:
Loading – Axial
Frequency – 798, 1500, or 1728 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 2

Maximum Stress Equation:
Log Nf = 13.4 − 6.29 log (Smax)
Std. Error of Estimate, Log (Life) = 0.441
Standard Deviation, Log (Life) = 0.931
R2 = 78%

Sample Size: 99
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Figure 3.7.10.1.10(a). Residual strength behavior of 0.063-inch-thick 7475T61 aluminum alloy sheet at room temperature.

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Figure 3.7.10.1.10(b). Residual strength behavior of 0.063-inch-thick 7475T61 aluminum alloy sheet at room temperature.

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Figure 3.7.10.1.10(c). Residual strength behavior of 0.063-inch-thick 7475T61 clad aluminum alloy sheet at room temperature.

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Figure 3.7.10.1.10(d). Residual strength behavior of 0.063-inch-thick 7475-T61 clad aluminum alloy sheet at room temperature.

3.7.10.2T7351 Temper

Figures 3.7.10.2.6(a) and (b) present tensile and compressive stress-strain and tangent-modulus curves for T7351 plate. Fatigue data for 7475-T7351 plate are presented in Figures 3.7.10.2.8(a) and (b); Figure 3.7.10.2.8(b) also covers 7475-T7651 plate. Figures 3.7.10.2.9(a) and (b) present fatigue-crack-propagation data for T7351 plate.

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Figure 3.7.10.2.6(a). Typical tensile stress-strain curves for 7475-T7351 aluminum alloy plate at room temperature.

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Figure 3.7.10.2.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7475-T7351 aluminum alloy plate at room temperature.

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Figure 3.7.10.2.8(a). Best-fit S/N curves for unnotched 7475-T7351 plate, longitudinal and long transverse orientation.

Correlative Information for Figure 3.7.10.2.8(a)

Product Form: Plate, 0.5, 1.0, 2.0, 3.0, and 4.0-inches thick

Properties: L — TUS 70 ksi, TYS 60 ksi, RT; LT — TUS 71 ksi, TYS 60 ksi, RT

Specimen Details:
Unnotched
Hourglass
0.300 inch net diameter
9.875 inch test section radius

Surface Condition: As machined

References: 3.7.10.2.8(a) and (b)

Test Parameters:
Loading — Axial
Frequency — Not specified
Temperature — RT
Environment — Air

No. of Heats/Lots: 5

Equivalent Stress Equation:
Log Nf = 17.42 − 7.56 log (Seq)
Seq = Smax(1−R)0.40
Std. Error of Estimate, Log (Life) = 0.433
Standard Deviation, Log (Life) = 0.857
R2 = 74%

Sample Size: 52

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.10.2.8(b). Best-fit S/N curves for notched, Kt = 3.0, 7475-T7351 and T7651 plate, longitudinal and long transverse direction.

Correlative Information for Figure 3.7.10.2.8(b)

Product Form: Plate, 0.5, 1.0, 1.5, 2.0, 3.0, and 4.0 inches thick

Properties: L (T7351) — TUS 70 ksi, TYS 60 ksi, RT; LT (T7351) — TUS 71 ksi, TYS 61 ksi, RT; L (T7351) — TUS 72 ksi, TYS 62 ksi, RT; (T7651) — Not specified; L (T7351) — TUS 72 ksi, TYS 63 ksi, RT; LT (T7351) — TUS 73 ksi, TYS 62 ksi, RT

Specimen Details:
Notched, Kt = 3.0
Circumferentially notched
0.253 inch gross width
0.147 inch net width
0.013 inch root radius, r
60° flank angle
Edge notched
1.00 inch gross width
0.70 inch net width
root radius not specified
60° flank angle
Edge notched
2.25 inch gross width
1.50 inch net width
0.113 inch root radius, r
60° flank angle
Circumferentially notched
1.375 inch gross width
0.25 inch net width
0.13 inch root radius, r
60° flank angle

References: 3.7.10.2.8(a) through (e)

Surface Condition:
Not specified [Ref. (a) and (b)]
As machined and deburred [Ref. (c)]
32 RMS [Ref. (d)]
10 RMS [Ref. (e)]

Test Parameters:
Loading — Axial
Frequency
— Not specified [Ref. (a) and (b)]
— 1800 cpm [Ref. (c) and (d)]
— 1500 cpm [Ref. (e)]
Temperature — RT
Environment — Air

No. of Heats/Lots: 8

Equivalent Strain Equation:
Log Nf = 8.46 − 3.21 log (Seq − 7.5)
Seq = Smax(1−R)0.72

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 3.7.10.2.9(a). Fatigue-crack-propagation data for 1.5-inch-thick, 7475T7351 aluminum alloy plate [References 3.7.10.2.9(a) and (b)].

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Figure 3.7.10.2.9(b). Fatigue-crack-propagation data for 0.500-inch-thick, 7475T7351 aluminum alloy plate [Reference 3.7.10.2.9(c)].

3.7.10.3T761 and T7651 Tempers

Figures 3.7.10.3.6(a) through (j) present tensile and compressive stress-strain and tangent-modulus curves for T761 bare and clad sheet (in three thickness ranges: 0.040–0.062, 0.063–0.187, and 0.188–0.249 inch) and T7651 plate. Figures 3.7.10.3.6(k) and (l) contain full-range tensile stress-strain curves for T761 bare and clad sheet, respectively. Fatigue data for 7475-T761 sheet are presented in Figures 3.7.10.1.8(a) through (c) (Section 3.7.10.1); fatigue data for 7475-T7651 plate are shown in Figure 3.7.10.2.8(b) (Section 3.7.10.2). Graphical displays of the residual strength behavior of middle-tension panels are presented in Figures 3.7.10.3.10(a) and (b).

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Figure 3.7.10.3.6(a). Typical tensile stress-strain curves for 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(i). Typical tensile stress-strain curves for 7475-T7651 aluminum alloy plate at room temperature.

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Figure 3.7.10.3.6(b). Typical compressive stress-strain and compressive tangent-modulus curves for 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(c). Typical tensile stress-strain curves for clad 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(d). Typical tensile stress-strain curves for clad 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(e). Typical tensile stress-strain curves for clad 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(f). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(g). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(h). Typical compressive stress-strain and compressive tangent-modulus curves for clad 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(j). Typical compressive stress-strain and compressive tangent-modulus curves for 7475-T7651 aluminum alloy plate at room temperature.

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Figure 3.7.10.3.6(k). Typical tensile stress-strain (full range) curves for 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.6(l). Typical tensile stress-strain (full range) curves for clad 7475T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.10(a). Residual strength behavior of 0.063-inch-thick 7475-T761 aluminum alloy sheet at room temperature.

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Figure 3.7.10.3.10(b). Residual strength behavior of 0.063-inch-thick 7475-T761 aluminum alloy sheet at room temperature.

Other MIL-HDBK-5 Chapters
Chapter 2 (Steel) Chapter 4 (Magnesium)

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