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7075-T6

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Published: 01 January 1996
Fig. 49 Fatigue-life curves for 7075-T6 and 7075-TMT. (a) Unnotched. (b) Notched, K t = 8 More
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Published: 15 June 2019
Fig. 1 Comparison of fatigue strength bands for 2014-T6, 2024-T4, and 7075-T6 aluminum alloys for rotating-beam tests. Source: Ref 3 More
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Published: 01 January 1996
Fig. 19 Comparison of fatigue strength bands for 2014-T6, 2024-T4, and 7075-T6 aluminum alloys for rotating-beam tests. Source: R. Templin, F. Howell, and E. Hartmann, “Effect of Grain-Direction on Fatigue Properties of Aluminum Alloys,” Alcoa, 1950 More
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Published: 01 June 2016
Fig. 12 Fit to Fink and Willey’s data for yield strength of a 7075-T6 aluminum alloy. Source: Ref 3 More
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Published: 01 June 2016
Fig. 27 C-curves of 7075-T6 determined from Jominy end-quench tests ( Ref 32 ) compared to Fink-Willey C-curves(see Fig. 9b ) More
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Published: 01 June 2016
Fig. 34 Effects of section size on tensile properties of 7075-T6 More
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Published: 01 June 2016
Fig. 35 Effects of reheating time and temperature on tensile properties of 7075-T6 sheet More
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Published: 01 June 2016
Fig. 36 Effects of room-temperature aging interval on tensile properties of 7075-T6 sheet More
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Published: 01 January 1990
Fig. 19 Fatigue crack growth of 2024-T3 versus 7075-T6 plate over entire da / dN -Δ K range More
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Published: 01 January 1990
Fig. 15 Effect of strain rate and temperature on tensile strength of alloy 7075-T6 More
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Published: 01 January 1990
Fig. 16 Effect of temperature on tensile properties of Alclad 7075-T6 More
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Published: 15 June 2019
Fig. 5 Fracture toughness of 7075-T6, T651 sheet and plate from tests of fatigue-cracked center-notched specimens (transverse). Source: Ref 11 More
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Published: 15 June 2019
Fig. 5 Variation in rotating-beam fatigue for (a) 2024-T4, (b) 7075-T6, (c) 2014-T6, and (d) 7079-T6 alloys. Notches (60°) were very sharp ( K t > 12) with a radius of approximately 0.005 mm (0.0002 in.). Results are from over a thousand rotating-beam tests performed in the 1940s. Source More
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Published: 15 June 2019
Fig. 1 The relative resistance to stress-corrosion cracking of 7075-T6 plate is influenced by direction of stressing. Samples are alternately immersed in 3.5% NaCl. Plate thickness: 6.4 to 76 mm (0.25 to 3 in.). Source: Ref 5 More
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Published: 15 June 2019
Fig. 5 Effects of section size on tensile properties of alloy 7075-T6 More
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Published: 01 January 1989
Fig. 9 Fillet area of 0.5 mm (0.020 in.) step 7075-T6 sheet chemically milled in (a) standard etchant and (b) TEA etchant. 55× More
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Published: 01 January 2002
Fig. 3 Cracked HL22-8 aluminum alloy 7075-T6 fasteners. (a) and (b) Typical cracked fastener head. (c) Typical head cracks produced by installing fasteners in misaligned holes during testing More
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Published: 01 January 2002
Fig. 46 Crack propagation in shear bands in a 7075-T6 plate specimen. Shear banding has occurred on four planes of high shear stress (two containing the width direction and two containing the thickness direction). Crack initiation has occurred in multiple locations, including the edge More
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Published: 01 January 2002
Fig. 86 Fracture on essentially one plane of high shear stress in a 7075-T6 cylindrical tensile specimen. There is a small flat region in the center of the specimen (not visible in photograph) that does not extend to the surface of the specimen. No fracture surface markings exist to indicate More
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Published: 01 January 2002
Fig. 20 Fatigue-fracture zones in aluminum alloy 7075-T6 plates. (a) Fatigue crack that grew as a flat-face fracture with a shallow convex crack front. (b) Change in orientation of fatigue fracture from plane strain (arrow A) to plane stress (arrow B). More