Fig. 49 Fatigue-life curves for 7075-T6 and 7075-TMT. (a) Unnotched. (b) Notched, K t = 8 More

Fig. 19 Fatigue crack growth of 2024-T3 versus 7075-T6 plate over entire da / dN -Δ K range More

Fig. 15 Effect of strain rate and temperature on tensile strength of alloy 7075-T6 More

Fig. 16 Effect of temperature on tensile properties of Alclad 7075-T6 More

Fig. 6 Fatigue crack growth behavior of equivalent yield strength P/M 7075-T6510, I/M 7075-T6510, and I/M 7475-T6510 in a laboratory air environment. Source: Ref 43 More

Fig. 15 Material substitution on Boeing 777 aircraft. Aluminum alloys 7075-T6 and 2024-T3 have been replaced by 7055-T7 and 2324-T3 and other more corrosion- and SCC-resistant aluminum alloys. More

Fig. 5 Fatigue properties of unexposed and corroded, 0.080 in. thick 7075-T6 sheet. Data of various exposure times of prohesion corrosion spray test are compared to MMPDS Handbook data. Stress-concentration factor K t =1 is smooth specimen, K t =2 has a discontinuity that doubles stress More

Fig. 8 Corroded lap joint of 7075-T6 skin with 2017 fasteners. (a) Specimen from panel exposed in the ASTM CASS spray test show pillowing and attack of cladding. (b) Micrograph cross section show loss of cladding, but no loss to the 7075-T6 core. Original magnification: 200× More

Fig. 10 Predicted fatigue lives for 7075-T6 alloy, open-hole geometry specimens with superimposed corrosion damage. Open-hole without corrosion damage, K t =3.0 curve. Char is the characteristic damage curve. 5% and 95% curves represent the 5th and 95th percentile of pit dimension More

Fig. 14 Stress-corrosion cracking on the Macchi MB-326 7075-T6 stabilizer spar of RAAF aircraft used by the acrobatic team More

Fig. 34 Section through an alloy 7075 ingot (edge at right), direct-chill semicontinuous cast. Etchant: dilute Keller's reagent. Original magnification 250×. Source: Ref 4 More

Fig. 40 Coarse primary crystal of CrAl7 in an alloy 7075 ingot. As-polished. Original magnification 100×. Source: Ref 4 More

Fig. 13 7075 Al alloy. (a) The effect of grain boundary precipitate size on fracture toughness and fracture morphology. (b) Equilibrium grain boundary η-MgZn 2 precipitates at grain boundaries More

Fig. 11 Aluminum alloy 7075-O radial draw formed T-section with radical changes in angle between leg and flange. Dimensions given in inches More

Fig. 12 Fracture toughness comparisons of aluminum alloys 2024, 2124, 7075 and 7475. Source: Ref 15 More

Fig. 19 Effect of R on fatigue crack growth rates in aluminum alloy 7075-T6. Source: Ref 54 More

Fig. 34 Thickness effect on crack growth in 7075-T6 under flight simulation loading. Load spectrum F-4; center-cracked tension specimen ( W = 101.6 mm). Source: Ref 68 More

Fig. 52 Monotonic and cyclic stress-strain curves for 7075-T73 aluminum alloy More