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Published: 01 August 2005
Fig. 5.76 Comparison between theory ( Eq 5.54 ) and fatigue crack growth data of 7079-T651 aluminum alloy tested in vacuum and saturated NaCl solution. Source: Ref 5.76 More
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Published: 01 August 1999
Fig. 22 Stress-corrosion cracking (SCC) in an aluminum alloy 7079-T6 main landing gear H-link. (a) Overall view of H-link. (b) Pitting and intergranular corrosion that initiated SCC. Source: Ref 17 More
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Published: 01 August 1999
Fig. 23 SCC in aluminum alloy 7079-T6 spars of a vertical fin. (a) Cracks in the mating surface of the rear spar. (b) Fracture surface of a statically broken front spar. Source: Ref 17 More
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Published: 01 August 1999
Fig. 26 Aluminum alloy 7079-T6 aircraft wing spar (a) showing crack (arrow). (b) Fracture surfaces of opened spar crack. Note clamshell marks at termination of the crack (left). Suspected multiple initiation sites are located between arrows. 1.5 x . (c) Section of flange with surface at right More
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Published: 01 August 1999
Fig. 33 Corrosion fatigue behavior of aluminum alloy 7079-T651 plate (S-L orientation). Temperature: 23 °C (73 °F); frequency: 4 cycles/s; stress ratio; R = 0. (a) Effect of stress intensity range on crack growth rate. K ICFC and a range of K ISCC are indicated at the bottom. (b More
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Published: 01 August 1999
Fig. 12 Relative effectiveness of various protective systems in preventing SCC of susceptible aluminum alloys. Combined data for highly elastically strained specimens of alloys 2014-T651 and 7079-T651 exposed at PI. Judith, RI; Comfort, TX; and New Kensington, PA. Anodized specimens include More
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Published: 01 August 1999
Fig. 34 The varied effects of loading frequency on corrosion fatigue crack (CFC) propagation rate in peak aged 7075, 7017, 7475, and 7079 exposed to aqueous chloride solution (free corrosion) at constant Δ K and R . The fatigue crack is parallel to the plate rolling plane in the SCC More
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Published: 01 November 2012
Fig. 29 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 More
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Published: 01 August 1999
Fig. 13 Influence of various anions on stress corrosion crack velocity of a high-strength aluminum alloy (7079-T651) immersed in aqueous solutions. 2.5 cm thick plate. T-L crack orientation (long transverse grain direction normal to the fracture plane; longitudinal direction of crack More
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Published: 01 August 1999
Fig. 14 The effect of electrode potential and stress intensity on stress corrosion crack velocity in a high strength aluminum alloy (7079-T651). 2.5 cm thick plate. T-L crack orientation (long transverse grain direction normal to the fracture plane; longitudinal direction of crack propagation More
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Published: 01 August 1999
Fig. 23 Crack depth and stress intensity versus time curves for double-beam specimens of aluminum alloys 7075-T651, 7079-T651, and 7075-T7351 having nearly identical deflections and starting crack depths. Specimens with S-L orientation (see Fig. 11 ) measuring 25 × 25 × 127 mm (1 × 1 × 5 More
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Published: 01 August 1999
-in starting stress intensity ( K lo for the tests of that material. Data for alloys 7075-T651 and 7079-T651 are from Ref 44 . Source: Ref 52 More
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Published: 01 January 2017
product indicates the pop-in starting stress intensity ( K Io ) for the tests of that material. Data for alloys 7075-T651 and 7079-T651 are from Ref 17.37 . Source: Ref 17.90 More
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Published: 01 August 1999
Fig. 25 Effect of corrosive environment on SCC velocity and threshold stress intensity for 7079-T651 plate (64 mm, or 2.5 in., thick) stressed in the short-transverse direction (S-L; see Fig. 11 ). Double-beam specimens bolt-loaded to pop-in. No SCC occurred during 3 years of exposure to dry More
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Published: 01 January 2017
Fig. 17.51 Effect of corrosive environment on SCC velocity and threshold stress intensity for 7079-T651 plate (64 mm, or 2.5 in., thick) stressed in the short-transverse direction (S-L; see Fig. 17.29 ). Double-beam specimens bolt-loaded to pop-in. No SCC occurred during 3 years of exposure More
Series: ASM Technical Books
Publisher: ASM International
Published: 01 August 1999
DOI: 10.31399/asm.tb.caaa.t67870099
EISBN: 978-1-62708-299-0
... … … 7178-T76 L >360 >52 >380 >55 … … LT >360 >52 >360 >52 … … ST 170 25 170 25 … … 7079-T6 L >380 >55 >410 >60 >340 >50 LT 270 40 240 35 210 30 ST <55 <8 <55 <8 <55 <8 7049-T73 ST...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 August 1999
DOI: 10.31399/asm.tb.caaa.t67870063
EISBN: 978-1-62708-299-0
... 2024-T6 C Yes Yes 2011-T3 D Yes Yes 2024-T3, T4 D Yes Yes 2219-T3 D Yes Yes 7075-T6 D Yes Yes 7175-T66 D Yes Yes 7079-T6 D Yes Yes 7178-T6 D Yes Yes (a) Stress-corrosion cracking (SCC) ratings are based on service experience (excluding special...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 August 2005
DOI: 10.31399/asm.tb.mmfi.t69540383
EISBN: 978-1-62708-309-6
... Comparison of steps in the original and <sc>RACETRAK</sc> −reduced spectra Table A4.2 Comparison of steps in the original and RACETRAK −reduced spectra Spectrum ID Type of spectrum Material Steps per block Original DMIN = 0.25 DMIN = 0.5 A Upper longeron FS 453 7079-T73511, ext, LT...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 March 2000
DOI: 10.31399/asm.tb.aet.t68260187
EISBN: 978-1-62708-336-2
... 5083 Non-heat-treatable Mg, Mn, Cr 20 5086 Non-heat-treatable Mg, Mn, Cr 25 5456 Non-heat-treatable Mg, Mn, Cr 20 7001 Heat treatable Zn, Mg, Cu, Cr 7 7075 Heat treatable Zn, Mg, Cu, Cr 10 7079 Heat treatable Zn, Mg, Cu, Mn, Cr 10 (a) ≤25, difficult to extrude...
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Series: ASM Technical Books
Publisher: ASM International
Published: 01 August 1999
DOI: 10.31399/asm.tb.caaa.t67870219
EISBN: 978-1-62708-299-0