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D6ac

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Published: 01 January 1989
Fig. 19 Residual stress from surface grinding of D6AC steel (56 HRC). Wheel A46K8V Wheel speed, m/min (ft/min) 1800 (6000) Cross feed, mm/pass (in./pass) 1.25 (0.050) Table speed, m/min (ft/min) 12 (40) Depth of grind, mm (in.) 0.25 (0.010) Grinding fluid Soluble More
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Published: 01 December 1998
Fig. 7 Residual stress from surface grinding of D6AC steel (56 HRC) Wheel A46K8V Wheel speed, m/min (ft/min) 1800 (6000) Cross feed, mm/pass (in./pass) 1.25 (0.050) Table speed, m/min (ft/min) 12 (40) Depth of grind, mm (in.) 0.25 (0.010) Grinding fluid Soluble oil More
Image
Published: 01 January 2002
Fig. 6 High-cycle fatigue in D6AC steel at Δ K > 60 MPa m (54.6 ksi in. ). (a) Macroscopic view of rapid fatigue growth under plane-stress conditions. (b) High-quality TEM replica showing elongated shear dimples from fatigue region More
Image
Published: 01 January 1996
Fig. 31 Sequence effects during fatigue crack growth in D6AC high-strength steel (0.42C-1Cr-0.65Ni-0.1Mo-0.12V) under program fatigue loading. S 0.2 = 1500 MPa, S U = 1650 MPa. (a) Program load history and corresponding bands on fatigue fracture. (b) Different da / dN in Lo-Hi and Hi More
Image
Published: 01 January 1987
Fig. 54 Three views of a fatigue fracture in D6AC steel plate, showing beach marks. (a) Plate subjected to a series of varied loading cycles in the laboratory. The crack origin, at the bottom center, was at a starter notch formed by electrical discharge machining. (b) Area in lower square More
Image
Published: 01 January 1996
Fig. 9 Effect of ausforming on SCC of D6AC steel in distilled water ( Ref 97 ) More
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Published: 15 January 2021
Fig. 6 High-cycle fatigue in D6AC steel at Δ K > 60 MPa m (54.6 ksi in . ). (a) Macroscopic view of rapid fatigue growth under plane-stress conditions. (b) High-quality transmission electron microscopy replica showing elongated shear dimples from fatigue region More
Image
Published: 15 January 2021
Fig. 54 High-cycle fatigue in D6AC steel at Δ K > 60 M P a m (54.6 ksi in .). (a) Macroscopic view of rapid fatigue growth under plane-stress conditions. (b) High-quality transmission electron microscopy replica showing elongated shear dimples from fatigue region More
Image
Published: 01 February 2024
Fig. 78 Continuous-cooling-transformation diagram illustrating the ausbay cooling process for a D6AC steel. Adapted from Ref 186 More
Image
Published: 01 January 1989
Fig. 21 Change in deflection versus wheel speed and down feed in the surface grinding of D6AC steel (56 HRC) Wheel grade A46K8V Cross feed, mm/pass (in./pass) 1.25 (0.050) Table speed, m/min (ft/min) 12 (40) Depth of cut, mm (in.) 0.25 (0.010) Specimen size, mm More
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002394
EISBN: 978-1-62708-193-1
... was manufactured from D6ac steel. During a test flight that occurred in December 1969, the wing failed in the steel wing pivot fitting and the aircraft crashed, killing the pilots. An investigation was undertaken to determine the cause of failure. Recovered from the wreckage was a portion of the wing box...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002397
EISBN: 978-1-62708-193-1
... by problems in material selection, fabrication, and heat treatment of the D6ac steel wing carrythrough structure for the F-111 aircraft. Other government agencies have included damage tolerance requirement specifications, and it is expected that this trend will continue. These concepts have already been...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002378
EISBN: 978-1-62708-193-1
... through box (the structure at which the wings join to the fuselage). Failures of the F-111 were related to choice of a very brittle material (D6AC—a high-strength tool steel) and a heat-treating procedure that produced non-uniform microstructures. In 1988, the upper fuselage of a Boeing 737 operated...
Series: ASM Desk Editions
Publisher: ASM International
Published: 01 December 1998
DOI: 10.31399/asm.hb.mhde2.a0003190
EISBN: 978-1-62708-199-3
... is in compression. Development of high residual tension stresses causes problems in meeting dimensional specifications as a result of the accompanying distortion of thin parts and also increases susceptibility to stress-corrosion failure. Fig. 7 Residual stress from surface grinding of D6AC steel (56 HRC...
Book: Machining
Series: ASM Handbook
Volume: 16
Publisher: ASM International
Published: 01 January 1989
DOI: 10.31399/asm.hb.v16.a0002119
EISBN: 978-1-62708-188-7
... RC IGA IGA Hardenable 4340 and D6ac steels R R R R R PD PD MCK SE SE L & T MCK RC IGA IGA MCK UTM UTM UTM OTM OTM OTM OTM D2 tool steel R R R R R PD PD MCK SE SE L & T MCK RC IGA IGA MCK UTM UTM UTM OTM OTM...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003540
EISBN: 978-1-62708-180-1
... and Cyclic IG Processes Cyclic microvoid and cyclic IG processes ( Ref 13 ) have also been observed. The former is shown in Fig. 6 for an ultrahigh-strength D6AC steel tested at a stress-intensity factor range (Δ K ) greater than 60 MPa m (54.6 ksi in. ). The crack advance per cycle...
Series: ASM Handbook
Volume: 13A
Publisher: ASM International
Published: 01 January 2003
DOI: 10.31399/asm.hb.v13a.a0003636
EISBN: 978-1-62708-182-5
... 550 ST S 8620 leaded Pb 204 399 ST S A-4 Pb 288 550 ST S A-4 leaded Pb 204 399 ST S D6ac Cd 149 300 DF N (a) ST, standard tensile test; DF, delayed-failure tensile test. (b) S, smooth specimen; N, notched specimen. (c) NA, data not available. Courtesy...
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006777
EISBN: 978-1-62708-295-2
...-intensity factor range (Δ K ) values ( Ref 17 ). Cyclic Microvoid and Cyclic Intergranular Processes <xref rid="a0006777-ref18" ref-type="bibr">(Ref 18)</xref> Cyclic microvoid and cyclic IG processes have also been observed. The former is shown in Fig. 6 for an ultrahigh-strength D6AC steel tested...
Series: ASM Desk Editions
Publisher: ASM International
Published: 01 December 1998
DOI: 10.31399/asm.hb.mhde2.a0003224
EISBN: 978-1-62708-199-3
.... In the late 1960s and early 1970s, the USAF F-111 fighter aircraft experienced catastrophic failure of the wing through box (the structure at which the wings join to the fuselage). Failures were related to the choice of a very brittle material (D6AC high-strength steel) and a heat-treating procedure...
Series: ASM Handbook
Volume: 13C
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v13c.a0004128
EISBN: 978-1-62708-184-9
...” approach has been used to account for corrosion pitting in D6AC steel (UNS K24728 with nominal composition of Fe-0.46C-1.00Cr-1.00Mo-0.55Ni, a medium-carbon, ultrahigh-strength, quench-and-temper steel commonly used for highly stressed aircraft parts ( Ref 29 ). This study was undertaken to incorporate...