MIL-HDBK-5: Chapter 5.4 — Titanium
Chapter 5.4 Contents
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Chapter 1 — General Chapter 2 — Steel Chapter 3 — Aluminum Chapter 4 — Magnesium Chapter 5 — Titanium 5.1 — General 5.2 — Unalloyed Titanium 5.3 — Alpha and Near-Alpha Titanium Alloys 5.4 — Alpha-Beta Titanium Alloys 5.5 — Beta, Near-Beta, and Metastable-Beta Titanium Alloys 5.6 — Element Properties Chapter 6 — Heat-Resistant Alloys
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 5.4.1.0(a)Material Specifications for Ti-6Al-4V Table 5.4.1.0(b)Design Mechanical and Physical Properties of Ti-6Al-4V Sheet, Strip, and Plate Table 5.4.1.0(c1)Design Mechanical and Physical Properties of Ti-6Al-4V Bar Table 5.4.1.0(c2)Design Mechanical and Physical Properties of Ti-6Al-4V Bar Table 5.4.1.0(d)Design Mechanical and Physical Properties of Ti-6Al-4V Bar Table 5.4.1.0(e)Design Mechanical and Physical Properties of Ti-6Al-4V Extrusion Table 5.4.1.0(f)Design Mechanical and Physical Properties of Ti-6Al-4V Die Forging Table 5.4.1.0(g)Design Mechanical and Physical Properties of Ti-6Al-4V Titanium Alloy Casting Table 5.4.2.0(a)Material Specifications for Ti-6Al-6V-2Sn Table 5.4.2.0(b)Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Sheet, Strip, and Plate Table 5.4.2.0(c)Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Bar Table 5.4.2.0(d)Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Forging Table 5.4.2.0(e)Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Extruded Bar and Shapes Table 5.4.3.0(a)Material Specification for Ti-4.5Al-3V-2Fe-2Mo Titanium Alloy Table 5.4.3.0(b)Design Mechanical and Physical Properties of Ti-4.5Al-3V-2Fe-2Mo Titanium Alloy Sheet Table 5.4.3.0(c)Design Mechanical and Physical Properties of Ti-4.5Al-3V-2Fe-2Mo Titanium Alloy Bar
Table of Figures — Ti-6Al-4V (5.4.1)
Fig 5.4.1.0Effect of temperature on the physical properties of Ti-6Al-4V alloy (wrought products). Fig 5.4.1.1.1Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of annealed Ti-6Al-4V alloy (all wrought products). Fig 5.4.1.1.2Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of annealed Ti-6Al-4V alloy (all wrought products). Fig 5.4.1.1.3Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of annealed Ti-6Al-4V alloy (all wrought products). Fig 5.4.1.1.4Effect of temperature on the tensile and compressive moduli (E and Ec) of annealed Ti-6Al-4V alloy sheet and bar. Fig 5.4.1.1.5Effect of temperature on the elongation of annealed Ti-6Al-4V alloy sheet and bar. Fig 5.4.1.1.6(a)Typical tensile stress-strain curves at cryogenic, room, and elevated temperatures for annealed Ti-6Al-4V alloy extrusion. Fig 5.4.1.1.6(b)Typical compressive stress-strain curves at room and elevated temperatures for annealed Ti-6Al-4V alloy extrusion. Fig 5.4.1.1.6(c)Typical compressive tangent-modulus curves at room and elevated temperatures for annealed Ti-6Al-4V alloy extrusion. Fig 5.4.1.1.6(d)Typical tensile stress-strain curves (full range) for annealed Ti-6Al-4V sheet at room temperature. Fig 5.4.1.1.8(a)Best-fit S/N curves for unnotched Ti-6Al-4V annealed bar, longitudinal direction. Fig 5.4.1.1.8(b)Best-fit S/N curves for notched, Kt = 2.43, Ti-6Al-4V annealed bar, longitudinal direction. Fig 5.4.1.1.8(c)Best-fit S/N curves for unnotched annealed Ti-6Al-4V extrusion at room temperature, longitudinal direction. Fig 5.4.1.1.8(d)Best-fit S/N curves for notched, Kt = 2.8, annealed Ti-6Al-4V extrusion at room temperature, longitudinal direction. Fig 5.4.1.1.8(e)Best-fit S/N curves for notched, Kt = 2.8, annealed Ti-6Al-4V extrusion at 400 and 600°F, longitudinal direction. Fig 5.4.1.1.8(f)Best-fit S/N curves for unnotched Ti-6Al-4V annealed sheet, long transverse direction. Fig 5.4.1.1.8(g)Best-fit S/N curves for notched, Kt = 3.0, Ti-6Al-4V annealed sheet, longitudinal and long transverse direction. Fig 5.4.1.1.9Fatigue-crack-propagation data for 0.250-inch-thick Ti-6Al-4V mill-annealed titanium alloy plate with buckling restraint. [Reference 5.4.1.1.9] Fig 5.4.1.2.1Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of solution-treated and aged Ti-6Al-4V alloy (all products). Fig 5.4.1.2.2Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of solution-treated and aged Ti-6Al-4V alloy (all products). Fig 5.4.1.2.3Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of solution-treated and aged Ti-6Al-4V alloy (all products). Fig 5.4.1.2.4Effect of temperature on the tensile and compressive moduli (E and Ec) of solution-treated and aged Ti-6Al-4V alloy.
Table of Figures — Ti-6Al-4V (cont.)
Fig 5.4.1.2.6(a)Typical tensile stress-strain curves for solution-treated and aged Ti-6Al-4V alloy sheet at room and elevated temperatures. Fig 5.4.1.2.6(b)Typical compressive stress-strain curves for solution-treated and aged Ti-6Al-4V alloy sheet at room and elevated temperatures. Fig 5.4.1.2.6(c)Typical compressive tangent-modulus curves for solution-treated and aged Ti-6Al-4V alloy sheet. Fig 5.4.1.2.6(d)Typical compressive stress-strain curves for solution-treated and aged Ti-6Al-4V alloy sheet, long transverse direction. Fig 5.4.1.2.6(e)Typical compressive tangent-modulus curves for solution-treated and aged Ti-6Al-4V alloy sheet, long transverse direction. Fig 5.4.1.2.6(f)Typical tensile stress-strain curves for solution-treated and aged Ti-6Al-4V alloy plate at room and elevated temperatures. Fig 5.4.1.2.6(g)Typical compressive stress-strain and tangent-modulus curves for solution-treated and aged Ti-6Al-4V alloy plate. Fig 5.4.1.2.6(h)Typical tensile stress-strain curves (full range) for solution-treated and aged Ti-6Al-4V alloy at room and elevated temperatures. Fig 5.4.1.2.7Typical creep properties of solution-treated and aged Ti-6Al-4V alloy sheet for temperature range 600°F through 800°F. Fig 5.4.1.2.8(a)Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V sheet at room temperature, longitudinal direction. Fig 5.4.1.2.8(b)Best-fit S/N curves for notched, Kt = 2.8, solution-treated and aged Ti-6Al-4V sheet at room temperature, longitudinal direction. Fig 5.4.1.2.8(c)Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V sheet at 400°F and 600°F, longitudinal direction. Fig 5.4.1.2.8(d)Best-fit S/N curves for notched, Kt = 2.8, solution-treated and aged Ti-6Al-4V sheet at 400°F and 600°F, longitudinal direction. Fig 5.4.1.2.8(e)Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V sheet at 800°F and 900°F, longitudinal direction. Fig 5.4.1.2.8(f)Best-fit S/N curves for notched, Kt = 2.8, solution-treated and aged Ti-6Al-4V sheet at 800°F and 900°F, longitudinal direction. Fig 5.4.1.2.8(g)Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V plate at room temperature, longitudinal direction. Fig 5.4.1.2.8(h)Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V plate at room temperature, long transverse direction. Fig 5.4.1.2.8(i)Best-fit S/N curves for notched, Kt = 3.0, solution-treated and aged Ti-6Al-4V plate at room temperature, longitudinal direction.
Table of Figures — Ti-6Al-6V-2Sn (5.4.2) & Ti-4.5Al-3V-2Fe-2Mo (5.4.3)
Fig 5.4.2.0Effect of temperature on the physical properties of Ti-6Al-6V-2Sn alloy. Fig 5.4.2.1.1(a)Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of annealed Ti-6Al-6V-2Sn extrusion. Fig 5.4.2.1.1(b)Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of annealed Ti-6Al-6V-2Sn plate. Fig 5.4.2.1.2(a)Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of annealed Ti-6Al-6V-2Sn extrusion. Fig 5.4.2.1.2(b)Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of annealed Ti-6Al-6V-2Sn plate. Fig 5.4.2.1.3(a)Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of annealed Ti-6Al-6V-2Sn extrusion. Fig 5.4.2.1.3(b)Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of annealed Ti-6Al-6V-2Sn plate. Fig 5.4.2.1.6(a)Typical compressive stress-strain and tangent-modulus curves at room temperature for annealed Ti-6Al-6V-2Sn extrusion. Fig 5.4.2.1.6(b)Typical tensile stress-strain curve at room temperature for annealed Ti-6Al-6V-2Sn extrusion. Fig 5.4.2.1.6(c)Typical tensile stress-strain curve (full range) for annealed Ti-6Al-6V-2Sn sheet at room temperature. Fig 5.4.2.1.8(a)Best-fit S/N curves for annealed Ti-6Al-6V-2Sn plate and die forging, Kt = 1.0, longitudinal direction. Fig 5.4.2.1.8(b)Best-fit S/N curves for annealed Ti-6Al-6V-2Sn plate, Kt = 3.0, longitudinal direction. Fig 5.4.2.2.1Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of solution-treated and aged Ti-6Al-6V-2Sn plate. Fig 5.4.2.2.2Effect of temperature on compressive yield strength (Fcy) of solution-treated and aged Ti-6Al-6V-2Sn plate. Fig 5.4.3.1.6(a)Typical tensile stress-strain curves at room temperature for annealed Ti-4.5Al-3V-2Fe-2Mo alloy sheet. Fig 5.4.3.1.6(b)Typical compressive stress-strain and tangent-modulus curves at room temperature for annealed Ti-4.5Al-3V-2Fe-2Mo alloy sheet. Fig 5.4.3.1.6(c)Typical tensile stress-strain curves (full-range) for annealed Ti-4.5Al-3V-2Fe-2Mo alloy sheet. Fig 5.4.3.1.8(a)Best-fit S/N curves for unnotched Ti-4.5Al-3V-2Fe-2Mo annealed sheet. Fig 5.4.3.1.8(b)Best-fit S/N curves for notched, Kt = 2.8, Ti-4.5Al-3V-2Fe-2Mo annealed sheet. Fig 5.4.3.1.9Fatigue-crack-propagation data for 1 inch thick Ti-4.5Al-3V-2Fe-2Mo mill annealed titanium alloy plate.
5.4Alpha-Beta Titanium Alloys

The alpha-beta titanium alloys contain both alpha and beta phases at room temperature. The alpha phase is similar to that of unalloyed titanium but is strengthened by alpha stabilizing additions (e.g., aluminum). The beta phase is the high-temperature phase of titanium but is stabilized to room temperature by sufficient quantities of beta stabilizing elements such as vanadium, molybdenum, iron, or chromium. In addition to strengthening of titanium by the alloying additions, alpha-beta alloys may be further strengthened by heat treatment. The alpha-beta alloys have good strength at room temperature and for short times at elevated temperature. They are not noted for long-time creep strength. With the exception of annealed Ti-6Al-4V, these alloys are not recommended for cryogenic applications. The weldability of many of these alloys is poor because of the two-phase microstructure. However, some of them can be welded successfully with special precautions.

5.4.1Ti-6Al-4V
5.4.1.0Comments and Properties

Ti-6Al-4V is available in all mill product forms as well as castings and powder metallurgy forms. It can be used in either the annealed or solution treated plus aged (STA) conditions and is weldable. Useful temperature range is from −320 to 750°F. For maximum toughness, Ti-6Al-4V should be used in the annealed or duplex-annealed conditions whereas for maximum strength, the STA condition is used. The full strength potential for this alloy is not available in sections greater than 1 inch.

Manufacturing Considerations — Ti-6Al-4V alloy may be forged above the beta transus temperature using procedures to promote a high toughness material. The material is routinely finished below beta transus temperature for good combinations of fabricability, strength, ductility, and toughness. Elevated temperatures are usually used for form flat-rolled products although extensive forming may be accomplished at room temperature. Flat-rolled products are usually formed and used in the annealed condition although some forming in the STA condition is possible.

This alloy can be spot welded and is being fusion welded extensively in certain applications. Established titanium-welding techniques must be employed and special design considerations may be involved in fusion weldments. Stress-relief annealing after welding is recommended.

Environmental Considerations — Ti-6Al-4V can withstand prolonged exposure to temperatures up to 750°F without loss of ductility. Its toughness in the annealed condition is adequate at temperatures down to −320°F. (A special low interstitial grade may be used down to −423°F.) Ti-6Al-4V is resistant to hot-salt stress corrosion to about its maximum use temperature depending on exposure time and exposure stress. The material is marginally susceptible to aqueous chloride solution stress corrosion, but is considered to have good resistance to this reaction compared with other commonly used alloys. Under certain conditions, titanium, when in contact with cadmium, silver, mercury, or certain of their compounds, may become embrittled. Refer to MIL-S-5002 and MIL-STD-1568 for restrictions concerning applications with titanium in contact with these metals or their compounds.

Heat Treatment — This alloy is commonly specified in either the annealed condition or in the fully heat-treated condition. Annealing requires 1 hour at 1300°F followed by furnace cooling if maximum ductility is required.

The specified fully heat-treated, or solution-treated and aged condition for sheet is as follows: Solution treat at 1700°F for 5 to 25 minutes, quench in water. Age at 975°F for 4 to 6 hours, air cool.

For bars and forgings: Solution treat at 1700°F for 1 hour, quench in water. Age at 1000°F for 3 hours, air cool.

Specifications and Properties — Some material specifications for Ti-6Al-4V are shown in Table 5.4.1.0(a). Room-temperature mechanical properties for Ti-6Al-4V are shown in Tables 5.4.1.0(b) through (g). The effect of temperature on physical properties is shown in Figure 5.4.1.0.

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Table 5.4.1.0(a). Material Specifications for Ti-6Al-4V
SpecificationForm
AMS-T-9046Sheet, strip, and plate
MIL-T-9047aBar
AMS 4934Extrusion
AMS 4935Extrusion
AMS 4965Bar
AMS 4928Bar and die forging
AMS 4911Sheet, strip, and plate
AMS 4920Die forging
AMS 4962Investment casting
a Inactive for new design
5.4.1.1Annealed Condition

Elevated temperature curves for annealed Ti-6Al-4V are shown in Figures 5.4.1.1.1 through 5.4.1.1.5. Typical stress-strain curves at several temperatures are shown in Figures 5.4.1.1.6(a) through (c). Typical full-range stress-strain curves at room temperature are shown in Figure 5.4.1.1.6(d). Unnotched and notched fatigue data are shown in Figures 5.4.1.1.8(a) through (g). Fatigue crack-propagation data for plate are shown in Figure 5.4.1.1.9.

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Table 5.4.1.0(b). Design Mechanical and Physical Properties of Ti-6Al-4V Sheet, Strip, and Plate
SpecificationAMS 4911 and AMS-T-9046a, Comp. AB-1AMS-T-9046a, Comp. AB-1
FormSheetPlateSheet, strip, and plate
ConditionAnnealedSolution treated and aged
Thickness, in.≤0.18750.1875-
2.000		2.001-4.000≤0.18750.1875-
0.750		0.751-
1.000		1.001-
2.000
BasisABABABSSSS
Mechanical Properties:
Ftu, ksi:
L134139130b135130c137160160150145
LT134139130b138130c137160160150145
Fty, ksi:
L126131120125118123145145140135
LT126131120b131118129145145140135
Fcy, ksi:
L133138124129122127154150145···
LT135141130142128140162·········
Fsu, ksi8790798479841009387···
Fbru, ksi:
(e/D = 1.5)213d221d206d214d206d217d236248233···
(e/D = 2.0)272d283d260d276d260d274d286308289···
Fbry, ksi:
(e/D = 1.5)171c178d164d179d161d176d210210203···
(e/D = 2.0)208d217d194d212d191d209d232243235···
e, percent (S-basis):
L8e···10···10···5f866
LT8e···10···10···5f866
E, 103 ksi16.0
Ec, 103 ksi16.4
G, 103 ksi6.2
μ0.31
Physical Properties:
ω, lb/in.30.160
C, K, and αSee Figure 4.5.1.0
a MIL-T-9046 was canceled and superceded by AMS-T-9046
b The rounded T99 values are higher than specification values as follows: Ftu(L) = 131 ksi, Ftu(LT) = 132 ksi, and Fty(LT) = 123 ksi.
c The rounded T99 values are higher than specification values as follows: Ftu(L) = 133 ksi and Ftu(LT) = 133 ksi.
d Bearing values are “dry pin” values per Section 1.4.7.1.
e 8%—0.025 to 0.062 in. and 10%—0.063 in. and above.
f 5%—0.050 in. and above; 4%—0.033 to 0.049 in. and 3%—0.032 in. and below.
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Table 5.4.1.0(c1). Design Mechanical and Physical Properties of Ti-6Al-4V Bar. Not digitized in this pass.

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Table 5.4.1.0(c2). Design Mechanical and Physical Properties of Ti-6Al-4V Bar
SpecificationMIL-T-9047a
FormBar
ConditionAnnealed
Cross-sectional area, in.2≤48
Thickness or diameter, in.<0.5000.500-1.0001.001-2.0002.001-3.0003.001-4.0004.001-5.0005.001-6.000
BasisSABABABABABAB
Mechanical Properties:
Ftu, ksi:
L130130b142130b140130b138130135128133125131
LT130c130b144130b143130b142130b141130b139130b138
Fty, ksi:
L120120d134120d131120d128120125117122114119
LT120c120d134120d132120d131120d129120127119125
Fcy, ksi:
L124124138124135························
LT·······································
Fsu, ksi8080878086························
Fbru, ksi:
(e/D = 1.5)194194212194209························
(e/D = 2.0)244244266244262························
Fbry, ksi:
(e/D = 1.5)170170190170186························
(e/D = 2.0)197197220197215························
e, percent (S basis):
L1010···10···10···10···10···10···
LT10c10c···10c···10c···10···10···10···
ST·····················8···8···8···
RA, percent (S-basis):
L2525···25···25···25···20···20···
LT25c25c···25c···25c···25···20···20···
ST·····················15···15···15···
E, 103 ksi16.9
Ec, 103 ksi17.2
G, 103 ksi6.5
μ0.31
Physical Properties:
ω, lb/in.30.160
C, K, and αSee Figure 5.4.1.0
a Inactive for new design.
b S-basis. The rounded T99 values for Ftu are as follows: 0.500-1.000 (L) = 137 ksi and (LT) = 140 ksi, 1.001-2.000 (L) = 134 ksi and (LT) = 139 ksi, 2.001-3.000 (L) = 132 ksi and (LT) = 138 ksi, 3.001-4.000 (LT) = 136 ksi, 4.001-5.000 (LT) = 135 ksi, and 5.001-6.000 (LT) = 134 ksi.
c Applicable, providing LT dimension is ≥ 3.000 inches.
d S-basis. The rounded T99 values for Fty are as follows: 0.500-1.000 (L) and (LT) = 129 ksi, 1.001-2.000 (L) = 126 ksi and (LT) = 127 ksi, 2.001-3.000 (L) = 123 ksi and (LT) = 125 ksi, 3.001-4.000 (LT) = 123 ksi, and 4.001-5.000 (LT) = 121 ksi.
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Table 5.4.1.0(d). Design Mechanical and Physical Properties of Ti-6Al-4V Bar
SpecificationAMS 4965a and MIL-T-9047bMIL-T-9047b
FormRectangular barRound, square, and hexagon bar
ConditionSolution treated and aged
Width, in.0.501-
8.000		1.001-
4.000		4.001-
8.000		1.501-
4.000		4.001-
8.000		2.001-
4.000		4.001-
8.000		3.001-
8.000		4.001-
8.000		···············
Thickness, in.≤0.5000.501-1.0001.001-1.5001.501-2.0002.001-
3.000		3.001-
4.000		≤0.5000.501-
1.000		1.001-
1.500		1.501-
2.000		2.001-
3.000
BasisSSSSSSSSSSSSSS
Mechanical Properties:
Ftu, ksi:
L160155150150145145140135130165160155150140
LT160155150150145145140135130165160155150140
Fty, ksi:
L150145140140135135130125120155150145140130
LT150145140140135135130125120155150145140130
Fcy, ksi:
L··········································
LT··········································
Fsu, ksi92·······································
Fbru, ksi:
(e/D = 1.5)··········································
(e/D = 2.0)··········································
Fbry, ksi:
(e/D = 1.5)··········································
(e/D = 2.0)··········································
e, percent:
L101010101010101081010101010
LT101010101010101081010101010
RA, percent:
L2520202020202020152020202020
LT2520202020202020152020202020
E, 103 ksi16.9
Ec, 103 ksi17.2
G, 103 ksi6.2
μ0.31
Physical Properties:
ω, lb/in.30.160
C, K, and αSee Figure 5.4.1.0
a For AMS 4965, e and RA values may be different than those shown.
b Inactive for new design.
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Table 5.4.1.0(e). Design Mechanical and Physical Properties of Ti-6Al-4V Extrusion
SpecificationAMS 4935AMS 4934
FormExtrusion
ConditionAnnealedSolution treated and aged
Thickness or diameter, in.≤2.0002.001-3.000<0.5000.501-0.7500.751-1.0001.001-2.0002.001-3.000
BasisABABABABABSS
Mechanical Properties:
Ftu, ksi:
L130a137130b135155163151157147153140130
LTc130a139130b139155163151157147155140130
Fty, ksi:
L120124118122138147138143133140130120
LTc120a128120125138147138145133142130120
Fcy, ksi:
L128133124128147157147153142150139128
LTc129138······147157147155139152139128
Fsu, ksi8389······9499929689938579
Fbrud, ksi:
(e/D = 1.5)214226······243256237246231240220204
(e/D = 2.0)264278······311327303315295307281261
Fbryd, ksi:
(e/D = 1.5)180186······208222208216201212196182
(e/D = 2.0)210217······242257242250233245228210
e, percent (S-basis):
L10···10···6···6···6···66
LTc8···8···6···6···6···66
RA, percent (S-basis):
L20···20···12···12···12···1212
LTc15···15···12···12···12···1212
E, 103 ksi16.9
Ec, 103 ksi17.2
G, 103 ksi6.5
μ0.31
Physical Properties:
ω, lb/in.30.160
C, K, and αSee Figure 5.4.1.0
a S-basis. The rounded T99 values are higher than specification values as follows: Ftu (L) and (LT) = 132 ksi and Fty (LT) = 121 ksi.
b S-basis. The rounded T99 values are higher than specification values as follows: Ftu (L) = 132 ksi and Ftu (LT) = 136 ksi.
c Applicable, providing LT dimension is ≥2.500 inches.
d Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 5.4.1.0(f). Design Mechanical and Physical Properties of Ti-6Al-4V Die Forging
SpecificationAMS 4928AMS 4920
FormDie forging
ConditionAlpha-beta processed, annealedAlpha-beta or beta processed, annealed
Thickness, in.≤2.0002.001-4.0004.001-6.000≤2.0002.001-6.000
BasisSSSSS
Mechanical Properties:
Ftu, ksi:
L135130130130130
LT135a130a130130a130a
ST···130a130···130a
Fty, ksi:
L125120120120120
LT125a120a120120a120a
ST···120a120···120a
Fcy, ksi:
L···123123···123
LT···128128···128
ST···············
Fsu, ksi···7979···79
Fbru, ksi:
(e/D = 1.5)···203203···203
(e/D = 2.0)···257257···257
Fbry, ksi:
(e/D = 1.5)···171171···171
(e/D = 2.0)···201201···201
e, percent:
L10101088
LT10a10a108a8a
ST···10a8···8a
RA, percent:
L2525201515
LT20a20a2015a15a
ST···15a15···15a
E, 103 ksi16.9
Ec, 103 ksi17.2
G, 103 ksi6.5
μ0.31
Physical Properties:
ω, lb/in.30.160
C, K, and αSee Figure 5.4.1.0
a Applicable providing LT or ST dimension is ≥2.500 inches.
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Table 5.4.1.0(g). Design Mechanical and Physical Properties of Ti-6Al-4V Titanium Alloy Casting
SpecificationAMS 4962
FormHIP Casting
TemperAnnealed
Thickness, in.≤1.000
Location within castingDesignated area
BasisAB
Mechanical Properties:
Ftu, ksi125a128
Fty, ksi119122
Fcy, ksi······
Fsu, ksi······
Fbru, ksi:
(e/D = 1.5)······
(e/D = 2.0)······
Fbry, ksi:
(e/D = 1.5)······
(e/D = 2.0)······
e, percent (S-basis)5···
E, 103 ksi16.9
Ec, 103 ksi16.9
G, 103 ksi···
μ···
Physical Properties:
ω, lb/in.3···
C, Btu/(lb)(°F)···
K, Btu/[(hr)(ft2)(°F)/ft]···
α, 10−6 in./in./°F···
a S-basis. The rounded T99 value is 126 ksi.
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C

α

Figure 5.4.1.0. Effect of temperature on the physical properties of Ti-6Al-4V alloy (wrought products).

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Figure 5.4.1.1.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of annealed Ti-6Al-4V alloy (all wrought products).

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Figure 5.4.1.1.2. Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of annealed Ti-6Al-4V alloy (all wrought products).

Figure 5.4.1.1.3. Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of annealed Ti-6Al-4V alloy (all wrought products).

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Figure 5.4.1.1.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of annealed Ti-6Al-4V alloy sheet and bar.

Figure 5.4.1.1.5. Effect of temperature on the elongation of annealed Ti-6Al-4V alloy sheet and bar.

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Figure 5.4.1.1.6(a). Typical tensile stress-strain curves at cryogenic, room, and elevated temperatures for annealed Ti-6Al-4V alloy extrusion.

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Figure 5.4.1.1.6(b). Typical compressive stress-strain curves at room and elevated temperatures for annealed Ti-6Al-4V alloy extrusion.

Figure 5.4.1.1.6(c). Typical compressive tangent-modulus curves at room and elevated temperatures for annealed Ti-6Al-4V alloy extrusion.

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Figure 5.4.1.1.6(d). Typical tensile stress-strain curves (full range) for annealed Ti-6Al-4V sheet at room temperature.

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Figure 5.4.1.1.8(a). Best-fit S/N curves for unnotched Ti-6Al-4V annealed bar, longitudinal direction.

Correlative Information for Figure 5.4.1.1.8(a)

Product Form: Bar, 1.25 inch diameter

Properties: TUS 137 ksi, TYS 129 ksi, RT

Specimen Details: Unnotched
0.280 inch diameter

Surface Conditions:
0 ksi mean stress—32 RMS ground
47 ksi mean stress—100 RMS machined
70 ksi mean stress—32 RMS ground and 100 RMS machined

Reference: 5.4.1.1.8(a)

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

No. of Heats/Lots: Not specified

Equivalent Strain Equation:
Log Nf = 19.18 − 7.55 log Smax, Sm = 0
= 5.70 − 0.94 Log (Smax − 82.3), Sm = 47
= 7.08 − 2.18 Log (Smax − 99.6), Sm = 70

Sample Size: 134
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Figure 5.4.1.1.8(b). Best-fit S/N curves for notched, Kt = 2.43, Ti-6Al-4V annealed bar, longitudinal direction.

Correlative Information for Figure 5.4.1.1.8(b)

Product Form: Bar, 1 inch diameter

Properties: TUS 150 ksi, TYS 143 ksi, RT

Specimen Details: 60° V-notch
0.025 inch notch radius
0.260 inch test section diameter at notch

Surface Condition: RMS 100 machined

Reference: 5.4.1.1.8(a)

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

No. of Heats/Lots: Not specified

Equivalent Strain Equation:
Log Nf = 24.1 − 10.7 log Seq
Seq = Smax(1−R)0.49
Std. Error of Estimate, Log (Life) = 0.677
Standard Deviation, Log (Life) = 0.920
R2 = 46%

Sample Size: 46

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.1.8(c). Best-fit S/N curves for unnotched annealed Ti-6Al-4V extrusion at room temperature, longitudinal direction.

Correlative Information for Figure 5.4.1.1.8(c)

Product Form: Extrusion, 0.300 and 0.560 inch thick

Properties: TUS 143 ksi, TYS 127 ksi, RT

Specimen Details: Unnotched
1.50 inch gross width
0.75 inch net width
4.00 inch net section radius

Surface Conditions: RMS 63

Reference: 5.4.1.1.8(b)

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

No. of Heats/Lots: Not specified

Equivalent Strain Equation:
Log Nf = 24.8 − 9.6 log (Smax)
Std. Error of Estimate, Log (Life) = 0.41
Standard Deviation, Log (Life) = 0.81
R2 = 75%

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 5.4.1.1.8(d). Best-fit S/N curves for notched, Kt = 2.8, annealed Ti-6Al-4V extrusion at room temperature, longitudinal direction.

Correlative Information for Figure 5.4.1.1.8(d)

Product Form: Extrusion, 0.300 and 0.560 inch thick

Properties: TUS 143 ksi, TYS 127 ksi, RT

Specimen Details: Notched, hole type, Kt = 2.8
0.250 inch hole diameter
1.50 inch gross width
1.25 inch net width

Surface Conditions: RMS 63

Reference: 5.4.1.1.8(b)

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

No. of Heats/Lots: Not specified

Equivalent Strain Equation:
Log Nf = 14.8 − 5.8 log (Seq − 14)
Seq = Smax(1−R)0.50
Std. Error of Estimate, Log (Life) = 0.41
Standard Deviation, Log (Life) = 0.86
R2 = 78%

Sample Size: 40

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.1.8(e). Best-fit S/N curves for notched, Kt = 2.8, annealed Ti-6Al-4V extrusion at 400 and 600°F, longitudinal direction.

Correlative Information for Figure 5.4.1.1.8(e)

Product Form: Extrusion, 0.300 and 0.560 inch thick

Properties: TUS 112 ksi, TYS 92 ksi, 400°F
TUS 101 ksi, TYS 77 ksi, 600°F

Specimen Details: Notched, hole type, Kt = 2.8
0.250 inch hole diameter
1.250 inch net width
1.500 inch gross width

Surface Conditions: RMS 63

Reference: 5.4.1.1.8(b)

Test Parameters:
Loading – Axial
Frequency – 1800 cpm
Temperature – 400°F and 600°F
Environment – Air

No. of Heats/Lots: Not specified

Equivalent Strain Equation:
Log Nf = 21.0 − 9.18 log (Seq)
Seq = Smax(1−R)0.62
Std. Error of Estimate, Log (Life) = 0.50
Standard Deviation, Log (Life) = 0.89
R2 = 68%

Sample Size: 47

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.1.8(f). Best-fit S/N curves for unnotched Ti-6Al-4V annealed sheet, long transverse direction.

Correlative Information for Figure 5.4.1.1.8(f)

Product Form: Sheet, 0.063, 0.070, 0.078 inch thick

Properties: TUS 147–152 ksi, TYS 136–143 ksi, RT

Specimen Details: Unnotched, 0.375 inch width

Surface Conditions: Machined to 32 RMS, lightly polished with 400 grit emery paper

Reference: 5.4.1.1.8(c)

Test Parameters:
Loading – Axial
Frequency – 10–95 Hz
Temperature – RT
Environment – Air

No. of Heats/Lots: 3

Equivalent Strain Equation:
Log Nf = 12.59 − 4.89 log (Seq − 82.8)
Seq = Smax(1−R)0.29
Std. Error of Estimate, Log (Life) = 0.62
Standard Deviation, Log (Life) = 0.88
R2 = 50.6%

Sample Size: 47

[Caution: The equivalent strain model may provide unrealistic life predictions for strain ratios and ranges beyond those represented above.]
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Figure 5.4.1.1.8(g). Best-fit S/N curves for notched, Kt = 3.0, Ti-6Al-4V annealed sheet, longitudinal and long transverse direction.

Correlative Information for Figure 5.4.1.1.8(g)

Product Form: Sheet, 0.063, 0.070, 0.078 inch thick

Properties: TUS 145–152 ksi, TYS 136–146 ksi, RT

Specimen Details: Notched, Kt = 3.0
0.487 inch net section

Surface Conditions: Machined to 32 RMS, lightly polished with 400 grit emery paper

Reference: 5.4.1.1.8(c)

Test Parameters:
Loading – Axial
Frequency – 10–95 Hz
Temperature – RT
Environment – Air

No. of Heats/Lots: 3

Equivalent Strain Equation:
Log Nf = 19.28 − 8.25 log (Seq)
Seq = Smax(1−R)0.57
Std. Error of Estimate, Log (Life) = 0.53
Standard Deviation, Log (Life) = 0.87
R2 = 62.5%

Sample Size: 141

[Caution: The equivalent strain model may provide unrealistic life predictions for strain ratios and ranges beyond those represented above.]
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Figure 5.4.1.1.9. Fatigue-crack-propagation data for 0.250-inch-thick Ti-6Al-4V mill-annealed titanium alloy plate with buckling restraint. Specimen Thickness: 0.250 inch; Specimen Width: 9.6, 16, 32 inches; Specimen Type: M(T); Environment: 50% R.H.; Temperature: RT; Orientation: L-T. [Reference 5.4.1.1.9]

5.4.1.2Solution-Treated and Aged Condition

Elevated temperature curves for solution-treated and aged alloy are shown in Figures 5.4.1.2.1 through 5.4.1.2.4. Typical tensile and compressive stress-strain and tangent-modulus curves are shown in Figures 5.4.1.2.6(a) through (g). Typical full-range stress-strain curves at several temperatures up to 1000°F are shown in Figure 5.4.1.2.6(h). A nomograph of typical creep properties of solution-treated and aged sheet for the temperature range 600°F through 800°F is shown in Figure 5.4.1.2.7. Fatigue data at room and elevated temperatures are shown in Figures 5.4.1.2.8(a) through (i).

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Figure 5.4.1.2.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of solution-treated and aged Ti-6Al-4V alloy (all products).

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Figure 5.4.1.2.2. Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of solution-treated and aged Ti-6Al-4V alloy (all products).

Figure 5.4.1.2.3. Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of solution-treated and aged Ti-6Al-4V alloy (all products).

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Figure 5.4.1.2.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of solution-treated and aged Ti-6Al-4V alloy.

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Figure 5.4.1.2.6(a). Typical tensile stress-strain curves for solution-treated and aged Ti-6Al-4V alloy sheet at room and elevated temperatures.

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Figure 5.4.1.2.6(b). Typical compressive stress-strain curves for solution-treated and aged Ti-6Al-4V alloy sheet at room and elevated temperatures.

Figure 5.4.1.2.6(c). Typical compressive tangent-modulus curves for solution-treated and aged Ti-6Al-4V alloy sheet.

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Figure 5.4.1.2.6(d). Typical compressive stress-strain curves for solution-treated and aged Ti-6Al-4V alloy sheet, long transverse direction.

Figure 5.4.1.2.6(e). Typical compressive tangent-modulus curves for solution-treated and aged Ti-6Al-4V alloy sheet, long transverse direction.

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Figure 5.4.1.2.6(f). Typical tensile stress-strain curves for solution-treated and aged Ti-6Al-4V alloy plate at room and elevated temperatures.

Compressive Stress-Strain

Compressive Tangent Modulus

Figure 5.4.1.2.6(g). Typical compressive stress-strain and tangent-modulus curves for solution-treated and aged Ti-6Al-4V alloy plate.

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Figure 5.4.1.2.6(h). Typical tensile stress-strain curves (full range) for solution-treated and aged Ti-6Al-4V alloy at room and elevated temperatures.

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Figure 5.4.1.2.7Not digitized in this pass.

Figure 5.4.1.2.7. Typical creep properties of solution-treated and aged Ti-6Al-4V alloy sheet for temperature range 600°F through 800°F.

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Figure 5.4.1.2.8(a). Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V sheet at room temperature, longitudinal direction.

Correlative Information for Figure 5.4.1.2.8(a)

Product Forms: Sheet, 0.063 inch and 0.125 inch thick

Properties: TUS 166–177 ksi, TYS 153–167 ksi, RT

Specimen Details: Unnotched
Ref. 5.4.3.2.8(a)
Specimen details not available
Ref. 5.4.3.2.8(b)
1.000 inch net width
8.000 inch test section radius
3.00 inch gross width

Surface Conditions:
Ref. 5.4.3.2.8(a). Edges finished with a crocus cloth.
Ref. 5.4.3.2.8(b). Machined specimens were cleaned with methyl ethyl ketone. Edges polished with number 1 and 00 grit emery paper, recleaned with methyl ethyl ketone.

References: 5.4.1.2.8(a) and (b)

Test Parameters:
Loading – Axial
Frequency –
Ref. 5.4.3.2.8(a), not specified
Ref. 5.4.3.2.8(b), 1500–2200 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 4

Equivalent Strain Equation:
Log Nf = 14.29 − 4.91 log (Seq − 30.6)
Seq = Smax(1−R)0.42
Std. Error of Estimate, Log (Life) = 0.48
Standard Deviation, Log (Life) = 0.90
R2 = 72%

Sample Size: 99

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.2.8(b). Best-fit S/N curves for notched, Kt = 2.8, solution-treated and aged Ti-6Al-4V sheet at room temperature, longitudinal direction.

Correlative Information for Figure 5.4.1.2.8(b)

Product Forms: Sheet, 0.063 inch and 0.125 inch thick

Properties: TUS 166–177 ksi, TYS 153–167 ksi, RT

Specimen Details: Notched, hole type, Kt = 2.8
0.9375 inch net width
1.000 inch gross width
8.000 inch test section radius
0.0625 inch-diameter hole

Surface Conditions: Machined specimens were cleaned with methyl ethyl ketone. Edges polished with number 1 and 00 grit emery paper and recleaned with methyl ethyl ketone.

Reference: 5.4.1.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 1500–2200 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 3

Equivalent Strain Equation:
Log Nf = 10.87 − 3.80 log (Seq − 24.0)
Seq = Smax(1−R)0.50
Std. Error of Estimate, Log (Life) = 0.43
Standard Deviation, Log (Life) = 0.98
R2 = 81%

Sample Size: 87

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.2.8(c). Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V sheet at 400°F and 600°F, longitudinal direction.

Correlative Information for Figure 5.4.1.2.8(c)

Product Forms: Sheet, 0.063 inch and 0.125 inch thick

Properties: TUS 142–143 ksi, TYS 117–121 ksi, 400°F
TUS 125–134 ksi, TYS 102–113 ksi, 600°F

Specimen Details: Unnotched
Ref. 5.4.3.2.8(a)
Specimen details not available
Ref. 5.4.3.2.8(b)
1.000 inch gross width
8.000 inch test section radius
3.00 inch gross width
0.9375 inch net width

Surface Conditions:
Ref. 5.4.3.2.8(a). Edges finished with a crocus cloth
Ref. 5.4.3.2.8(b). Machined specimens were cleaned with methyl ethyl ketone. Edges polished with number 1 and 00 grit emery paper, recleaned with methyl ethyl ketone.

References: 5.4.1.2.8(a) and (b)

Test Parameters:
Loading – Axial
Frequency –
Ref. 5.4.3.2.8(a), not specified
Ref. 5.4.3.2.8(b), 1500–2200 cpm
Temperature – 400°F and 600°F
Environment – Air

No. of Heats/Lots: 4

Equivalent Strain Equation:
Log Nf = 14.7 − 5.31 log (Seq − 21.8)
Seq = Smax(1−R)0.54
Std. Error of Estimate, Log (Life) = 0.58
Standard Deviation, Log (Life) = 0.93
R2 = 61%

Sample Size: 163

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.2.8(d). Best-fit S/N curves for notched, Kt = 2.8, solution-treated and aged Ti-6Al-4V sheet at 400°F and 600°F, longitudinal direction.

Correlative Information for Figure 5.4.1.2.8(d)

Product Forms: Sheet, 0.063 inch and 0.125 inch thick

Properties: TUS 142–143 ksi, TYS 117–121 ksi, 400°F
TUS 129–133 ksi, TYS 103–105 ksi, 600°F

Specimen Details: Notched, hole type, Kt = 2.8
1.000 inch gross width
8.000 inch test section radius
0.0625 inch-diameter hole
0.9375 inch net width

Surface Conditions: Machined specimens were cleaned with methyl ethyl ketone. Edges polished with number 1 and 00 grit emery paper and recleaned with methyl ethyl ketone.

Reference: 5.4.1.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 1500–2200 cpm
Temperature – 400°F and 600°F
Environment – Air

No. of Heats/Lots: 3

Equivalent Stress Equation:
Log Nf = 10.64 − 3.77 log (Seq − 20.9)
Seq = Smax(1−R)0.51
Std. Error of Estimate, Log (Life) = 0.42
Standard Deviation, Log (Life) = 0.93
R2 = 80%

Sample Size: 175

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.2.8(e). Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V sheet at 800°F and 900°F, longitudinal direction.

Correlative Information for Figure 5.4.1.2.8(e)

Product Forms: Sheet, 0.063 inch and 0.125 inch thick

Properties: TUS 120–125 ksi, TYS 93–96 ksi, 800°F
TUS 110–111 ksi, TYS 84–86 ksi, 900°F

Specimen Details: Unnotched
1.000 inch gross width
8.000 inch test section radius
3.00 inch gross width
0.9375 inch net width

Surface Conditions: Machined specimens were cleaned with methyl ethyl ketone. Edges polished with number 1 and 00 grit emery paper and recleaned with methyl ethyl ketone.

References: 5.4.1.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 1500–2200 cpm
Temperature – 800°F and 900°F
Environment – Air

No. of Heats/Lots: 3

Equivalent Stress Equation:
Log Nf = 17.34 − 6.61 log (Seq)
Seq = Smax(1−R)0.50
Std. Error of Estimate, Log (Life) = 0.51
Standard Deviation, Log (Life) = 0.99
R2 = 73%

Sample Size: 154

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.2.8(f). Best-fit S/N curves for notched, Kt = 2.8, solution-treated and aged Ti-6Al-4V sheet at 800°F and 900°F, longitudinal direction.

Correlative Information for Figure 5.4.1.2.8(f)

Product Forms: Sheet, 0.063 inch and 0.125 inch thick

Properties: TUS 120–124 ksi, TYS 93–96 ksi, 800°F
TUS 110–111 ksi, TYS 84–88 ksi, 900°F

Specimen Details: Notched, hole type, Kt = 2.8
1.000 inch gross width
8.000 inch test section radius
0.0625 inch-diameter hole
0.9375 inch net width

Surface Conditions: Machined specimens were cleaned with methyl ethyl ketone. Edges polished with number 1 and 00 grit emery paper and recleaned with methyl ethyl ketone.

Reference: 5.4.1.2.8(b)

Test Parameters:
Loading – Axial
Frequency – 1500–2200 cpm
Temperature – 800°F and 900°F
Environment – Air

No. of Heats/Lots: 3

Equivalent Stress Equation:
Log Nf = 11.75 − 4.45 log (Seq − 15.0)
Seq = Smax(1−R)0.62
Std. Error of Estimate, Log (Life) = 0.43
Standard Deviation, Log (Life) = 0.96
R2 = 79%

Sample Size: 173

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.2.8(g). Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V plate at room temperature, longitudinal direction.

Correlative Information for Figure 5.4.1.2.8(g)

Product Form: Plate, 1.00 inch

Properties: TUS 158 ksi, TYS 149 ksi, RT
TUS 155 ksi, TYS 145 ksi, RT

Specimen Details: Unnotched, rounded
Uniform gage: reduced section radius of curvature, inch —; diameter, inch 0.195
Hourglass: reduced section radius of curvature, inch 3.25; diameter, inch 0.250

Surface Condition: Longitudinally polished with No. 000 emery paper removing all circumferential marks.

References: 5.4.1.2.8(c) and (d)

Test Parameters:
Loading – Axial
Frequency – 1,800–18,000 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 2

Equivalent Stress Equation:
Log Nf = 24.6 − 9.35 log (Seq)
Seq = Smax(1−R)0.48
Std. Error of Estimate, Log (Life) = 0.39
Standard Deviation, Log (Life) = 0.83
R2 = 79%

Sample Size: 49

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.1.2.8(h). Best-fit S/N curves for unnotched solution-treated and aged Ti-6Al-4V plate at room temperature, long transverse direction.

Correlative Information for Figure 5.4.1.2.8(h)

Product Form: Plate, 0.50 inch thick

Properties: TUS 173 ksi, TYS 164 ksi, RT

Specimen Details: Unnotched, flat hourglass
10 inch reduced section radius of curvature
1 inch net section width
0.156 inch net section thickness

Surface Conditions: Machined to 63 RMS

Reference: 5.4.1.2.8(d)

Test Parameters:
Loading – Axial
Frequency – Unspecified
Temperature – RT
Environment – Air

No. of Heats/Lots: 1

Maximum Stress Equation:
Log Nf = 47.9 − 20.2 log (Smax)
Std. Error of Estimate, Log (Life) = 0.33
Standard Deviation, Log (Life) = 0.89
R2 = 87%

Sample Size: 14
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Figure 5.4.1.2.8(i). Best-fit S/N curves for notched, Kt = 3.0, solution-treated and aged Ti-6Al-4V plate at room temperature, longitudinal direction.

Correlative Information for Figure 5.4.1.2.8(i)

Product Form: Plate, 1.025 and 0.750 inch thick

Properties: TUS 155 ksi, TYS 145 ksi, RT (unnotched)
TUS 187 ksi, TYS —, RT (notched)

Specimen Details: Circumferentially notched, Kt = 3.0
Gross diameter, inch: 0.195 (Ref. (c)), 0.430 (Ref. (e))
Net section, inch: 0.136 (Ref. (c)), 0.300 (Ref. (e))
Notch radius, r, inch: 0.005 (Ref. (c)), 0.016 (Ref. (e))
Flank angle, ω: 60° (Ref. (c)), 60° (Ref. (e))

Surface Condition:
Ref. (c) notch made with light finishing cuts
Ref. (e) notch polished in lathe

References: 5.4.1.2.8(c) and (e)

Test Parameters:
Loading – Axial
Frequency – 1,800–18,000 cpm
Temperature – RT
Environment – Air

No. of Heats/Lots: 2

Equivalent Stress Equation:
Log Nf = 14.4 − 5.51 log (Seq)
Seq = Smax(1−R)0.58
Std. Error of Estimate, Log (Life) = 0.24
Standard Deviation, Log (Life) = 0.81
R2 = 92%

Sample Size: 31

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
5.4.2Ti-6Al-6V-2Sn
5.4.2.0Comments and Properties

Ti-6Al-6V-2Sn alloy is similar to Ti-6Al-4V alloy in many respects but has higher strength and deeper hardenability (i.e., use of thicker sections possible). A variety of mill product forms are available including billet, bar, plate, sheet, strip, and extrusions and these may be used in either the annealed or the solution-treated and aged (STA) conditions. The maximum strength is developed in the STA condition in sections up to about 2 inches in thickness.

Manufacturing Considerations — To ensure optimum mechanical properties in Ti-6Al-6V-2Sn forgings, at least 50 percent reduction should be done at temperatures below the beta transus temperature (i.e., <1735°F). The Ti-6Al-6V-2Sn is readily formable in the annealed condition. In the sheet or plate forms the alloy is generally used in the annealed condition, although the alloy is capable of heat treatment to higher strength levels with some loss of toughness. When the Ti-6Al-6V-2Sn sheet and plate are hot formed at any temperature over 1000°F and air cooled, the material should be stabilized by reheating to 1000°F followed by air cooling. Welding is not usually recommended although limited weld joining operations are possible if the assembly is amenable to post-weld thermal treatments for the restoration of ductility to the weld and heat-affected zones.

Environmental Considerations — While the short-time elevated-temperature properties and stability of Ti-6Al-6V-2Sn alloy are good, creep strength above 650°F and long-term stability at temperatures above 800°F are not. The material ages during prolonged exposures around 800°F and above, particularly when under stress. Oxidation resistance of Ti-6Al-6V-2Sn is satisfactory in short-term exposures to 1000°F. The material is nearly equivalent to the Ti-6Al-4V alloy in terms of hot-salt and aqueous chloride solution stress-corrosion resistance. Under certain conditions, titanium, when in contact with cadmium, silver, mercury, or certain of their compounds, may become embrittled. Refer to MIL-S-5002 and MIL-STD-1568 for restrictions concerning applications with titanium in contact with these metals or their compounds.

Heat Treatment — This alloy is commonly specified in either the annealed condition or the solution-treated and aged condition. The solution-treated and aged condition is as follows: Solution treat at 1625°F for ½ to 1 hour, quench in water. Age at 1000±25°F for 4 to 8 hours, air cool.

Specifications and Properties — Material specifications for Ti-6Al-6V-2Sn are shown in Table 5.4.2.0(a). Room-temperature mechanical properties are shown in Tables 5.4.2.0(b) through (e). The effect of temperature on physical properties is shown in Figure 5.4.2.0.

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Table 5.4.2.0(a). Material Specifications for Ti-6Al-6V-2Sn
SpecificationForm
AMS-T-9046Sheet, strip, and plate
AMS 4979Bar and forging
MIL-T-81556, AMS-T-81556Extruded bar and shapes
AMS 4971Bar and forging
AMS 4978Bar and forging
AMS 4918Sheet, strip, and plate
5.4.2.1Annealed Condition

Elevated temperature curves for annealed condition are shown in Figures 5.4.2.1.1(a) through 5.4.2.1.3(b). Typical stress-strain and tangent-modulus curves for this condition are shown in Figures 5.4.2.1.6(a) and (b). A typical full range tensile stress-strain curve is shown in Figure 5.4.2.1.6(c). Unnotched and notched fatigue data are presented in Figures 5.4.2.1.8(a) and (b).

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Table 5.4.2.0(b). Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Sheet, Strip, and Plate
SpecificationAMS-T-9046, Comp. AB-3, and AMS 4918AMS-T-9046, Comp. AB-3
FormSheet, strip, and plate
ConditionAnnealedSolution treated and aged
Thickness, in.<0.18750.1875-
0.500		0.501-
1.000		1.001-
1.500		1.501-
2.000		2.001-
4.000		≤0.18750.1875-
1.500		1.501-
2.500		2.501-
4.000
BasisABSSSSSSSSS
Mechanical Properties:
Ftu, ksi:
L155160150150150150145170170160150
LT155150150150150150145170170160150
Fty, ksi:
L145a152140140140140135160160150140
LT145a154140140140140135160160150140
Fcy, ksi:
L······139142146148······170······
LT······151147141136······170······
Fsu, ksi······91939595······101······
Fbru, ksi:
(e/D = 1.5)······236241247250······264······
(e/D = 2.0)······294303312317······324······
Fbry, ksi:
(e/D = 1.5)······193196199202······237······
(e/D = 2.0)······215223234240······266······
e, percent (S-basis):
L10b···1010101088866
LT8b···888866866
E, 103 ksi16.0
Ec, 103 ksi16.4
G, 103 ksi6.2
μ0.31
Physical Properties:
ω, lb/in.30.164
C, K, and αSee Figure 5.4.2.0
a The rounded T99 values are higher than specification values as follows: Fty (L) = 147 ksi, Fty (LT) = 149 ksi.
b Longitudinal <0.025 in. = 8 percent. Long transverse < 0.025 in. = 6 percent.
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Table 5.4.2.0(c). Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Bar
SpecificationAMS 4978AMS 4971 and AMS 4979
FormBarBar and forging
ConditionAir-cool annealedaSolution treated and aged
Thickness or diameter, in.≤1.5001.501-
3.000		3.001-
4.000		≤1.0001.001-
2.000		2.001-
3.000		3.001-
4.000
BasisABABABSSSS
Mechanical Properties:
Ftu, ksi:
L144150139145136142175170155150
LTb147152143148140145175170155150
STb························155150
Fty, ksi:
L131138126132123129160155145140
LTb136141131136127132160155145140
STb························145140
Fcy, ksi:
L······························
LTb······························
STb······························
Fsu, ksi······························
Fbru, ksi:
(e/D = 1.5)······························
(e/D = 2.0)······························
Fbry, ksi:
(e/D = 1.5)······························
(e/D = 2.0)······························
e, percent (S-basis):
L10···10···10···8888
LTb8···8···8···6666
STb······8···8·········66
RA, percent (S-basis):
L20···20···15···20202020
LTb15···15···15···15151515
STb······15···15·········1515
E, 103 ksi16.0
Ec, 103 ksi16.4
G, 103 ksi6.2
μ0.31
Physical Properties:
ω, lb/in.30.164
C, K, and αSee Figure 5.4.2.0
a 1300 to 1350°F for 1-3 hours, air cool to room temperature.
b Applicable, providing LT or ST dimension is ≥2.500 inches.
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Table 5.4.2.0(d). Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Forging
SpecificationAMS 4978
FormForging
ConditionAnnealed
Thickness, or diameter, in.≤2.0002.001-4.000
BasisSS
Mechanical Properties:
Ftu, ksi:
L150145
LTa150145
STa···145
Fty, ksi:
L140135
LTa140135
STa···135
Fcy, ksi:
L······
LTa······
STa······
Fsu, ksi······
Fbru, ksi:
(e/D = 1.5)······
(e/D = 2.0)······
Fbry, ksi:
(e/D = 1.5)······
(e/D = 2.0)······
e, percent:
L1010
LTa88
STa···7
RA, percent:
L2020
LTa1515
STa1515
E, 103 ksi16.0
Ec, 103 ksi16.4
G, 103 ksi6.2
μ0.31
Physical Properties:
ω, lb/in.30.164
C, K, and αSee Figure 5.4.2.0
a Applicable, providing LT or ST dimension is ≥2.500 inches.
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Table 5.4.2.0(e). Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Extruded Bar and Shapes
SpecificationMIL-T-81556 & AMS-T-81556, Comp. AB-3
FormExtruded bar and shapes
ConditionAnnealedSolution treated and aged
Thickness or diameter, in.≤2.0002.001-
3.000		3.001-
4.000		0.188-
0.500		0.501-
1.500		1.501-
2.500		2.501-
4.000
BasisABSSSSSS
Mechanical Properties:
Ftu, ksi:
L142148145140170165160150
LT141148145140170165160150
Fty, ksi:
L129135135130160155150140
LT128135135130160155150140
Fcy, ksi:
L137144140135165160155145
LT136142140135165160155145
Fsu, ksi9397··················
Fbrua, ksi:
(e/D = 1.5)218229··················
(e/D = 2.0)268281··················
Fbrya, ksi:
(e/D = 1.5)196203··················
(e/D = 2.0)227235··················
e, percent (S-basis):
L10···10108888
LT8···886666
RA, percent (S-basis):
L20···202015151515
LT15···151512121212
E, 103 ksi16.0
Ec, 103 ksi16.4
G, 103 ksi6.2
μ0.31
Physical Properties:
ω, lb/in.30.164
C, K, and αSee Figure 5.4.2.0
a Bearing values are “dry pin” values per Section 1.4.7.1.
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C

α

Figure 5.4.2.0. Effect of temperature on the physical properties of Ti-6Al-6V-2Sn alloy.

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Figure 5.4.2.1.1(a). Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of annealed Ti-6Al-6V-2Sn extrusion.

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Figure 5.4.2.1.1(b). Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of annealed Ti-6Al-6V-2Sn plate.

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Figure 5.4.2.1.2(a). Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of annealed Ti-6Al-6V-2Sn extrusion.

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Figure 5.4.2.1.2(b). Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of annealed Ti-6Al-6V-2Sn plate.

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Figure 5.4.2.1.3(a). Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of annealed Ti-6Al-6V-2Sn extrusion.

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Figure 5.4.2.1.3(b). Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of annealed Ti-6Al-6V-2Sn plate.

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Compressive Stress-Strain

Compressive Tangent Modulus

Figure 5.4.2.1.6(a). Typical compressive stress-strain and tangent-modulus curves at room temperature for annealed Ti-6Al-6V-2Sn extrusion.

Figure 5.4.2.1.6(b). Typical tensile stress-strain curve at room temperature for annealed Ti-6Al-6V-2Sn extrusion.

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Figure 5.4.2.1.6(c). Typical tensile stress-strain curve (full range) for annealed Ti-6Al-6V-2Sn sheet at room temperature.

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Figure 5.4.2.1.8(a). Best-fit S/N curves for annealed Ti-6Al-6V-2Sn plate and die forging, Kt = 1.0, longitudinal direction.

Correlative Information for Figure 5.4.2.1.8(a)

Product Form: Plate, 1.57 inch thick; die forging, thickness not specified

Properties: TUS 154.5 ksi, TYS 148.5 ksi, RT
TUS 159.9 ksi, TYS 151.5 ksi, RT

Specimen Details: Unnotched
0.195 inch diameter
Unspecified diameter from forging

Surface Condition: RMS 32
Unspecified from forging

References: 5.4.1.2.8(c) and 5.4.2.1.8

Test Parameters:
Loading – Axial
Frequency – Unspecified
Temperature – RT
Atmosphere – Air

No. of Heats/Lot: 3

Equivalent Stress Equation:
Log Nf = 20.90 − 8.10 log (Seq)
Seq = Sa + 0.41 Sm
Std. Error of Estimate, Log (Life) = 23.5 (1/Seq)
Standard deviation, Log (Life) = 0.884
R2 = 89%

Sample Size: 38

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.2.1.8(b). Best-fit S/N curves for annealed Ti-6Al-6V-2Sn plate, Kt = 3.0, longitudinal direction.

Correlative Information for Figure 5.4.2.1.8(b)

Product Form: Plate, 1.57 inch thick

Properties: TUS 154.6 ksi, TYS 148.5 ksi, RT

Specimen Details: V-Groove, Kt = 3.0
0.195 inch gross diameter
0.136 inch net diameter
0.005 inch root radius
60° flank angle

Surface Condition: RMS 32

References: 5.4.1.2.8(c)

Test Parameters:
Loading – Axial
Frequency – Unspecified
Temperature – RT
Atmosphere – Air

No. of Heats/Lot: 1

Equivalent Stress Equation:
Log Nf = 8.31 − 2.73 log (Seq − 16.9)
Seq = Sa + 0.37 Sm
Std. Error of Estimate, Log (Life) = 8.87 (1/Seq)
Standard Deviation, Log (Life) = 0.947
R2 = 92%

Sample Size: 32

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
5.4.2.2Solution-Treated and Aged Condition

Elevated temperature curves are shown in Figures 5.4.2.2.1 and 5.4.2.2.2.

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Figure 5.4.2.2.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of solution-treated and aged Ti-6Al-6V-2Sn plate.

Figure 5.4.2.2.2. Effect of temperature on compressive yield strength (Fcy) of solution-treated and aged Ti-6Al-6V-2Sn plate.

5.4.3Ti-4.5Al-3V-2Fe-2Mo
5.4.3.0Comments and Properties

Ti-4.5Al-3V-2Fe-2Mo alloy is a beta rich alpha-beta titanium composition developed for improved hot formability and fatigue resistance. The alloy consists of fine microstructure and has excellent superplastic formability at temperatures below 1475°F. This alloy also shows significantly improved cold formability over Ti-6Al-4V. Although this alloy was originally developed for flat product applications in the annealed condition, it has expanded into other areas such as billets, bars, and forgings. This alloy has been reported to possess significantly better hardenability than Ti-6Al-4V.

Manufacturing Considerations — Superplastic forming of Ti-4.5Al-3V-2Fe-2Mo at temperatures between 1380°F–1425°F is recommended. At these forming temperatures the formation of alpha case is not observed and the thickness of oxygen enriched layer is generally less than 0.001 inch. Diffusion bonding at 1425°F is possible but slightly higher temperatures than the superplastic forming temperature, e.g., 1470°F, are recommended to ensure perfect bonding. Ti-4.5Al-3V-2Fe-2Mo is weldable by standard titanium welding techniques. This alloy shows an increase in hardness in the welded zone but with limited ductility loss. Stress relief annealing after welding is recommended.

Environmental Considerations — Ti-4.5Al-3V-2Fe-2Mo exhibits significantly improved resistance to aqueous chloride solution stress-corrosion cracking over Ti-6Al-4V. The alloy is nearly equivalent to Ti-6Al-4V hot-salt stress corrosion cracking.

Heat Treatment — This alloy is commonly specified in the annealed condition, but is also used in the solution-treated and aged condition. Annealing: 1325°F for a time commensurate with product thickness. Annealing requires 1 hour at 1475°F followed by furnace cooling if maximum ductility is required. The solution treated and aged conditions commonly employed are as follows: Solution treat at 1500–1580°F for ½–1 hour followed by air cooling. Age at 900–1060°F followed by air cooling.

Specifications and Properties — Some material specifications for Ti-4.5Al-3V-2Fe-2Mo are shown in Table 5.4.3.0(a). Room temperature mechanical properties and physical properties are shown in Table 5.4.3.0(b) through (d).

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Table 5.4.3.0(a). Material Specification for Ti-4.5Al-3V-2Fe-2Mo Titanium Alloy
SpecificationForm
AMS 4899Sheet, Strip, and Plate
AMS 4964Bars, Wire, Forgings, and Rings
5.4.3.1Anneal Condition

Typical tensile stress-strain and full-range stress-strain curves are shown in Figures 5.4.3.1.6(a) and (b). Compressive stress-strain and tangent modulus curves are shown in Figure 5.4.3.1.6(c). Unnotched and notched fatigue data as well as fatigue crack propagation data are presented in Figures 5.4.3.1.8(a), (b) and 5.4.3.1.9.

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Table 5.4.3.0(b). Design Mechanical and Physical Properties of Ti-4.5Al-3V-2Fe-2Mo Titanium Alloy Sheet
SpecificationAMS 4899
FormSheet
ConditionAnnealed
Thickness, in.0.025 to 0.063, exclusive0.063 to 0.187, exclusive
BasisABAB
Mechanical Properties:
Ftu, ksi:
L134a145134b144
LT134a147134b144
Fty, ksi:
L126a134126b132
LT126a137126b134
Fcy, ksi:
L128136130139
LT131143132141
Fsuc, ksi:
LT90999198
Fbrud, ksi: LT
(e/D = 1.5)196215207223
(e/D = 2.0)258283276296
Fbryd, ksi: LT
(e/D = 1.5)157171165176
(e/D = 2.0)190207198210
e, percent (S-basis):
L8···10···
LT8···10···
E, 103 ksi16.0
Ec, 103 ksi16.2
G, 103 ksi···
μ···
Physical Properties:
ω, lb/in.30.164
C, Btu/(lb)(°F)0.12
K, Btu/[(hr)(ft2)(°F)/ft]4.00
α, 10−6 in./in./°F5.17 (60-932°F)
a S-basis. Rounded T99 values for thickness range 0.025 - 0.063 in. are as follows; Ftu (L) and (LT) = 140 ksi, Fty (L) = 129 ksi and Fty (LT) = 131 ksi.
b S-basis. Rounded T99 values for thickness range 0.063 - 0.187 in. are as follows; Ftu (L) = 141 ksi, Ftu (LT) = 140 ksi, Fty (L) = 128 ksi and Fty (LT) = 127 ksi.
c Determined in accordance with ASTM B769.
d Bearing values are “dry pin” values per Section 1.4.7.1.
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Table 5.4.3.0(c). Design Mechanical and Physical Properties of Ti-4.5Al-3V-2Fe-2Mo Titanium Alloy Bar
SpecificationAMS 4964
FormBar
ConditionAnnealed
Thickness, in.≤2.0002.001-4.0004.001-6.000
BasisABABAB
Mechanical Properties:
Ftu, ksi:
L135139130a135130133
LT (S-basis)135···130···130···
Fty, ksi:
L124128119123119123
LT (S-basis)125···120···120···
Fcy, ksi:
L124128············
LT (S-basis)··················
Fsub, ksi
L-R8184············
Fbruc, ksi:
(e/D = 1.5)··················
(e/D = 2.0)··················
Fbryc, ksi:
(e/D = 1.5)··················
(e/D = 2.0)··················
e, percent (S-basis):
L10···10···10···
LT10d···10d···10···
Red. in Area, percent (S-basis):
L25···20···20···
LT20d···20d···20···
E, 103 ksi16.0
Ec, 103 ksi16.2
G, 103 ksi···
μ···
Physical Properties:
ω, lb/in.30.164
C, Btu/(lb)(°F)0.12
K, Btu/[(hr)(ft2)(°F)/ft]4.00
α, 10−6 in./in./°F5.17 (60-932°F)
a Rounded T99 for Ftu = 131 ksi.
b Determined in accordance with ASTM B769.
c Bearing values are “dry pin” values per Section 1.4.7.1.
d Applicable, providing LT dimension is no less than 2.500 inches.
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Figure 5.4.3.1.6(a). Typical tensile stress-strain curves at room temperature for annealed Ti-4.5Al-3V-2Fe-2Mo alloy sheet.

Compressive Stress-Strain

Compressive Tangent Modulus

Figure 5.4.3.1.6(b). Typical compressive stress-strain and tangent-modulus curves at room temperature for annealed Ti-4.5Al-3V-2Fe-2Mo alloy sheet.

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Figure 5.4.3.1.6(c). Typical tensile stress-strain curves (full-range) for annealed Ti-4.5Al-3V-2Fe-2Mo alloy sheet.

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Figure 5.4.3.1.8(a). Best-fit S/N curves for unnotched Ti-4.5Al-3V-2Fe-2Mo annealed sheet.

Correlative Information for Figure 5.4.3.1.8(a)

Product Form: 0.059, 0.118, 0.157 inch thick

Properties: TUS 148–149 ksi, TYS 135–138 ksi, RT

Specimen Details: Unnotched, 0.252 inch width

Surface Conditions: Lightly polished with 400 grit emery paper

References: 5.4.3.1.8

Test Parameter:
Loading – Axial
Frequency – 10 Hz
Temperature – RT
Environment – Air

No. of Heats: 3

Equivalent Stress Equation:
Log Nf = 7.72 − 2.59 log (Seq − 114.68)
Seq = Smax(1−R)0.13
Std. Error of Estimate, Log (Life) = 0.40
Standard Deviation, Log (Life) = 0.60
Adjusted R2 = 56.5%

Sample Size: 43

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.3.1.8(b). Best-fit S/N curves for notched, Kt = 2.8, Ti-4.5Al-3V-2Fe-2Mo annealed sheet.

Correlative Information for Figure 5.4.3.1.8(b)

Product Form: 0.059, 0.118, 0.157 inch thick

Properties: TUS 148–149 ksi, TYS 135–138 ksi, RT

Specimen Details: Notched, Kt = 2.8
0.466 inch net width

Surface Conditions: HF/HNO3 pickled

References: 5.4.3.1.8

Test Parameter:
Loading – Axial
Frequency – 10 Hz
Temperature – RT
Environment – Air

No. of Heats: 3

Equivalent Stress Equation:
Log Nf = 7.22 − 1.96 log (Seq − 44.05)
Seq = Smax(1−R)0.65
Std. Error of Estimate, Log (Life) = 0.24
Standard Deviation, Log (Life) = 0.47
Adjusted R2 = 72.9%

Sample Size: 41

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]
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Figure 5.4.3.1.9. Fatigue-crack-propagation data for 1 inch thick Ti-4.5Al-3V-2Fe-2Mo mill annealed titanium alloy plate. Specimen Thickness: 0.25 inch; Specimen Width: 2.0 inches; Specimen Type: C(T); Environment: 50% RH; Temperature: RT; Orientation: L-T.

References
  • 5.4.1.1.8(a)“Fatigue Evaluation of Ti-6Al-4V Bar Stock”, Sikorsky Aircraft, Report No. SER-50631 (MIL-HDBK-5 Source M-459) (March 1970).
  • 5.4.1.1.8(b)Brockett, R. M., and Gottbrath, J. A., “Development of Engineering Data on Titanium Extrusion for Use in Aerospace Design”, Lockheed-California Co., Technical Report AFML-TR-67-189 (July 1967) (MCIC 69807, MIL-HDBK-5 Source M-543).
  • 5.4.1.1.8(c)Rhode, T. M., and Ertel, P. W., “Constant Amplitude Fatigue Life Data for Notched and Unnotched Annealed Ti-6Al-4V Sheet”, AFWAL-TR-88-4081, January 1988 (MIL-HDBK-5 Source M-696).
  • 5.4.1.1.9Fedderson, C. E., and Hyler, W. S., “Fracture and Fatigue-Crack Propagation Characteristics of ¼-Inch Mill Annealed Ti-6Al-4V Titanium Alloy Plate”, Report No. G9706, Battelle, Columbus, Ohio (1971).
  • 5.4.1.2.8(a)“Fatigue Strength Properties for Heat Treated Ti-4Al-30Mo-1V and Ti-6Al-4V Titanium Alloys (LP-69-132 and LP-69-129)”, North American Aviation, Report No. TFD-60-521 (July 18, 1960) (MCIC 65737).
  • 5.4.1.2.8(b)“Determination of Design Data for Heat Treated Titanium Alloy Sheet”, Lockheed-Georgia Co., Report No. ASD-TDR-62-335, Vol. 3, Contract No. AF33(616)-6346 (May 1962) (MCIC 90172).
  • 5.4.1.2.8(c)Sommer, A. W., and Martin, G. R., “Design Allowables for Titanium Alloys”, North American Rockwell, AFML-TR-69-161 (June 1969) (MCIC 75727).
  • 5.4.1.2.8(d)Marrocco, A. G., “Fatigue Characteristics of Ti-6Al-4V and Ti-6Al-6V-2Sn Sheet and Plate”, Grumman Aircraft Engineering Corp., EMG-81 (November 18, 1968) (MCIC 76303).
  • 5.4.1.2.8(e)Sargent, M. R., “Fatigue Characteristics of Ti-6Al-4V Plate and Forgings (SWIP)”, General Dynamics, FGT-3218 (September 22, 1965) (MIL-HDBK-5 Source M-457).
  • 5.4.2.1.8Marrocco, A. G., “Evaluation of Ti-6Al-4V and Ti-6Al-6V-2Sn Forgings”, Grumman Aircraft Engineering Corporation, EMG-82, November 1968 (MIL-HDBK-5 Source M-522).
  • 5.4.3.1Unpublished data from NKK, January 2001, (MIL-HDBK-5 Source M-914).
Other MIL-HDBK-5 Chapters
Chapter 1 (General) Chapter 2 (Steel) Chapter 3 (Aluminum) Chapter 4 (Magnesium) Chapter 6 (Heat-Resistant Alloys)

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