Knovel sample book

Click to View Calculation Example

Example 2.1: Liquid Discharge through a Hole in a Tank Input Data: Tank pressure above liquid: Pressure outside hole: Liquid density: Liquid level above hole: Hole diameter: Excess Head Loss Factors: Entrance: Exit: Others: TOTAL:

0.1 barg O barg 490 kg/m**3 2m 10 mm 0.5 1 O 1.5

Calculated Results: Hole area:

7.9E-05 m**2

Equation terms: Pressure term: Height term: Velocity coefficient: Exit velocity: Mass flow:

I

-20.4082 m**2/s**2 -19.6 m**2/s**2 1.25 5.7 m/s 0.22 kg/s

Figure 2.8. Spreadsheet output for Example 2.1: Liquid discharge through a hole in the tank.

Example 2.2: Liquid Trajectory from a Hole. Consider again Example 2.1. A stream of liquid discharging from a hole in a tank will stream out of the tank and impact the ground at some distance away from the tank. In some cases the liquid stream could shoot over any diking designed to contain the liquid. (a) If the hole is 3 m above the ground, how far will the stream of liquid shoot away from the tank? (b) At what point on the tank will the maximum discharge distance occur? What is this distance? Solution: (a) The geometry of the tank and the stream is shown in Figure 2.9. The distance away from the tank the liquid stream will impact the ground is given by s = v2t

FIGURE 2.9. Tank geometry for Example 2.2.

(2.1.32)

Click to View Calculation Example

Example 2.2a: Liquid Trajectory from a Hole Input Data: Liquid velocity at hole: Height of hole above ground:

5.7 m/s 3m

Calculated Results: Time to reach ground: Horizontal distance from hole:

I

0.78 s 4.46 m

I |

FIGURE 2.10. Spreadsheet output for Example 2.2a: Liquid trajectory from a hole. where s is the distance (length), V2 is the discharge velocity (distance/time), and t is the time (time). The time, £, for the liquid to fall the distance h, is given by simple acceleration due to gravity, t=fikTg

(2.1.33)

These two equations are implemented in the spreadsheet shown in Figure 2.10. The velocity is obtained from Example 2.1. The horizontal distance the stream will impact the ground is 4.46 m away from the base of the tank. Solution (b) The solution to this problem is found by solving Eq. (2.1.10) for V2. The algebraic result is substituted into Eq. (2.1.32), along with Eq. (2.1.33). The resulting equation for s is differentiated with respect to h. The expression is set to zero to determine the maximum, and solved for h. The result is

*.l(w+«i] A SP )

<"•*>

where H is the total liquid height above ground level (length). Equations (2.1.33) and (2.1.34) are then substituted into Eq. (2.1.32) for s to determine the maximum distance. The result is

, = ^MM

(2.1.35)

!/"1X IfPg = O, i.e. the tank is vented to the atmosphere, then the maximum discharge distance, from Eq. (2.1.34) occurs when the hole is located at h = H/2. As the tank pressure increases, the location of the hole moves up and eventually reaches the top of the liquid. These equations are conveniently implemented using a spreadsheet, as shown in Figure 2.11. For this case, the hole location for the maximum discharge conditions is at 3.54 m above the ground. The maximum discharge distance is 4.48 m. This example demonstrates the important point that the incident is selected based on the objective of the study. If the objective of the study is to determine the maximum discharge rate from the tank, then a hole is specified at the bottom of the tank. If the study objective is to determine the maximum discharge distance, then Eq. (2.1.34) is used to place the location of the hole.

Click to View Calculation Example

Example 2,2b: Maximum Discharge Distance from a Hole in a Tank Input Data: Tank pressure above liquid: Max. liquid height in tank: Density of liquid: Excess Head Loss Factors: Entrance: Exit: Others: TOTAL:

0.1 bang 5m 490 kg/m**3 0.5 1 O 1.5

Calculated Results: Hole height for max. distance:

3.54 m <- Above ground

Actual height: Discharge distance:

3.54 m <-Cannot exceed liquid height 4.48 m

I

I |

FIGURE 2.11. Spreadsheet output for Example 2.2b: Liquid trajectory from a hole.

Example 2.3: Liquid Discharge through a Piping System. Figure 2.12 shows a transfer system between two tanks; The system is used to transfer a hazardous liquid. The pipe is commercial steel pipe with an internal diameter of 100-mm with a total length of 10 m. The piping system contains two standard, flanged 90° elbows and a standard, full-line gate valve. A 3-kW pump with an efficiency of 70% assists with the liquid transfer. The maximum fluid height in the supply tank is 3 m, and the elevation change between the two tanks is as shown in Figure 2.12. Data: Fluid density (p) = 1600 kg/m3 Fluid viscosity (JJL) = 1.8 X 10~3 kg/m s Solution: The postulated scenario is the detachment of the pipe at its connection to the second tank. The objective of the calculation is to determine the maximum dis-

Standard Gate Valve

Pump

Pipe Detaches here FIGURE 2.12. Example 2.3: Liquid discharge through a piping system.

charge rate of liquid from the pipe. Liquid would also discharge from the hole in the tank previously connected to the pipe, but this is not considered in this calculation. The 2-Kmethod, in conjunction with Eq. (2.1.10) will be used. A trial and error solution method is required, as discussed in the section on liquid discharges. A spreadsheet solution is best, with the output shown in Figure 2.13 Click to View Calculation Example

Example 2.3: Liquid Discharge through a Piping System Input Data: !Guessed discharge velocity: Fluid density: Fluid viscosity: Pipe diameter: Pipe roughness: Point 1 pressure: Point 2 pressure: Point 1 velocity: Point 1 height: Point 2 height: Pipe length: Net pump energy: Fittings: Elbows: Valves: Inlet: Exit:

Number 2 1 1 1

7.74 m/s

T

1600 kg/m**3 0.0018 kg/m*s 0.1 m 0.046 mm O Pa O Pa O m/s 13 m Om 10 m -2.1 kw K1 800 300 160 O

K-inifinity 0.25 0.1 0.5 1

Calculated Results: Reynolds No: Friction factor: Pipe area:

687702 0.0043 0.000103 0.0079 m**2

Fittings and pipe K factors: Elbows: 0.629 Valves: 0.126 Inlet: 0.500 Exit: 1.000 Pipe: 1.718 TOTAL: 3.974 Mechanical energy balance terms (m**2/s**2): Pressure: 0.00 Height: -127.49 Point 1 velocity: 0.00 Fittings/pipe: 118.92 Pump: -21.60 TOTAL: -30.17 [Calculated Discharge Velocity: 7.77 m/s Velocity Difference: -0.03081 m/s [Resulting mass discharge rate:

97.61 kg/s

""") |

FIGURE 2.13. Spreadsheet output for Example 2.3: Liquid discharge through a piping system.

Click to View Calculation Example Example 2.4: Gas Discharge through a Hole Input Data: Heat capacity ratio of gas: Hole size: Upstream pressure: Dowstream pressure: Temperature: Gas molecular weight:

1.15 10 mm 5.01 bar abs 1.01 bar abs 298 K 44

Excess Head Loss Factors: Entrance: 0.5 Exit: 1 Others: 0_ TOTAL: 1.5 Calculated Results: Hole area: Upstream gas density: Expansion factor, Y:

7.9E-05 m**2 8.90 kg/m**3 0.614

Actual pressure ratio:

0.80 <-- Must be greater than sonic pressure ratio below to insure sonic flow.

Heat capacity ratio, k: Sonic pressure ratios: Choked pressure:

1.2 0.536 2.33

1.4 1.67 0.575 0.618 2.13 1.91 bar

Mass flow:

0.0861

0.0892

!interpolated mass flow:

0.085342 kg/s

0.0925 kg/s I

FIGURE 2.14. Spreadsheet output for Example 2.4: Gas discharge through a hole.

rate by two methods (1) using the orifice discharge equation, Eq. (2.1.17) and assuming a hole size equal to the pipe diameter, and (2) using a complete adiabatic flow model. For nitrogen, k = 1.4. Solution: The problem will be solved using two methods (1) a hole discharge and (2) an adiabatic pipe flow solution. Method 1: Hole discharge.Assume a discharge coefficient, C0 = 0.85. The cross-sectional area of the pipe is ^ = ^-=1.96 x 1(T5 m2 4 Also,

M I

2

V'*"7"""

= 334

-y ° I 2 \<14/"'

Equation (2.1.17) is used to estimate the mass discharge rate, I kg Mf ^choked

=C

D^^f

2 V4+1^*'1* (-j-fi)

Click to View Calculation Example

Example 2.5: Gas Discharge through a Piping System Input Data: Heat capacity ratio, k: Temperature: Molecular weight of gas: Point 1 pressure: Point 2 pressure: Pipe diameter: Pipe length: Pipe roughness:

1.4 298 28 2101000 101325 0.005 10 0.046

K Pa Pa m m mm

Fittings: Number Elbows: Valves: Inlet: Exit:

4 2 O 1

Kjnfinite 0.4 0.1 0.5 1

Calculated Results: Pipe area: Initial gas density: Pipe friction factor:

2E-05 m**2 23.74 kg/m**3 0.009214

Fittings and pipe K factors: Elbows: 1.60 Valves: 0.20 Inlet: 0.00 Exit: 1.00 Pipe: 73.71 TOTAL: 76.51 Ln(K): 4.34 Expansion factor:

0.72

Heat capacity ratio.k 1.2 1.4 1.67 (P1-P2)/P1: 0.906 0.914 0.929 P-choked: 197534.4 180552.4 148466.5 Pa Mass flow:

0.015273 0.015341 0.015468 kg/s

[Interpolated mass flow:

0.015341 kg/s

|

FIGURE 2.15. Spreadsheet output for Example 2.5: Gas discharge through a piping system. The mass discharge rate calculated assuming a hole is more than 5 times larger than the result from the adiabatic pipe flow method. Both methods require about the same effort, but the adiabatic flow method produces a much more realistic result. The entire adiabatic pipe flow method is readily implemented using a spreadsheet. The spreadsheet solution is shown in Figure 2.15. Example 2.6: Two-Phase Flashing Flow through a Pipe. Propane is stored in a vessel at its vapor pressure of 95 bar gauge and a temperature of 298 K. Determine the discharge mass flux if the propane is discharged through a pipe to atmospheric pressure. Assume a discharge coefficient of 0.85 and a critical pipe length of 10 cm. Determine the mass flux for the following pipe lengths:

Basic Concepts

T

apping the sidewalk repeatedly with his cane, a blind man makes his way along a busy street, keeping a fixed distance from the wall of a building on his right—hence also a safe distance from the curb and the traffic whizzing by on his left. Emitting a train of shrill beeps, a bat deftly avoids the obstacles in its path and unerringly homes in on a succession of tiny nocturnal insects that are its prey. Just as unerringly, the pilot of a supersonic fighter closes in on a possible enemy intruder, hidden behind a cloud bank a hundred and fifty miles away (Fig. 1). How do they do it? Underlying each of these remarkable feats is a very simple and ancient principle: that of detecting objects and determining their distances (range) from the echoes they reflect. The chief difference is that, in the cases of the blind man and the bat, the echoes are those of sound waves, whereas in the case of the fighter, they are echoes of radio waves. In this chapter, we will briefly review the fundamental 1 radar concept and see in a little more detail how it is applied to such practical uses as detecting targets and measuring their ranges and directions. We will then take up a second important concept: that of determining the relative speed or range rate of the reflecting object from the shift in the radio frequency of the reflected waves relative to that of the transmitted waves, the phenomenon known as the doppler effect. We will see how, by sensing doppler shifts, a radar can not only measure range rates but also differentiate between echoes from moving targets and the clutter of echoes from the ground and objects on it which are stationary. We will further learn how, rather than rejecting the echoes from the ground, the radar can use them to produce high resolution maps of the terrain (Fig. 2). 3

Click for high-quality image

1.

Looking out through a streamlined faring in the nose of a supersonic fighter, a small but powerful radar enables the pilot to home in on an intruder hidden behind or in a cloud bank a hundred and fifty miles away.

1. Radar = Radio Detection And Ranging.

Click for high-quality image

2.

Rather than rejecting echoes from the ground, as when searching for airborne targets, the radar may use them to produce real-time high-resolution maps of the terrain.

PART I Overview of Airborne Radar

Radio Detection

3.

Most objects—aircraft, ships, vehicles, buildings, features of the terrain, etc.—reflect radio waves, much as they do light (Fig. 3). Radio waves and light are, in fact, the same thing—the flow of electromagnetic energy. The sole difference is that the frequencies of light are very much higher. The reflected energy is scattered in many directions, but a detectable portion of it is generally scattered back in the direction from which it originally emanated. At the longer wavelengths (lower frequencies) used by many shipboard and ground based radars, the atmosphere is almost completely transparent. And it is nearly so even at the shorter wavelengths used by most airborne radars. By detecting the reflected radio waves, therefore, it is possible to “see” objects not only at night, as well as in the daytime, but through haze, fog, or clouds. In its most rudimentary form, a radar consists of five elements: a radio transmitter, a radio receiver tuned to the transmitter’s frequency, two antennas, and a display (Fig. 4). To detect the presence of an object (target), the transmitter generates radio waves, which are radiated by one of the antennas. The receiver, meanwhile, listens for the “echoes” of these waves, which are picked up by the other antenna. If a target is detected, a blip indicating its location appears on the display. In practice, the transmitter and receiver generally share a common antenna (Fig. 5).

That radio waves are reflected by aircraft, buildings, and other objects is repeatedly demonstrated by the multiple images (ghosts) we sometimes see on TV screens.

Transmitter Antennas

Receiver Display 4.

In rudimentary form, a radar consists of five basic elements.

Transmitter

Receiver Antenna 5.

τ Power

Transmitted Pulse

T Time 6.

To keep transmission from interfering with reception, the radar usually transmits the radio waves in pulses and listens for the echoes in between.

In practice, a single antenna is generally time-shared by the transmitter and the receiver.

To avoid problems of the transmitter interfering with reception, the radio waves are usually transmitted in pulses, and the receiver is turned off (“blanked”) during transmission (Fig. 6). The rate at which the pulses are transmitted is called the pulse repetition frequency (PRF). So that the radar can differentiate between targets in different directions as well as detect targets at greater ranges, the antenna concentrates the radiated energy into a narrow beam. To find a target, the beam is systematically swept through 4

CHAPTER 1 Basic Concepts

the region in which targets are expected to appear. The path of the beam is called the search scan pattern. The region covered by the scan is called the scan volume or frame; the length of time the beam takes to scan the complete frame, the frame time (Fig. 7). Incidentally, in the world of radar the term target is broadly used to refer to almost anything one wishes to detect: an aircraft, a ship, a vehicle, a man-made structure on the ground, a specific point in the terrain, rain (weather radars), aerosols, even free electrons . Like light, radio waves of the frequencies used by most airborne radars travel essentially in straight lines. Consequently, for a radar to receive echoes from a target, the target must be within the line of sight (Fig. 8).

8.

7.

Typical search scan pattern for a fighter application. Number of bars and width and position of frame may be controlled by the operator.

9.

As a distant target approaches, its echoes rapidly grow stronger. But only when they emerge from the background of noise and/or ground clutter will they be detected.

To be seen by most radars, a target must be within the line of sight.

Even then, the target will not be detected unless its echoes are strong enough to be discerned above the background of electrical noise that invariable exists in the output of a receiver, or, above the background of simultaneously received echoes from the ground (called ground clutter) which in some situations may be substantially stronger than the noise. The strength of a target’s echoes is inversely proportional to the target’s range to the fourth power (1/R4). Therefore, as a distant target approaches, its echoes rapidly grow stronger (Fig. 9). The range at which they become strong enough to be detected depends upon a number of factors. Among the most important are these: • Power of the transmitted waves • Fraction of the time, τ/T, during which the power is transmitted • Size of the antenna • Reflecting characteristics of the target • Length of time the target is in the antenna beam during each search scan • Number of search scans in which the target appears • Wavelength of the radio waves • Strength of background noise or clutter 5

PART I Overview of Airborne Radar

Much as the sunlight reflected from a car on a distant highway scintillates and fades, the strength of the echoes scattered in the radar’s direction varies more or less at random (Fig. 10). Because of this and the randomness of the background noise, the range at which a given target is detected by the radar will not always be the same. Nevertheless, the probability of its being detected at any particular range (or by the time it reaches a given range) can be predicted with considerable certainty. By optimizing those parameters over which one has control, a radar can be made small enough to fit in the nose of a fighter yet detect small targets at ranges on the order of a hundred miles. Radars of larger aircraft (Fig. 11) can detect targets at greater ranges.

10. Since the target return scintillates and fades, and noise varies randomly, detection ranges must be expressed in terms of probabilities.

Click for high-quality image

11. Radars in larger aircraft (e.g. AWACS) can detect small aircraft at ranges out to 200 to 400 nmi.

Determining Target Position

R = 1 (Round-Trip Time) X (Speed of Light) 2 10 = 1 X s X 300,000,000 m/s 2 1,000,000 = 1.5 km 12. Transit time is measured in millionths of a second (µs). A transit time of 10 µs corresponds to a range of 1.5 kilometers.

In most applications, it is not enough merely to know that a target is present. It is also necessary to know the target’s location—its distance (range) and direction (angle). Measuring Range. Range may be determined by measuring the time the radio waves take to reach the target and return. Radio waves travel at essentially a constant speed— the speed of light. A target’s range, therefore, is half the round-trip (two-way) transit time times the speed of light (Fig. 12). Since the speed of light is high—300 million meters per second—ranging times are generally expressed in millionths of a second (microseconds). A round-trip transit time of 10 microseconds, for example, corresponds to a range of 1.5 kilometers. The transit time is most simply measured by observing the time delay between transmission of a pulse and reception of the echo of that pulse (Fig. 13)—a technique called pulse-delay ranging. So that echoes of closely spaced targets won’t overlap and appear to be the return from a single target, the width of the pulse, τ, is generally limited to a microsecond or less. To radiate enough energy to detect distant targets, however, pulses must often be made very much 6

CHAPTER 1 Basic Concepts

wider. This dilemma may be resolved by compressing the echoes after they are received. One method of compression, called chirp, is to linearly increase the frequency of each transmitted pulse throughout its duration (Fig. 14). The received echoes are then passed through a filter which introduces a delay that decreases with increasing frequency, thereby compressing the received energy into a narrow pulse. Another method of compression is to mark off each pulse into narrow segments and, as the pulse is transmitted, reverse the phase of certain segments according to a special code (Fig. 15). When each received echo is decoded, its energy is compressed into a pulse the width of a single segment. With either technique, resolution of a foot or so may be obtained without limiting range. Resolutions of a few hundred feet, though, are more typical. Radars which transmit a continuous wave (CW radars) or which transmit their pulses too close together for pulsedelay ranging, measure range with a technique called frequency-modulation (FM) ranging. In it, the frequency of the transmitted wave is varied and range is determined by observing the lag in time between this modulation and the corresponding modulation of the received echoes (Fig. 16).

Transmitter

Frequency

τ Time

14. Chirp pulse compression modulation. The transmitter’s frequency increases linearly throughout the duration, τ, of each pulse.

Transmitted Pulse 0°

0°

0°

0°

0° 180° 180°

0°

0° 180°

0°

0°

15. In binary phase-modulation pulse compression, the phases of certain segments of each transmitted pulse are reversed according to a special code. Decoding the received echoes compress them to the width of a single segment.

ho Ec

∆f = k t

t’s

t =

1 ∆f k

R=

c t 2

ge

t

∆f Ta r

ed itt Tr an sm

Frequency

Si

gn

al

R

Time 16. In FM ranging, the frequency of the transmitted signal is varied linearly and the instantaneous difference, ∆f, between the transmitter’s frequency and the target echo‘s frequency is sensed. The round-trip transit time, t, to the target, hence the target’s range, R, is proportional to this difference.

Measuring Direction. In most airborne radars, direction is measured in terms of the angle between the line of sight to the target and a horizontal reference direction such as north, or the longitudinal reference axis of the aircraft’s fuselage. This angle is usually resolved into its horizontal and vertical components. The horizontal component is called azimuth; the vertical component, elevation (Fig. 17). 7

17. Angle between the fuselage reference axis and the line of sight to a target is usually resolved into azimuth and elevation components.

PART I Overview of Airborne Radar

Where both azimuth and elevation are required, as for detecting and tracking an aircraft, the beam is given a more or less conical shape (Fig. 18a). This is called a pencil beam. Typically it is three or four degrees wide. Where only azimuth is required, as for long-range surveillance, mapping, or detecting targets on the ground, the beam may be given a fan shape (Fig. 18b). Angular position may be measured with considerably greater precision than the width of the beam. For example, if echoes are received during a portion of the azimuth search scan extending from 30˚ to 34˚, the target’s azimuth may be concluded to be very nearly 32˚. With more sophisticated processing of the echoes, such as used for automatic tracking, the angle can be determined more accurately.

a. Pencil Beam 3 - 4°

b. Fan Beam

18. For detecting and tracking aircraft, a pencil beam is used. For long-range surveillance, mapping, or detecting targets on the ground, a fan beam may be used.

Automatic Tracking. Frequently it is desired to follow the movements of one or more targets while continuing to search for more. This may be done in a mode of operation called track-while-scan. In it, the position of each target of interest is tracked on the basis of the periodic samples of its range, range rate, and direction obtained when the antenna beam sweeps across it (Fig. 19).

Click for high-quality image

20. For tasks requiring precision, such as predicting the flight path of a tanker in preparation for refueling, a single-target tracking mode is generally provided.

19. In track-while-scan, any number of targets may be tracked simultaneously on the basis of samples of each target‘s range, range rate, and direction obtained when the beam sweeps across it in the course of the search scan.

Track-while-scan is ideal for maintaining situation awareness. It provides sufficiently accurate target data for launching guided missiles, which can correct their trajectories after launch, and is particularly useful for launching missiles in rapid succession against several widely separated targets. But it does not provide accurate enough data for predicting the flight path of a target for a fighter’s guns or of a tanker for refueling (Fig. 20). For such uses, the antenna is trained on the target continuously in a single-target track mode. To keep the antenna trained on a target in this mode, the radar must be able to sense its pointing errors. This may be 8

CHAPTER 1 Basic Concepts

done in several ways. One is to rotate the beam so that its central axis sweeps out a small cone about the pointing axis (boresight line) of the antenna (Fig. 21). If the target is on the boresight line (i.e., no error exists), its distance from the center of the beam will be the same throughout the conical scan, and the amplitude of the received echoes will be unaffected by the scan. However, since the strength of the beam falls off toward its edges, if a tracking error exists, the echoes will be modulated by the scan. The amplitude of the modulation indicates the magnitude of the tracking error, and the point in the scan at which the amplitude reaches its minimum indicates the direction of the error. In more advanced radars, the error is sensed by sequentially placing the center of the beam on one side and then the other of the boresight line during reception only, a technique called lobing (Fig. 22). To avoid inaccuracies due to pulse-to-pulse fluctuations in the echoes’ strength, more advanced radars form the lobes simultaneously, enabling the error to be sensed with a single pulse. In one such technique, called amplitudecomparison monopulse, the antenna is divided into halves which produce overlapping lobes. In another, called phasecomparison monopulse, both halves of the antenna produce beams pointing in the boresight direction. If a tracking error exists, the distance from the target to each half will differ slightly in proportion to the error θe. Consequently, the error can be determined by sensing the resulting difference in radio frequency phase of the signals received by the two halves (Fig. 23).

θe

a

Lobe A

Boresight line

21. Conical scan. Angle tracking errors are sensed by rotating the antenna‘s beam about the boresight line and sensing the resulting modulation of the received echoes.

θ

Position A

a

Boresight

Position B Polar plot of antenna gain versus azimuth angle, θ.

Error θe

θe ∝ (a – b)

22. Lobing. For reception, antenna lobe is alternately deflected to the right and left of the boresight line to measure the angletracking error, θe.

From Target

d

b

b

θe

Lobe B ∆R = d θe

23. Phase comparison monopulse. Difference in distances from target to antenna’s two halves, ∆R; hence (for small angles), the difference in phases of outputs a and b, is proportional to the tracking error, θe.

By continuously sensing the tracking error with either of these techniques and correcting the antenna’s pointing direction to minimize the error, the antenna can be made to follow the target’s movement precisely. 9

PART I Overview of Airborne Radar

24. Target‘s relative velocity may be computed from measured values of range, range rate, and angular rate of line of sight.

While the target is being tracked in angle, its range and direction may be continuously measured. Its range rate may then be computed from the continuously measured range, and its angular rate (rate of rotation of the line of sight to the target) may be computed from the continuously measured direction. Knowing the target’s range, range rate, direction, and angular rate, its velocity and acceleration may be computed as illustrated in Fig. 24. For greater accuracy, both angular rate and range rate may be determined directly: Angular rate may be measured by mounting rate gyros sensitive to motion about the azimuth and elevation axes, on the antenna. Range rate may be measured by sensing the shift in the radio frequency of the target’s echoes due to the doppler effect. Exploiting the Doppler Effect

25. A common example of the doppler shift. Motion of car crowds sound waves propagated ahead, spreads waves propagated behind.

The classic example of the doppler effect is the change in pitch of a locomotive’s whistle as it passes by. Today, a more common example is found in the roar of a racing car, which deepens as the car zooms by (Fig. 25). Because of the doppler effect, the radio frequency of the echoes an airborne radar receives from an object is shifted relative to the frequency of the transmitter in proportion to the object’s range rate. Since the range rates encountered by an airborne radar are a minuscule fraction of the speed of radio waves, the doppler shift—or doppler frequency as it is called—of even the most rapidly closing target is extremely slight. So slight that it shows up simply as a pulse-to-pulse shift in the radio frequency phase of the target’s echoes. To measure the target’s doppler frequency, therefore, the following two conditions must be met: • At least several (and in some cases, a great many) successive echoes must be received from the target, and • The first wavefront of each pulse must be separated from the last wavefront of the same polarity in the preceding pulse by a whole number of wavelengths— a quality called coherence.

26. By cutting a radar‘s transmitted pulses from a continuous wave, the radio frequency phase of successive echoes from the same target will be coherent, enabling their doppler frequency to be readily measured.

Coherence may be achieved by, in effect, cutting the radar’s transmitted pulses from a continuous wave (Fig. 26). By sensing doppler frequencies, a radar can not only measure range rates directly, but also expand its capabilities in other respects. Chief among these is the substantial reduction, or in some cases complete elimination, of “clutter.” The range rates of aircraft are generally quite different from the range rates of most points on the ground, as well as of rain and other stationary or slowly moving sources of unwanted return. By sensing doppler frequencies, therefore, a radar can differentiate echoes of aircraft from clutter 10

CHAPTER 1 Basic Concepts

and reject the clutter. This feature is called moving target indication (MTI). In some cases, it may also be called airborne moving target indication (AMTI) to differentiate it from the simpler MTI used in ground based radars. MTI is of inestimable value in radars which must operate at low altitudes or look down in search of aircraft flying below them. The antenna beam then commonly intercepts the ground at the target’s range. Without MTI, the target echoes would be lost in the ground return (Fig. 27). MTI can also be of great value when flying at higher altitudes and looking straight ahead. For even then, the lower edge of the beam may intercept the ground at long ranges. A radar can similarly isolate the echoes of moving vehicles on the ground. In some situations where MTI is used, the abundance of moving vehicles on the ground can make aircraft difficult to spot. But echoes from aircraft and echoes from vehicles on the ground can usually be differentiated by virtue of differences in closing rates, due to the ground vehicles’ lower speeds. Where desired, by sensing the doppler shift, a radar can measure its own velocity. For this, the antenna beam is generally pointed ahead and down at a shallow angle. The echoes from the point at which the beam intercepts the ground are then isolated and their doppler shift is measured. By sequentially making several such measurements at different azimuth and elevation angles, the aircraft’s horizontal ground speed can be accurately computed (Fig. 28).

27. With MTI, echoes from aircraft and moving vehicles on the ground are separated from ground clutter on the basis of the differences in their doppler frequencies. Generally, echoes from aircraft and echoes from moving vehicles on the ground similarly may be differentiated as a result of the ground vehicles’ lower speed.

28. Radar‘s own velocity may be computed from doppler frequencies of three or more points on the ground at known angles.

Ground Mapping The radio waves transmitted by a radar are scattered back in the direction of the radar in different amounts by different objects—little from smooth surfaces such as lakes2 and roads, more from farm lands and brush, and heavily from most man-made structures. Thus, by displaying the differences in the intensities of the received echoes when the antenna beam is swept across the ground, it is possible to produce a pictorial map of the terrain, called a ground map. Radar maps differ from aerial photographs and road maps in several fundamental respects: In the first place, because of the difference in wavelengths, the relative reflectivity of the various features of the terrain may be quite different for radio waves than for visible light. Consequently, what is bright in a photograph may not be bright in a radar map, and vice versa. In addition, unlike road maps, radar maps contain shadows, may be distorted, and unless special measures are taken to improve azimuth resolution, may show very little detail. 11

2. This depends upon the lookdown angle. Water and flat ground directly below a radar produce very strong return.

PART I Overview of Airborne Radar Click for high-quality image

29. Shadows leave holes in radar maps. At steep lookdown angles, shadowing is minimized.

30. At steep lookdown angles, mapped distances are foreshortened. Except for distortion due to slope of the ground, foreshortening may be corrected before map is displayed.

Shadows are produced whenever the transmitted waves are intercepted—in part or in whole—by hills, mountains, or other obstructions. The effect can be visualized by imagining that you are looking directly down on a relief map illuminated by a single light source at the radar’s location (Fig. 29). Shadowing is minimal if the terrain is reasonably flat or if the radar is looking down at a fairly steep angle. Distortion arises, however, if the lookdown angle is large. Since the radar measures distance in terms of slant range, the apparent horizontal distance between two points at the same azimuth is foreshortened (Fig. 30). If the terrain is sloping, two points separated by a small horizontal distance can, in the extreme, be mapped as a single point. Usually, the foreshortening can be corrected on the basis of the lookdown angle, before the map is displayed. The degree of detail provided by a radar map depends upon the ability of the radar to separate (resolve) closely spaced objects in range and azimuth. Range resolution is limited primarily by the width of the radar’s pulses. By transmitting wide pulses and employing large amounts of pulse compression, the radar may obtain strong returns even from very long ranges and achieve range resolution as fine as a foot or so. Fine azimuth resolution is not so easily obtained. In conventional (real-beam) ground mapping, azimuth resolution is determined by the width of the antenna beam (Fig. 31).

Click for high-quality image Click for high-quality image

31. With conventional mapping, dimensions of resolution cell are determined by pulsewidth and width of the antenna beam.

32. Real-beam map enhanced for detection of seaborne targets. Map was made by the radar of a fighter aircraft. Although azimuth resolution is limited, map can be highly useful. (Courtesy Northrop Grumman).

With a beamwidth of 3º, for example, at a range of 10 miles azimuth resolution of a real-beam map may be no finer than half a mile (Fig. 32). Azimuth resolution may be improved by operating at higher frequencies or by making the antenna larger. But if exceptionally high frequencies are used, detection ranges are reduced by atmospheric attenuation, and there are prac12

CHAPTER 1 Basic Concepts

tical limitations on how large an antenna most aircraft can accommodate. However, an antenna of almost any length can by synthesized with a technique called synthetic array radar (or synthetic aperture radar), SAR. SAR. Rather than scanning the terrain in the conventional way, with SAR the radar beam is pointed out to the side to illuminate the patch of ground of interest. Each time the radar radiates a pulse, it assumes the role of a single radiating element. Because of the aircraft’s velocity, each such element is a little farther along on the flight path (Fig. 33). By storing the returns of a great many pulses and combining them—as a feed system combines the returns received by the radiating elements of a real antenna—the radar can synthesize the equivalent of a linear array long enough to provide azimuth resolution as fine as a foot or so (Fig. 34). Moreover, by increasing the length of the synthesized array in proportion to the range of the area being mapped, the same fine resolution can be obtained at a range of 100 miles as at a range of only a few miles. Moving targets tend to wash out in a SAR map because of their rotational motion. By taking advantage of it instead of the radar’s forward motion, target images can be made, a technique called inverse SAR (ISAR). Summary By transmitting radio waves and listening for their echoes, a radar can detect objects day or night and in all kinds of weather. By concentrating the waves into a narrow beam, it can determine direction. And by measuring the transit time of the waves, it can measure range. To find a target, the radar beam is repeatedly swept through a search scan. Once detected, the target may be automatically tracked and its relative velocity computed on the basis of either (a) periodic samples of its range and direction obtained during the scan or (b) continuous data obtained by training the antenna on the target. In the latter case, the target’s echoes must be singled out in range and/or doppler frequency, and some means such as lobing must be provided to sense angular tracking errors. Because of the doppler effect, the radio frequencies of the radar echoes are shifted in proportion to the reflecting object’s range rates. By sensing these shifts, which is possible if the radar’s pulses are coherent, the radar can measure target closing rates, reject clutter, and differentiate between ground return and moving vehicles on the ground. It can even measure its own velocity. Since radio waves are scattered in different amounts by different features of the terrain, a radar can map the ground. With SAR, detailed maps can be made. 13

Patch being mapped. L

Points where pulses are transmitted correspond to radiators of a linear array.

Cross-range resolution = λ R λ = wavelength R = range

2L

33. SAR principle. With its antenna trained on a patch to be mapped, each time the radar transmits a pulse, it assumes the role of a single radiator. When the returns of a great many pulses are added up, the result is essentially the same as would have been obtained with a linear array antenna of length L. The mode illustrated here is called spotlight.

Click for high-quality image

34. One-foot-resolution SAR map. Was made in real time in the spotlight mode from a long range, as indicated by radar shadows cast by trees. Regardless of the range, of course, radar maps always appear the same as if viewed from directly over head. (Crown copyright DERA Malvern)

Ag-Al

1

Ag-Al (Silver-Aluminum) Phase diagram The diagram in Fig. 1 is taken from various compilations [58Han1, 65Ell1, 69Shu1, 73Hul1, 80Ell1]. In most parts it agrees with the diagram assessed by McAlister et al. [87McA1]. The solubility of Al in solid Ag is given in Fig. 2 [41Foo1]. Pollock has determined by thermoelectric measurements the solubility of Al in Ag at 303 K. He found a solubility limit of < 2.6 at % Al [67Pol1]. Zakharova et al. have measured the solubility of Ag in solid Al at a pressure of 1.04 GPa. The results are given in Fig. 3 [50Zak1]. By cooling of the melt using extremely high cooling rates the solid solution of Ag in Al can be prepared with up to 40 at% Ag [67Dix1]. By rapid quenching of the β-phase, this phase can be retained at room temperature, or there can occur a massive or a martensitic transformation [68Haw1]. Arias et al. have investigated the massive as well as the martensitic transformation in the composition range between 23.2 and 27.9 at% Al. The martensitic temperature (Ms) as a function of Al concentration is indicated in Fig. 4 [69Ari1]. Marty et al. have observed by electrical resistivity measurements the formation of Guinier-Preston zones at 98.7 at% Al. Aging temperature: 243 … 273 K [71Mar1]. By means of atom-probe field ion microscopy Osamura et al. have investigated metastable phases in an 94.28 at% Al alloy [86Osa1]. The Al concentration of the η-Guinier-Preston zones (aging at 413 K) is 54.2 at% Al. Aging at 436 K yields ε-Guinier-Preston zones and the metastable phase γ′ simultaneously. The Al content of ε is 64.7 at% Al and that of γ′ is 66.7 at% Al. The formation of γ′ is preceded by the formation of Guinier-Preston zones [81Shc1].

LIVE GRAPH

Fig. 1. Ag-Al. Phase diagram. Landolt-Börnstein New Series IV/5

Ag-Al

8

References 35Obi1 41Foo1 50Zak1 58Han1 58Pea1 59Mas1 59Wit1 60Wil1 62Hel1 65Ell1 66Neu1 67Dix1 67Pea1 67Pol1 68Haw1 68Neu1 69Ari1 69Shu1 70Mas1 71Mar1 73Hul1 80Ell1 81Shc1 86Osa1 87McA1 88Nag1

Obinata, J., Hagiya, M.: Kinzoku no Kenkyu 12 (1935) 419; Sci. Rep. Tohoku Imp. Univ. Honda Anniversary Vol. 1936, p. 715. Foote, F., Jette, E.R.: Trans. AIME 143 (1941) 151. Zakharova, M.V., Ilina, V.A.: Zh. Fiz. Khim. 24 (1950) 714. Hansen, M., Anderko, K.: „Constitution of Binary Alloys“, New York: McGraw-Hill 1958. Pearson, W.B.: „A Handbook of Lattice Spacings and Structures of Metals and Alloys“, Oxford: Pergamon Press 1958. Massalski, T.B., Cockayne, B.: Acta Metallurgica 7 (1959) 762. Wittig, F.E., Schilling, W.: Z. Metallkde. 50 (1959) 610. Wilder, T.C., Elliott, J.F.: J. Electrochem. Soc. 107 (1960) 628. Helfrich, W.J., Dodd, R.A.: Trans. AIME 224 (1962) 757. Elliott, R.P.: „Constitution of Binary Alloys“, First Supplement, New York: McGraw-Hill 1965. Neumann, J.P.: Acta Metallurgica 14 (1966) 505. Dixmier, J., Guinier, A.: Mem. Sci. Rev. Met. 64 (1967) 53. Pearson, W.B.: „A Handbook of Lattice Spacings and Structures of Metals and Alloys“, Vol. 2, Oxford: Pergamon Press 1967. Pollock, D.D.: Trans. AIME 239 (1967) 1768. Hawbolt, E.B., Brown, L.C.: Trans. AIME 242 (1968) 1182. Neumann, J.P., Chang, Y.A.: Trans. AIME 242 (1968) 700. Arias, D., Kittl, J.: Trans. AIME 245 (1969) 182. Shunk, F.A.: „Constitution of Binary Alloys“, Second Supplement, New York: McGraw-Hill 1969. Massart, G., Desré, P., Bonnier, E.: J. Chim. Phys. 67 (1970) 1485. Marty, K.N., Vasu, K.I.: J. Mater. Sci. 6 (1971) 39. Hultgren, R., Desai, P.D., Hawkins, D.T., Gleiser, M., Kelley, K.K.: „Selected Values of the Thermodynamic Properties of Binary Alloys“, Metals Park, Ohio: Am. Soc. Met. 1973. Elliott, R.P.: Bull. Alloy Phase Diagrams 1 (1980) 36. Shchegleva, T.V.: Fiz. Metal. Metalloved. 51 (1981) 1015. Osamura, K., Nakamura, T., Kobayashi, B., Hashizume, T., Sakurai, T.: Acta Metallurgica 34 (1986) 1563. McAlister, A.J.: Bull. Alloy Phase Diagrams 8 (1987) 526. Nagasawa, A., Tatsumi, A.: Trans. Jpn. Inst. Met. 29 (1988) 625.

Landolt-Börnstein New Series IV/5

List of Interactive Tables for Chapter 5 Table 5.2.1.0(b). Design Mechanical and Physical Properties of Commercially Pure Titanium Table 5.2.1.0(c). Design Mechanical and Physical Properties of Commercially Pure Titanium Extruded Bars and Shapes Table 5.3.1.0(b). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Sheet, Strip, and Plate Table 5.3.1.0(c). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Bar and Forging Table 5.3.1.0(d). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Extrusion Table 5.3.2.0(b1). Design Mechanical and Physical Properties of Ti-8Al-1Mo-1V Sheet and Plate Table 5.3.2.0(b2). Design Mechanical and Physical Properties of Ti-8Al-1Mo-1V Sheet and Plate Table 5.3.2.0(c). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Bar and Forging Table 5.3.3.0(b). Design Mechanical and Physical Properties of Ti-6Al-2Sn-4Zr-2Mo Table 5.3.3.0(c). Design Mechanical and Physical Properties of Ti-6Al-2Sn-4Zr-2Mo 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(c3). Design Mechanical and Physical Properties of Ti-6Al-4V Bar and Plate 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(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 (b). Design Mechanical and Physical Properties of Ti-4.5 Al-3V-2Fe-2Mo Titanium Alloy Sheet

Table 5.5.1.0(b). Design Mechanical and Physical Properties of Ti-13V-11Cr-3Al Table 5.5.2.0(b). Design Mechanical and Physical Properties of Ti-15V-3Cr-3Sn-3Al Sheet Table 5.5.3.0(b). Design Mechanical and Physical Properties of Ti-10V-2Fe-3Al Die Forging Table 5.5.3.0(c). Design Mechanical and Physical Properties of Ti-10V-2Fe-3Al Hand Forging

MIL-HDBK-5H, Change Notice 1 1 October 2001

CHAPTER 5 TITANIUM 5.1 GENERAL This chapter contains the engineering properties and related characteristics of titanium and titanium alloys used in aircraft and missile structural applications. General comments on engineering properties and the considerations relating to alloy selection are presented in Section 5.1. Mechanical- and physical-property data and characteristics pertinent to specific alloy groups or individual alloys are reported in Sections 5.2 through 5.5. Titanium is a relatively lightweight, corrosion-resistant structural material that can be strengthened greatly through alloying and, in some of its alloys, by heat treatment. Among its advantages for specific applications are: good strength-to-weight ratio, low density, low coefficient of thermal expansion, good corrosion resistance, good oxidation resistance at intermediate temperatures, good toughness, and low heattreating temperature during hardening, and others. 5.1.1 TITANIUM INDEX — The coverage of titanium and its alloys in this chapter has been divided into four sections for systematic presentation. The system takes into account unalloyed titanium and three groups of alloys based on metallurgical differences which in turn result in differences in fabrication and property characteristics. The sections and the individual alloys covered under each are shown in Table 5.1. Table 5.1. Titanium Alloys Index Section Alloy Designation 5.2 Unalloyed Titanium 5.2.1 Commercially Pure Titanium 5.3 Alpha and Near-Alpha Titanium Alloys 5.3.1 Ti-5A1-2.5Sn (Alpha) 5.3.2 Ti-8A1-1Mo-1V (Near-Alpha) 5.3.3 Ti-6A1-2Sn-4Zr-2Mo (Near-Alpha) 5.4 Alpha-Beta Titanium Alloys 5.4.1 Ti-6A1-4V 5.4.2 Ti-6A1-6V-2Sn 5.4.3 Ti - 4.5Al-3V-2Fe-2Mo 5.5 Beta, Near-Beta, and Metastable Titanium Alloys 5.5.1 Ti-13V-11Cr-3A1 5.5.2 Ti-15V-3Cr-3Sn-3A1 5.5.3 Ti-10V-2Fe-3A1

5.1.2 MATERIAL PROPERTIES — The material properties of titanium and its alloys are determined mainly by their alloy content and heat treatment, both of which are influential in determining the allotropic forms in which this material will be bound. Under equilibrium conditions, pure titanium has an “alpha” structure up to 1620EF, above which it transforms to a “beta” structure. The inherent properties of these two structures are quite different. Through alloying and heat treatment, one or the other or a combination of these two structures can be made to exist at service temperatures, and the properties of the material vary

Supersedes page 5-1 of MIL-HDBK-5H

5-1

MIL-HDBK-5H, Change Notice 1 1 October 2001 accordingly. References 5.1.2(a) and (b) provide general discussion of titanium microstructures and associated metallography. Titanium and titanium alloys of the alpha and alpha-beta type exhibit crystallographic textures in sheet form in which certain crystallographic planes or directions are closely aligned with the direction of prior working. The presence of textures in these materials lead to anisotropy with respect to many mechanical and physical properties. Poisson’s ratio and Young’s modulus are among those properties strongly affected by texture. Wide variations experienced in these properties both within and between sheets of titanium alloys have been qualitatively related to variations of texture. In general, the degree of texturing, and hence the variation of Young’s modulus and Poisson’s ratio, that is developed for alpha-beta alloys tends to be less than that developed in all alpha titanium alloys. Rolling temperature has a pronounced effect on the texturing of titanium alloys which may not in general be affected by subsequent thermal treatments. The degree of applicability of the effect of textural variations discussed above on the mechanical properties of products other than sheet is unknown at present. The values of Young’s modulus and Poisson’s ratio listed in this document represent the usual values obtained on products resulting from standard mill practices. References 5.1.2(c) and (d) provide further information on texturing in titanium alloys. 5.1.2.1 Mechanical Properties — 5.1.2.1.1 Fracture Toughness — The fracture toughness of titanium alloys is greatly influenced by such factors as chemistry variations, heat treatment, microstructure, and product thickness, as well as yield strength. For fracture critical applications, these factors should be closely controlled. Typical values of plane-strain fracture toughness for titanium alloys are presented in Table 5.1.2.1.1. Minimum, average, and maximum values, as well as coefficient of variation, are presented for various products for which valid data are available, but these values do not have the statistical reliability of the room-temperature mechanical properties. 5.1.3 MANUFACTURING CONSIDERATIONS — Comments relating to formability, weldability, and final heat treatment are presented under individual alloys. These comments are necessarily brief and are intended only to aid the designer in the selection of an alloy for a specific application. In practice, departures from recommended practices are very common and are based largely on in-plant experience. Springback is nearly always a factor in hot or cold forming. Final heat treatments that are indicated as “specified” heat treatments do not necessarily coincide with the producers’ recommended heat treatments. Rather, these treatments, along with the specified roomtemperature minimum tensile properties, are contained in the heat treating-capability requirements of applicable specifications, for example, MIL-H-81200. Departures from the specified aging cycles are often necessary to account for aging that may take place during hot working or hot sizing or to obtain more desirable mechanical properties, for example, improved fracture toughness. More detailed recommendations for specific applications are generally available from the material producers. 5.1.4 ENVIRONMENTAL CONSIDERATIONS — Comments relating to temperature limitations in the application of titanium and titanium alloys are presented under the individual alloys. Below about 300EF, as well as above about 700EF, creep deformation of titanium alloys can be expected at stresses below the yield strength. Available data indicate that room-temperature creep of unalloyed titanium may be significant (exceed 0.2 percent creep-strain in 1,000 hours) at stresses that exceed approximately 50 percent Fty, room-temperature creep of Ti-5A1-1.5Sn ELI may be significant at stresses above approximately 60 percent Fty, and room-temperature creep of the standard grades of titanium alloys may be significant at stresses above approximately 75 percent Fty. References 5.1.4(a) through (c) provide some limited data regarding room-temperature creep of titanium alloys.

Supersedes page 5-1 of MIL-HDBK-5H

5-2

MIL-HDBK-5H, Change Notice 1 1 October 2001 The use of titanium and its alloys in contact with either liquid oxygen or gaseous oxygen at cryogenic temperatures should be avoided, since either the presentation of a fresh surface (such as produced by tensile rupture) or impact may initiate a violent reaction [Reference 5.1.4(d)]. Impact of the surface in contact with liquid oxygen will result in a reaction at energy levels as low as 10 ft-lb. In gaseous oxygen, a partial pressure of about 50 psi is sufficient to ignite a fresh titanium surface over the temperature range from -250EF to room temperature or higher. Titanium is susceptible to stress-corrosion cracking in certain anhydrous chemicals including methyl alcohol and nitrogen tetroxide. Traces of water tend to inhibit the reaction in either environment. However, in N2O4, NO is preferred and inhibited N2O4 contains 0.4 to 0.8 percent NO. Red fuming nitric acid with less than 1.5 percent water and 10 to 20 percent NO2 can crack the metal and result in a pyrophoric reaction. Titanium alloys are also susceptible to stress corrosion by dry sodium chloride at elevated temperatures. This problem has been observed largely in laboratory tests at 450 to 500EF and higher and occasionally in fabrication shops. However, there have been no reported failures of titanium components in service by hot salt stress corrosion. Cleaning with a nonchlorinated solvent (to remove salt deposits, including fingerprints) of parts used above 450EF is recommended. In laboratory tests, with a fatigue crack present in the specimen, certain titanium alloys show an increased crack propagation rate in the presence of water or salt water as compared with the rate in air. These alloys also may show reduced sustained load-carrying ability in aqueous environments in the presence of fatigue cracks. Crack growth rates in salt water are a function of sheet or section thickness. These alloys are not susceptible in the form of thin-gauge sheet, but become susceptible as thickness increases. The thickness at which susceptibility occurs varies over a visual range with the alloy and processing. Alloys of titanium found susceptible to this effect include some from alpha, alpha-beta, and beta-type microstructures. In some cases, special processing techniques and heat treatments have been developed that minimize this effect. References 5.1.4(e) through (g) present detailed summaries of corrosion and stress corrosion of titanium alloys. Under certain conditions, titanium, when in contact with cadmium, silver, mercury, or certain of their compounds, may become embrittled. Refer to MIL-HDBK-1568 for restrictions concerning applications with titanium in contact with these metals or their compounds.

Supersedes page 5-1 of MIL-HDBK-5H

5-3

Table 5.1.2.1.1.

a

Values of Room Temperature Plain-Strain Fracture of Titanium Alloys

Alloy

Yield Product Specimen Heat Strength Thickness Number Thickness Treat Product Range, Range, of Sample Range, Condition Form Orientationb ksi inches Sources Size inches

Max.

Avg.

Min.

Coefficient of Variation

Ti-6Al-4V

Mill Forged Annealed Bar

L-T

121-143

<3.5

2

43

0.6-1.1

77

60

38

10.5

Ti-6Al-4V

Mill Forged Annealed Bar

T-L

124-145

<3.5

2

64

0.5-1.3

81

57

33

11.7

5-4

a These values are for information only. b Refer to Figure 1.4.12.3 for definition of symbols.

MIL-HDBK-5H 1 December 1998

REPRINTED WITHOUT CHANGE.

KIc, ksi
 in.

MIL-HDBK-5H 1 December 1998

5.2 UNALLOYED TITANIUM Several grades of unalloyed titanium are offered and are classified on the basis of manufacturing method, degree of purity, or strength, there being a close relationship among these. The unalloyed titanium grades most commonly used are produced by the Kroll process, are intermediate in purity, and are commonly referred to as being of commercial purity. 5.2.1 COMMERCIALLY PURE TITANIUM 5.2.1.0 Comments and Properties — Unalloyed titanium is available in all familiar product forms and is noted for its excellent formability. Unalloyed titanium is readily welded or brazed. It has been used primarily where strength is not the main requirement. Manufacturing Considerations — Unalloyed titanium is supplied in the annealed condition permitting extensive forming at room temperature. Severe forming operations also can be accomplished at elevated temperatures (300 to 900
F). Property degradation can be experienced after severe forming if as-received material properties are not restored by re-annealing. Commercially pure titanium can be welded readily by the several methods employed for titanium joining. Atmospheric shielding is preferable although spot or seam welding may be accomplished without shielding. Brazing requires protection from the atmosphere which may be obtained by fluxing as well as by inert gas or vacuum shielding. Environmental Considerations — Titanium has an unusually high affinity for oxygen, nitrogen, and hydrogen at temperatures above 1050
F. This results in embrittlement of the material, thus usage should be limited to temperatures below that indicated. Additional chemical reactivity between titanium and selected environments such as methyl alcohol, chloride salt solutions, hydrogen, and liquid metal, can take place at lower temperatures, as discussed in Section 5.1.4 and its references. 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 — Commercially pure titanium is fully annealed by heating to 1000 to 1300
F for 10 to 30 minutes. It is stress relieved by heating to 900 to 1000
F for 30 minutes. Commercially pure titanium cannot be hardened by heat treatment. Specifications and Properties — Some material specifications for commercially pure titanium are presented in Table 5.2.1.0(a). Room-temperature mechanical properties for commercially pure titanium are shown in Tables 5.1.2.0(b) and (c). The effect of temperature on physical properties is shown in Figure 5.2.1.0. 5.2.1.1 Annealed Condition — Elevated-temperature data for annealed commercially pure titanium are presented in Figures 5.2.1.1.1(a) through 5.2.1.1.3(b). Typical full-range stress-strain curves for the 40 and 70 ksi yield strength commercially pure titanium are shown in Figures 5.2.1.1.6(a) and (b).

REPRINTED WITHOUT CHANGE.

5-5

MIL-HDBK-5H, Change Notice 1 1 October 2001

Table 5.2.1.0(a). Material Specifications for Commercially Pure Titanium

Specification AMS 4900 AMS 4901 AMS 4902 AMS-T-9046 MIL-T-9047a AMS 4921 AMS-T-81556

Form Sheet, strip, and plate Sheet, strip, and plate Sheet, strip, and plate Sheet, strip, and plate Bar Bar Extruded bars and shapes

a Inactive for new design

Supersedes page 5-6 of MIL-HDBK-5H

5-6

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Table 5.2.1.0(b). Titanium

Interacti ve T ab le - T yp i c a l P r op ert i es

Design Mechanical and Physical Properties of Commercially Pure

AMS 4902 AMS 4900 AMS 4901 Specification . . . . . . . . . . . . . . . . . . MIL-T-9046 and MIL-T- and MIL-T- and MIL-T9046 9046 9046 Designation . . . . . . . . . . . . . . . . . . . .

CP-4

CP-3

CP-2

AMS 4921 and MIL-T9047

CP-1

MIL-T9047

CP-70

Form . . . . . . . . . . . . . . . . . . . . . . . . . .

Sheet, strip, and plate

Bar

Condition . . . . . . . . . . . . . . . . . . . . . .

Annealed

Annealed

Thickness or diameter, in. . . . . . . . . .


1.000

Basis . . . . . . . . . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ..................... LT . . . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . . . Fty, ksi: L ..................... LT . . . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . . . Fcy, ksi: L ..................... LT . . . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . . . e, percent: L ..................... LT . . . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . . . RA, percent: L ..................... LT . . . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . . .


2.999a

3.0004.000a

S

S

S

S

S

S

35 35 ...

50 50 ...

65 65 ...

80 80 ...

80 80b ...

80 80 80

25 25 ...

40 40 ...

55 55 ...

70 70 ...

70 70b ...

70 70 70

... ... ...

... ... ...

... ... ...

70 70 42

... ... ...

... ... ...

... ...

... ...

... ...

120 ...

... ...

... ...

... ...

... ...

... ...

101 ...

... ...

... ...

24c 24c ...

20c 20c ...

18c 18c ...

15c 15c ...

15 15b ...

15 15 15

... ... ...

... ... ...

... ... ...

... ... ...

30 30b ...

30 30 30

E, 103 ksi ........................ Ec, 103 ksi ...................... G, 103 ksi ....................... µ ......................................

15.5 16.0 6.5 ...

Physical Properties:
, lb/in.3 ......................... C, K, and  ....................

0.163 See Figure 5.2.1.0

a Maximum of 16-square-inch cross-sectional area. b Long transverse properties apply to rectangular bar only for thickness >0.500 inches and widths >3.000 inches. For AMS 4921, (e) (LT) = 12% and RA (LT) = 25%. c Thickness of 0.025 inch and above.

REPRINTED WITHOUT CHANGE.

5-7

MIL-HDBK-5H, Change Notice 1 1 October 2001

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.2.1.0(c). Design Mechanical and Physical Properties of Commercially Pure Titanium Extruded Bars and Shapes

Specification . . . . . . . . . . . . Comp. CP-4 Form . . . . . . . . . . . . . . . . . . . Condition . . . . . . . . . . . . . . . Thickness or diameter, in. . . Basis . . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fty, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fcy, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . e, percent: L ................... E, 103 ksi . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . µ .................... Physical Properties: ω, lb/in.3 . . . . . . . . . . . . . . C, K, and α . . . . . . . . . . . .

S

AMS-T-81556 Comp. CP-3 Comp. CP-2 Extruded bars and shapes Annealed 0.188-3.000 S S

Comp. CP-1

S

40 ...

50 ...

65 ...

80 ...

30 ...

40 ...

55 ...

70 ...

... ... ...

... ... ...

... ... ...

... ... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

a

a

a

a

15.5 16.0 6.5 ... 0.163 See Figure 5.2.1.0

a Elongation in percent as follows: Thickness, inches 0.188-1.000 1.001-2.000 2.001-3.000

Comp. CP-4 25 20 18

Supersedes page 5-8 of MIL-HDBK-5H

Comp. CP-3 20 18 15

5-8

Comp. CP-2 18 15 12

Comp. CP-1 15 12 10

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.2.1.0. Effect of temperature on the physical properties of commercially pure titanium.

5-9

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.2.1.1.1(a). Effect of temperature on the tensile ultimate strength (Ftu) of annealed commercially pure titanium.

VIEW INTERACTIVE GRAPH

Figure 5.2.1.1.1(b). Effect of temperature on the tensile yield strength (Fty) of annealed commercially pure titanium.

5-10

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.2.1.1.2(a). Effect of temperature on the compressive yield strength (Fcy) of annealed commercially pure titanium.

VIEW INTERACTIVE GRAPH

Figure 5.2.1.1.2(b). Effect of temperature on the shear ultimate strength (Fsu) of annealed commercially pure titanium.

5-11

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.2.1.1.3(a). Effect of temperature on the bearing ultimate strength (Fbru) of annealed commercially pure titanium.

VIEW INTERACTIVE GRAPH

Figure 5.2.1.1.3(b). Effect of temperature on the bearing yield strength (Fbry) of annealed commercially pure titanium.

5-12

VIEW INTERACTIVE GRAPH

5-13 Figure 5.2.1.1.6(a). Typical full-range tensile stress-strain curve for commercially pure titanium sheet (40 ksi yield at room temperature).

VIEW INTERACTIVE GRAPH

5-14 Figure 5.2.1.1.6(b). Typical full-range tensile stress-strain curve for commercially pure titanium sheet (70 ksi yield at room temperature).

MIL-HDBK-5H, Change Notice 1 1 October 2001

5.3 ALPHA AND NEAR-ALPHA TITANIUM ALLOYS The alpha titanium alloys contain essentially a single phase at room temperature, similar to that of unalloyed titanium. Alloys identified as near-alpha titanium have principally an all-alpha structure but contain small quantities of a beta phase because the composition contains some beta stabilizing elements. In both alloy types, alpha phase is stabilized by aluminum, tin, and zirconium. These elements, especially aluminum, contribute greatly to strength. The beta stabilizing additions (e.g., molybdenum and vanadium) improve fabricability and metallurgical stability of highly alpha-alloyed materials. All alpha alloys have excellent weldability, toughness at low temperatures, and long-term elevatedtemperature strength. They are well suited to cryogenic applications and to uses requiring good elevatedtemperature creep strength. The characteristics of near-alpha alloys are predictably between those of all alpha and alpha-beta alloys in regard to fabricability, weldability, and elevated-temperature strength. The hot workability of both alpha and near-alpha alloys is inferior to that of the alpha-beta or beta alloys and the cold workability is very limited at the high-strength level of these grades. However, considerable forming is possible if correct forming temperatures and procedures are used. 5.3.1 TI-5AL-2.5SN 5.3.1.0 Comments and Properties — Ti-5Al-2.5Sn is an all-alpha alloy available in many product forms and at two purity levels. The high purity grade of this composition is used principally for cryogenic applications and may be characterized as having lower strength but higher ductility and toughness than the standard grade. The normal purity grade also may be used at low temperatures but it is primarily suitable for room to elevated temperature applications (up to 900EF or to 1100EF for short times) where weldability is an important consideration. Manufacturing Considerations — Ti-5Al-2.5Sn is not so readily formed into complex shapes as other alloys with similar room-temperature properties, but far surpasses them in weldability. Except for some forging operations, fabrication of Ti-5Al-2.5Sn is conducted at temperatures where the structure remains all alpha. Severe forming operations may be accomplished at temperatures up to 1200EF. Moderately severe forming can be done at 300 to 600EF and simple forming may be done at room temperature. Most forming and welding operations are followed by an annealing treatment to relieve residual stresses imposed by the prior operation. Ti-5Al-2.5Sn can be welded readily by inert-gas or vacuum-shielded arc methods or by spot or seam welding without atmospheric shielding. Brazing requires protection from the atmosphere; however, this is accomplished by fluxing as well as by inert gas or vacuum shielding. Environmental Considerations — Ti-5Al-2.5Sn is metallurgically stable at moderate elevated temperatures. The material is susceptible to hot-salt stress corrosion as well as aqueous chloride solution stress corrosion. Care should be exercised in applications involving such environments. The alloy has good oxidation resistance up to 1050EF. Standard grade material has been used at moderately low cryogenic temperatures; however, the ELI grade has higher toughness and has been used in cryogenic applications down to -423EF. Under certain conditions, titanium, when in contact with cadmium, silver, mercury, or certain of their compounds, may become embrittled. Refer to MIL-HDBK-1568 for restrictions concerning applications with titanium in contact with these metals or their compounds. Heat Treatment — This alloy is annealed by heating 1400EF for 60 minutes and 1600EF for 10 minutes and cooling in air. Stress relieving requires 1 or 2 hours at 1000 to 1200EF. Ti-5Al-2.5Sn cannot be hardened by heat treatment.

Supersedes page 5-15 of MIL-HDBK-5H

5-15

MIL-HDBK-5H, Change Notice 1 1 October 2001 Specifications and Properties — Some material specifications for Ti-5Al-2.5Sn are shown in Table 5.3.1.0(a). Room-temperature mechanical properties for Ti-5Al-2.5Sn are shown in Tables 5.3.1.0(b) through (d). The effect of temperature on physical properties is shown in Figure 5.3.1.0.

Table 5.3.1.0(a). Material Specifications for Ti-5Al-2.5Sn

Specification AMS-T-9046 AMS 4926 MIL-T-9047a AMS-T-81556 AMS 4910 AMS 4966

Form Sheet, strip, and plate Bar Bar Extruded bar and shapes Sheet, strip, and plate Forging

a Inactive for new design

5.3.1.1 Annealed Condition — Elevated temperature curves for annealed Ti-5Al-2.5Sn are shown in Figures 5.3.1.1.1 through 5.3.1.1.5. Tensile properties cover the range -423EF to 1000EF; whereas other properties are for the range room temperature to 1000EF. Fatigue-crack-propagation data for sheet are shown in Figures 5.3.1.1.9(a) through (c).

Supersedes page 5-16 of MIL-HDBK-5H

5-16

MIL-HDBK-5H, Change Notice 1 1 October 2001 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.3.1.0(b). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Sheet, Strip, and Plate

Specification . . . . . . . Form . . . . . . . . . . . . . .

AMS 4910 and AMS-T-9046, Comp. A-1 Strip

Sheet

Plate

Condition . . . . . . . . . . Thickness, in. . . . . . . . Basis . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ........... LT . . . . . . . . . . Fty, ksi: L ........... LT . . . . . . . . . . Fcy, ksi: L ........... LT . . . . . . . . . . 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): L ........... LT . . . . . . . . . .

Annealed 0.0150.079

<0.187

0.0800.187

1.5014.000

A

B

A

B

A

B

S

S

120 120

120a 120a

128 129

120a 120a

131 132

120a 120a

135 137

120 120

115 115

113 113

110 113

115 118

113 113a

118 121

113a 113a

123 125

113 113

110 110

115 118 75

115 118 75

120 123 80

118 118 75

123 126 82

118 118 75

128 130 85

118 118 75

... ... ...

167 250

167 250

179 268

167 250

183 275

167 250

190 285

167 250

... ...

133 190

133 190

139 198

133 190

142 203

133 190

147 210

133 190

... ...

10 10

10b 10b

... ...

10 10

... ...

10 10

... ...

10 10

10 10

15.5 15.5 ... ...

Physical Properties: ω, lb/in.3 . . . . . . . . C, K, and α . . . . . .

0.162 See Figure 5.3.1.0

S-basis. The rounded T99 values are higher than specification values as follows: 0.015-0.079 0.080-0.187

0.188-0.250

Ftu L...... LT......

123 123

126 126

130 131

L....... LT......

.... ....

... 115

118 120

Fty

b

0.2511.500

S

E, 103 ksi . . . . . . . . Ec, 103 ksi . . . . . . . G, 103 ksi . . . . . . . µ ..............

a

0.1880.250

Thickness 0.025 inch and above.

Supersedes page 5-17 of MIL-HDBK-5H

5-17

MIL-HDBK-5H, Change Notice 1 1 October 2001

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.3.1.0(c). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Bar and Forging

Specification . . . . . . . . . . .

AMS 4926a and MIL-T-9047b

AMS 4966

Form . . . . . . . . . . . . . . . . .

Bar

Forging

Condition . . . . . . . . . . . . .

Annealed #2.999

Thickness or diameter, in. . Basis . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L .............. LT . . . . . . . . . . . . . ST . . . . . . . . . . . . . Fty, ksi: L .............. LT . . . . . . . . . . . . . ST . . . . . . . . . . . . . Fcy, ksi: L .............. LT . . . . . . . . . . . . . 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): L .............. LT . . . . . . . . . . . . . ST . . . . . . . . . . . . . RA, percent (S-basis): L .............. LT . . . . . . . . . . . . . ST . . . . . . . . . . . . .

3.000-4.000

...

B

S

115d 115e ...

126 ... ...

115 115 115

115 115f 115f

110d 110e ...

120 ... ...

110 110 110

110 110f 110f

... ... ...

... ... ...

... ... ...

... ... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

10 10e ...

... ... ...

10 10 8

10 10f 10f

25 25e ...

... ... ...

25 25 20

25 25f 25f

15.5 15.5 ... ...

Physical Properties: ω, lb/in.3 . . . . . . . . . . . . C, K, and α . . . . . . . . . .

0.162 See Figure 5.3.1.0

For AMS 4926, LT and ST values for e and RA may be different than those shown. Inactive for new design. Maximum of 16-square-inch cross-sectional area. The rounded T99 values are higher than S values as follows: Ftu = 117 ksi, Fty = 113 ksi. S-basis. Applicable providing LT dimension is >3.000 inches. Applicable, providing LT or ST dimension is $2.500 inches.

Supersedes page 5-18 of MIL-HDBK-5H

c

A

E, 103 ksi . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . µ ..................

a b c d e f

Annealed

c

5-18

MIL-HDBK-5H, Change Notice 1 1 October 2001

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.3.1.0(d). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Extrusion

Specification . . . . . . . . . . . . Form . . . . . . . . . . . . . . . . . . . Condition . . . . . . . . . . . . . . . Thickness or diameter, in. . . Basis . . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fty, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fcy, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . e, percent: L ................... LT . . . . . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . µ .................... Physical Properties: ω, lb/in.3 . . . . . . . . . . . . . . C, K, and α . . . . . . . . . . . .

Supersedes page 5-19 of MIL-HDBK-5H

0.1881.000 S

AMS-T-81556, Comp. A-1 Extruded bars and shapes Annealed 1.0012.0012.000 3.000 S S

3.0014.000 S

120 ...

115 ...

115 ...

115 ...

115 ...

110 ...

110 ...

110 ...

... ... ...

... ... ...

... ... ...

... ... ...

... ...

... ...

... ...

... ...

10 ...

10 ...

8 ...

6 ...

15.5 15.5 ... ... 0.162 See Figure 5.3.1.0

5-19

MIL-HDBK-5H 1 December 1998

.

VIEW INTERACTIVE GRAPH

0.2

C

6

12

5

10

4

-6

0.0

, 10 in./in./F

0.1

K

2

K, Btu/[(hr)(ft )(F)/ft]

C, Btu/(lb)(F)

- Between 70 F and indicated temperature K - At indicated temperature C - At indicated temperature

3

8

6

4

-400

-200

0

200

400

600

800

1000

1200

1400

1600

Temperature, F

Figure 5.3.1.0. Effect of temperature on the physical properties of Ti-5Al-2.5Sn alloy.

REPRINTED WITHOUT CHANGE.

5-20

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.1.1.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of annealed Ti-5Al-2.5Sn alloy.

5-21

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.1.1.2. Effect of temperature on the compressive yield strength(Fcy) and the shear ultimate strength (Fsu) of annealed Ti-5Al-2.5Sn alloy sheet.

VIEW INTERACTIVE GRAPH

Figure 5.3.1.1.3. Effect of temperature on the bearing ultimate strength(Fbru) and the bearing yield strength (Fbry) of annealed Ti-5Al-2.5Sn alloy sheet.

5-22

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.1.1.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of annealed Ti-5Al-2.5Sn alloy sheet.

VIEW INTERACTIVE GRAPH

Figure 5.3.1.1.5. Effect of temperature on the elongation (e) of annealed Ti-5Al-2.5Sn alloy sheet.

5-23

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.1.1.9(a). Fatigue-crack-propagation data for 0.084-inch-thick Ti-5Al-2.5Sn titanium alloy mill-annealed sheet. [Reference 5.3.1.1.9].

Specimen Thickness: 0.08 inch Specimen Width: 2.76 inches Specimen Type: M(T)

Environment: Lab air Temperature: RT Orientation: L-T and T-L

5-24

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.1.1.9(b). Fatigue-crack-propagation data for 0.084-inch-thick Ti-5Al-2.5Sn titanium alloy mill-annealed sheet. [Reference 5.3.1.1.9].

Specimen Thickness: 0.08 inch Specimen Width: 2.76 inches Specimen Type: M(T)

Environment: Distilled water Temperature: RT Orientation: L-T and T-L

5-25

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.1.1.9(c). Fatigue-crack-propagation data for 0.084-inch-thick Ti-5Al-2.5Sn titanium alloy mill-annealed sheet. [Reference 5.3.1.1.9].

Specimen Thickness: 0.08 inch Specimen Width: 2.76 inches Specimen Type: M(T)

Environment: 3.5% NaCl Temperature: RT Orientation: L-T and T-L

5-26

MIL-HDBK-5H 1 December 1998 5.3.2 TI-8AL-1Mo-1V 5.3.2.0 Comments and Properties — Ti-8Al-1Mo-1V alloy is a near-alpha composition developed for improved creep resistance and thermal stability up to about 850
F. The alloy is available as billet, bar, plate, sheet, strip, extrusions, and forgings. Manufacturing Considerations — Room temperature forming of Ti-8Al-1Mo-1V sheet is somewhat more difficult than in Ti-6Al-4V, and for severe operations hot forming is required. Ti-8Al-1Mo-1V can be fusion welded readily with inert-gas protection or spot welding without atmospheric protection. Weld strengths are comparable to those of the parent metal although ductility is somewhat lower in the weldment. Environmental Considerations — Ti-8Al-1Mo-1V exhibits good oxidation resistance and thermal stability up to 850
F. A decrease in tensile elongation has been reported for single-annealed sheet following 150 hours stressed exposure at 1000
F. Extended exposure to temperatures exceeding 600
F adversely affects room-temperature spot-weld tension strength. This alloy is not recommended for structural applications at liquid-hydrogen temperatures (-423
F). The Ti-8Al-1Mo-1V alloy also is susceptible to chloride stress-corrosion attack in either elevated-temperature (hot-salt stress-corrosion) or ambient-temperature (aqueous stress-corrosion) chloride environments. Thus, care should be exercised in applying the material in chloride containing environments. 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 — Three treatments are used with Ti-8Al-1Mo-1V. These are: Single Anneal: 1450
F for 8 hours, furnace cool. Duplex Anneal: 1450
F for 8 hours, furnace cool, followed by 1450
F for 15 to 20 minutes, air cool. Solution Treated and Stabilized: 1825
F for 1 hour, air cool, 1075
F for 8 hours, air cool. As a general guide, the single anneal is used to obtain highest room-temperature mechanical properties and the duplex anneal to obtain highest fracture toughness. Both the single anneal and the duplex anneal are compatible with hot-forming operations. The solution treated and stabilized condition is used for forgings. Specifications and Properties — Material specifications for Ti-8Al-1Mo-1V are presented in Table 5.3.2.0(a). Room-temperature mechanical and physical properties for Ti-8Al-1Mo-1V are shown in Tables 5.3.2.0(b) and (c). The effect of temperature on physical properties is shown in Figure 5.3.2.0.

Table 5.3.2.0(a). Material Specifications for Ti-8Al-1Mo-1V

Specification MIL-T-9046 MIL-T-9047 AMS 4973 AMS 4915 AMS 4916

Form Sheet, strip, and plate Bar Forging Sheet, strip, and plate Sheet, strip, and plate

5-27

MIL-HDBK-5H 1 December 1998 5.3.2.1 Single-Annealed Condition — Cryogenic, room-temperature, and elevated temperature property curves for this condition are shown in Figures 5.3.2.1.1 and 5.3.2.1.4. Typical tensile and compressive stress-strain and tangent-modulus curves are shown in Figures 5.3.2.1.6(a) and (b) for room temperature and several elevated temperatures. 5.3.2.2 Duplex-Annealed Condition — Cryogenic, room temperature, and elevated temperature curves for this condition are shown in Figure 5.3.2.2.1. Typical tensile and compressive stress-strain and tangent-modulus curves are shown in Figures 5.3.2.2.6(a) and (b) for room temperature and several elevated temperatures. Fatigue S/N curves for unnotched and notched specimens at room temperature and several elevated temperatures are shown in Figures 5.3.2.2.8(a) through (f).

VIEW INTERACTIVE GRAPH

Figure 5.3.2.0. Effect of temperature on the physical properties of Ti-8Al-1Mo-1V alloy.

5-28

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.3.2.0(b1). Design Mechanical and Physical Properties of Ti-8Al-1Mo-1V Sheet and Plate

Specification . . . . . . . . . . . . Form . . . . . . . . . . . . . . . . . . Condition . . . . . . . . . . . . . . Thickness, in. . . . . . . . . . . . Basis . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . Fty, ksi: L .................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . Fcy, ksi: L .................... LT . . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . e, percent: L ................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . µ .................... Physical Properties:
, lb/in.3 . . . . . . . . . . . . . . C, Btu/(lb)(
F) . . . . . . . . . K and  . . . . . . . . . . . . . . .

Sheet

< 0.1875 S

AMS 4915, MIL-T-9046, and Comp A-4 Plate Single Annealed 0.18750.5011.0010.500 1.000 2.500 S S S

2.5014.000 S

145 145 ...

145 145 ...

140 140 ...

130 130 ...

120 120 120b

135 135 ...

135 135 ...

130 130 ...

120 120 ...

110 110 110b

144 149 ... 93

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

239 294

... ...

... ...

... ...

... ...

196 214

... ...

... ...

... ...

... ...

a

10 10 ...

10 10 ... 17.5c 18.0c 6.7 0.32

10 10 ...

8 8 8b

a

...

0.158 0.12 See Figure 5.3.2.0

a 0.008-0.014 in. thickness, 6 percent; 0.015-0.024 in. thickness, 8 percent; > 0.025 in. thickness, 10 percent. b Applicable, providing ST dimension is > 3.000 inches. c Average, values may vary with test direction.

5-29

MIL-HDBK-5H 1 December 1998

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.3.2.0(b2). Design Mechanical and Physical Properties of Ti-8Al-1Mo-1V Sheet and Plate Specification . . . . . . . .

AMS 4916, MIL-T-9046, and Comp. A-4

Form . . . . . . . . . . . . . . Condition . . . . . . . . . .

Sheet

Plate Duplex Annealed

Thickness, in. . . . . . . . 0.015-0.024 0.025-0.1875 0.1875-0.500 0.501-1.000 1.001-2.000 2.001-4.000 Basis . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ............... LT . . . . . . . . . . . . . . Fty, ksi: L ............... LT . . . . . . . . . . . . . . Fcy, ksi: L ............... LT . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . (e/D = 2.0) . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . (e/D = 2.0) . . . . . . . e, percent: L ............... LT . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . Ec, 103 ksi . . . . . . . . . G, 103 ksi . . . . . . . . . µ ................ Physical Properties:
, lb/in.3 . . . . . . . . . . C, Btu/(lb)(
F) . . . . . K and  . . . . . . . . . . . a

S

S

S

S

S

S

135 135

135 135

130 130

130 130

125 125

120 120

120 120

120 120

120 120

120 120

115 115

110 110

126 126 84

126 126 84

... ... ...

... ... ...

... ... ...

... ... ...

223 269

223 269

... ...

... ...

... ...

... ...

174 191

174 191

... ...

... ...

... ...

... ...

8 8

10 10

10 10

10 10

10 10

8 8

17.5a 18.0a 6.7 0.32 0.158 0.12 See Figure 5.3.2.0

Average, L and LT; values may vary with test direction.

5-30

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.3.2.0(c). Design Mechanical and Physical Properties of Ti-5Al-2.5Sn Bar and Forging

Specification . . . . . . . . . . . . Form . . . . . . . . . . . . . . . . . . Condition . . . . . . . . . . . . . . Thickness or diameter, in. . . Basis . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . . Fty, ksi: L ................... LT . . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . . Fcy, ksi: L ................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . e, percent: L ................... LT . . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . . E, 103, ksi . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . µ .................... Physical Properties:
, lb/in.3 . . . . . . . . . . . . . . C, Btu/(lb)(
F) . . . . . . . . . K and  . . . . . . . . . . . . . . . a b c d

MIL-T-9047 Bar Duplex annealed 2.501-4.000a < 2.500a S S

AMS 4973 Forging Solution treated and stabilized < 2.499 2.500-4.000 S S

130 130b ...

120 120b 120b

130 130c ...

120 120 120

120 120b ...

110 110b 110b

120 120c ...

110 110 110

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

10 10b ...

10 10b 8b

10 10c ...

10 10 10

17.5d 18.0d 6.7 0.32 0.158 0.12 See Figure 5.3.2.0

Maximum of 16 square-inch cross-sectional area. Applicable, providing LT or ST dimension is > 3.000 inches. Applicable, providing LT dimension is > 2.500 inches. Average, values may vary with test direction.

5-31

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.1.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of single-annealed Ti-8Al-1Mo-1V alloy sheet.

5-32

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.1.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of Ti-8Al-1Mo-1V alloy sheet.

5-33

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse

.5 -hr exposure

160 RT

120

Stress, ksi

400 F 550 F

80

Ramberg - Osgood n (RT) = 33 n (400 F) = 50 n (500 F) = 50 TYPICAL

40

0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

Figure 5.3.2.1.6(a). Typical tensile stress-strain curves for single-annealed Ti-8Al-1Mo-1V alloy sheet at room and elevated temperatures.

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse

1/2 -hr exposure

RT

160

120

RT

550 F

Stress, ksi

550 F

80

Ramberg - Osgood n (RT) = 50 n (550 F) = 50

40

TYPICAL

0 0

4

8

12

16

20

24

Strain, 0.001 in./in. 3 Compressive Tangent Modulus, 10 ksi

Figure 5.3.2.1.6(b). Typical compressive stress-strain and compressive tangentmodulus curves for single-annealed Ti-8Al-1Mo-1V alloy sheet at room and elevated temperatures.

5-34

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.2.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of duplex-annealed Ti-8Al-1Mo-1V alloy sheet.

5-35

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse .5 -hr exposure

160

RT

Stress, ksi

120 400 F

550 F

80

Ramberg - Osgood n (RT) = 16 n (400 F) = 32 n (550 F) = 24 40

TYPICAL

0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

Figure 5.3.2.2.6(a). Typical tensile stress-strain curves for duplex-annealed Ti-8Al-1Mo-1V alloy sheet at room and elevated temperatures.

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse .5 -hr exposure

160

RT

RT

Stress, ksi

120 550 F

550 F

80

Ramberg - Osgood n (RT) = 50 n (500 F) = 22

40

TYPICAL

0 0

4

8

12 16 Strain, 0.001 in./in. 3 Compressive Tangent Modulus, 10 ksi

20

24

Figure 5.3.2.1.6(b). Typical compressive stress-strain and compressive tangentmodulus curves for duplex-annealed Ti-8Al-1Mo-1V alloy sheet at room and elevated temperatures.

5-36

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.2.8(a). Best-fit S/N curves for unnotched, duplex annealed T1-8Al-1Mo-1V sheet at room temperature, long transverse direction.

Correlative Information for Figure 5.3.2.2.8(a) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - RT Environment - Air

Product Form: Sheet, 0.050-inch thick Properties:

TUS, ksi

TYS, ksi

147.2

135.6

Temp.,
F RT

No. of Heats/Lots: 1

Specimen Details: Unnotched 0.750-inch net width

Equivalent Stress Equation: Surface Condition: HNO3/HF pickled References:

Log Nf = 10.57-3.46 log (Seq-66.7) Seq = Smax (1-R)0.61 Standard Error of Estimate = 0.47 Standard Deviation in Life = 0.81 R2 = 66.7%

5.3.2.2.8(a) and (b)

Sample Size = 24 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-37

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.2.8(b). Best-fit S/N curves for notched, Kt = 2.6, duplex annealed Ti-8Al-1Mo-1V sheet at room temperature, long transverse direction.

Correlative Information for Figure 5.3.2.2.8(b) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - RT Environment - Air

Product Form: Sheet, 0.050-inch thick Properties:

TUS, ksi

TYS, ksi

147.2

135.6

Temp.,
F RT Unnotched

No. of Heats/Lots: 1 Specimen Details: Notched, hole type, Kt = 2.6 1.500-inch, gross width 1.250-inch, net width 0.250-inch, diameter hole

Equivalent Stress Equation: Log Nf = 14.49-5.90 log (Seq-12.7) Seq = Smax (1-R)0.55 Standard Error of Estimate = 0.33 Standard Deviation in Life = 1.10 R2 = 90.9%

Surface Condition: HNO3/HF pickled References:

5.3.2.2.8(a) and (b)

Sample Size = 26 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-38

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.2.8(c). Best-fit S/N curves for unnotched duplex annealed T1-8Al-1Mo-1V sheet at 400°F, long transverse direction.

Correlative Information for Figure 5.3.2.2.8(c) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - 400
F Environment - Air

Product Form: Sheet, 0.050-inch thick Properties:

TUS, ksi

TYS, ksi

119.5

100.8

Temp.,
F 400

No. of Heats/Lots: 1

Specimen Details: Unnotched 0.750-inch net width

Equivalent Stress Equation: Surface Condition: HNO3/HF pickled References:

Log Nf = 8.30-2.53 log (Seq-73.9) Seq = Smax (1-R)0.74 Standard Error of Estimate = 0.38 Standard Deviation in Life = 0.87 R2 = 80.9%

5.3.2.2.8(a) and (b)

Sample Size = 23 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-39

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.2.8(d). Best-fit S/N curves for notched, Kt = 2.6, duplex annealed Ti-8Al-1Mo-1V sheet at 400°F, long transverse direction.

Correlative Information for Figure 5.3.2.2.8(d) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - 400
F Environment - Air

Product Form: Sheet, 0.050-inch thick Properties:

TUS, ksi

TYS, ksi

119.5

100.8

Temp.,
F 400 Unnotched

No. of Heats/Lots: 1 Specimen Details: Notched, hole type, Kt = 2.6 1.500-inch, gross width 1.250-inch, net width 0.250-inch, diameter hole

Equivalent Stress Equation: Log Nf = 13.39-5.68 log (Seq-18.7) Seq = Smax (1-R)0.46 Standard Error of Estimate = 0.41 Standard Deviation in Life = 1.16 R2 = 87.2%

Surface Condition: HNO3/HF pickled References:

5.3.2.2.8(a) and (b)

Sample Size = 20 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-40

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.2.8(e). Best-fit S/N curves for unnotched duplex anneled Ti-8Al-1Mo-1V sheet at 650°F, long transverse direction.

Correlative Information for Figure 5.3.2.2.8(e) Product Form: Sheet, 0.050-inch thick Properties:

TUS, ksi

TYS, ksi

110.2

86.8

Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - 650
F Environment - Air

Temp.,
F 650

No. of Heats/Lots: 1

Specimen Details: Unnotched 0.750-inch, net width

Equivalent Stress Equation: Surface Condition: HNO3/HF pickled References:

Log Nf = 9.83-3.66 log (Seq-73) Seq = Smax (1-R)0.78 Standard Error of Estimate = 0.88 Standard Deviation in Life = 1.18 R2 = 44.3%

5.3.2.2.8(a) and (b)

Sample Size = 20 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-41

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.2.2.8(f). Best-fit S/N curves for notched, Kt = 2.6, duplex annealed Ti-8Al-1Mo-1V sheet at 650°F, long transverse direction.

Correlative Information for Figure 5.3.2.2.8(f) Test Parameters: Loading - Axial Frequency - 1800 cpm Temperature - 650
F Environment - Air

Product Form: Sheet, 0.050-inch thick Properties:

TUS, ksi

TYS, ksi

110.2

86.8

Temp.,
F 650 Unnotched

No. of Heats/Lots: 1 Specimen Details: Notched, hole type, Kt = 2.6 1.500-inch, gross width 1.250-inch, net width 0.250-inch, diameter hole

Equivalent Stress Equation: Log Nf = 10.16-3.88 log (Seq-23) Seq = Smax (1-R)0.69 Standard Error of Estimate = 0.38 Standard Deviation in Life = 0.65 R2 = 66.0%

Surface Condition: HNO3/HF pickled References:

5.3.2.2.8(a) and (b)

Sample Size = 22 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-42

MIL-HDBK-5H 1 December 1998 5.3.3 Ti-6Al-2Sn-4Zr-2Mo 5.3.3.0 Comments and Properties — Ti-6Al-2Sn-4Zr-2Mo is a near-alpha titanium composition developed for improved elevated-temperature performance. The alloy has a titanium-aluminum base that is solid solution strengthened by additions of tin and zirconium. Molybdenum improves both room and elevated temperature strength, creep and thermal stability. Introduction of this alloy initially met the requirements for certain advanced performance gas turbine engine applications. Some of the more recent applications, however, require better creep strength than the alloy initially provided. Development work showed that a small addition of silicon, approximately 0.08 percent, substantially improved the creep strength of the alloy without significantly affecting the thermal stability. The alloy is creep resistant and relatively stable to about 1050
F. Creep and thermal stability of the alloy are further enhanced by solution treating high in the alpha-beta phase field. The alloy is available in bar, billet, plate, sheet, strip, and extrusions. Manufacturing Conditions — Forging of Ti-6Al-2Sn-4Zr-2Mo at temperatures below the beta transus temperature is recommended. For optimum creep properties beta forging or a modification of it is recommended with some loss in ductility to be expected. Elevated temperatures may be used for severe sheet forming operations while room-temperature forming may be used for mild contouring. Stress relief annealing may be combined with a final hot-sizing operation. The material can be welded using TIG or MIG fusion processes to achieve 100 percent joint efficiencies but with limited weld zone ductility. As in welding any titanium alloy, shielding from atmospheric contamination is required except for spot or seam welding. Environmental Considerations — Ti-6Al-2Sn-4Zr-2Mo is somewhat more resistant to hot-salt cracking than either Ti-8Al-1Mo-1V or Ti-6Al-4V alloys. The material is marginally susceptible to aqueous chloride solution stress-corrosion cracking. Surface oxides formed during exposure to service temperature (~950
F) do not adversely affect properties. 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 — Several different annealing treatments, which are described below, are available for Ti-6Al-2Sn-4Zr-2Mo. For sheet and strip: Duplex Anneal:

1650
F for ½ hour, air cool, followed by 1450
F for ¼ hour, and air cool.

Triplex Anneal: 1650
F for ½ hour, air cool, followed by 1450
F for ¼ hour, air cool, followed by 1100
F for 2 hours and air cool. For plate: Duplex Anneal: 1650
F for 1 hour, air cool, followed by 1100
F for 8 hours and air cool. Triplex Anneal: 1650
F for ½ hour, air cool, followed by 1450
F for ¼ hour, air cool, followed by 1100
F for 2 hours and air cool. For bars and forgings: Duplex Anneal: Solution anneal 25 to 50
F below beta transus temperature for 1 hour, air cool or faster, followed by 1100
F for 8 hours and air cool.

5-43

MIL-HDBK-5H 1 December 1998

Table 5.3.3.0(a). Material Specifications for Ti-6Al-2Sn-4Zr-2Mo

Specification MIL-T-9046 AMS 4975 AMS 4976 AMS 4919

Form Sheet and strip Bar Forging Sheet, strip, and plate

Specifications and Properties — Material specifications for Ti-6Al-2Sn-4Zr-2Mo are given in Table 5.3.3.0(a). Room-temperature mechanical and physical properties for Ti-6Al-2Sn-4Zr-2Mo are presented in Table 5.3.3.0(b) and (c). The effect of temperature on physical properties is shown in Figure 5.3.3.0. 5.3.3.1 Single, Duplex,and Triplex Annealed — Room and elevated temperature property curves are shown in Figures 5.3.3.1.1, 5.3.3.1.2, and 5.3.3.1.4. Typical stress-strain curves at room and elevated temperatures are shown in Figures 5.3.3.1.6(a) and (b). Full range stress-strain curves at room and elevated temperatures are shown in Figure 5.3.3.1.6(c).

5-44

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.3.3.0(b). Design Mechanical and Physical Properties of Ti-6Al-2Sn-4Zr-2Mo Supercedes page 5-45 of MIL-HDBK-5H

Specification . . . . . . . . . . .

AMS 4919

AMS-T-9046, Comp. AB-4

Form . . . . . . . . . . . . . . . . .

Sheet

Condition . . . . . . . . . . . . . .

Duplex annealed #0.046

Thickness or diameter, in. . Basis . . . . . . . . . . . . . . . . .

a b c d e

0.094-0.140

0.141-0.187

#0.187

A

B

A

B

A

B

A

B

Sa

135b 135b

143 143

135b 135b

143 143

135b 135b

143 143

135b 135b

143 143

145 145

125c 125c

136 134

125c 125c

136 134

125c 125c

136 134

125c 125c

136 134

135 135

132 132 ...

142 142 ...

132 132 ...

142 142 ...

132 132 ...

142 142 ...

132 132 ...

142 142 ...

... ... ...

195 217

206 230

205 243

217 258

214 266

227 282

219 279

232 295

... ...

171 202

183 217

171 202

183 217

171 202

183 217

171 202

183 217

... ...

8e 8e

... ...

e e

... ...

10 10

... ...

10 10

... ...

e e

E, 103 ksi . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . F ..................

16.5 18.0 6.2 0.32

Physical Properties: ω, lb/in.3 . . . . . . . . . . . . . . C, K and α . . . . . . . . . . . .

0.164 See Figure 5.3.3.0

S-basis values are representative of test specimens excised from duplex annealed material and thermally treated to triplex annealed condition in a laboratory furnace. S-basis. The rounded T99 values are as follows: Ftu(L<) = 139 ksi. S-basis. The rounded T99 values are as follows: Fty(L) = 131 ksi and Fty(LT) = 129 ksi. Bearing values are “dry pin” values per Section 1.4.7.1. 8% for 0.025 through 0.062 inch and 10% for >0.062 inch.

MIL-HDBK-5H, Change Notice 1 1 October 2001

5-45

Mechanical Properties: Ftu, ksi: L .................. LT . . . . . . . . . . . . . . . . . . Fty, ksi: L .................. LT . . . . . . . . . . . . . . . . . . Fcy, ksi: L .................. LT . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . Fbrud, ksi: (e/D=1.5) . . . . . . . . . . . . (e/D=2.0) . . . . . . . . . . . . Fbryd, ksi: (e/D=1.5) . . . . . . . . . . . . (e/D=2.0) . . . . . . . . . . . . e, percent (S-basis): L .................. LT . . . . . . . . . . . . . . . . . .

0.047-0.093

Triplex annealed

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.3.3.0(c). Design Mechanical and Physical Properties of Ti-6Al-2Sn-4Zr-2Mo

Specification...............................

AMS 4975

AMS 4976

Form...........................................

Bar

Forging

Condition....................................

STA (Duplex annealed)

STA (Duplex annealed)

Cross-Sectional area, in.2...........

16

9

Thickness, or diameter, in..........

3.000

3.000

Basis........................................... Mechanical Properties: Ftu, ksi: L............................................ LT.......................................... ST.......................................... Fty, ksi: L............................................ LT.......................................... ST.......................................... Fcy, ksi: L............................................ LT.......................................... ST.......................................... 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): L............................................ LT.......................................... ST.......................................... RA, percent (S basis): L............................................ LT.......................................... ST..........................................

A

B

S

130a 130b 130b

144 ... ...

130 130b 130b

120a 120b 120b

131 ... ...

120 120b 120b

... ... ... ...

... ... ... ...

... ... ... ...

... ...

... ...

... ...

... ...

... ...

... ...

10 10b 10b

... ... ...

10 10b 10b

25 25b 25b

... ... ...

25 25b 25b

E, 103 ksi................................. Ec, 103 ksi................................ G, 103 ksi................................. ...............................................

16.5 18.0 6.2 0.32

Physical Properties:
, lb/in.3................................... C, K, and ..............................

0.164 See Figure 5.3.3.0

a S basis. The rounded T99 values are as follows: Ftu(L) = 138 ksi and Fty(L) = 125 ksi. b S basis. Applicable providing transverse dimension is
2.500 in.

REPRINTED WITHOUT CHANGE.

5-46

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.3.0. Effect of temperature on the physical properties of Ti-6Al-2Sn-4Zr-2Mo alloy.

VIEW INTERACTIVE GRAPH

Figure 5.3.3.1.1. Effect of temperature on the tensile ultimate strength (Ftu) and tensile yield strength (Fty) of duplex- and triplex-annealed Ti-6Al-2Sn-4Zr-2Mo (all products).

5-47

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.3.1.2. Effect of temperature on the compressive yield strength (Fcy) of duplex annealed Ti-6Al-2Sn-4Zr-2Mo alloy sheet.

VIEW INTERACTIVE GRAPH

Figure 5.3.3.1.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of duplex-annealed Ti-6Al-2Sn-4Zr-2Mo alloy.

5-48

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 Longitudinal .5 -hr exposure 160 RT

Stress, ksi

120

900 F

80 Ramberg - Osgood n (RT) = 34 n (900 F) = 10 TYPICAL

40

Thickness = 1.125 - 1.250 in.

0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

Figure 5.3.3.1.6(a). Typical tensile stress-strain curves for duplex-annealed Ti-6Al-2Sn-4Zr-2Mo alloy bar at various temperatures.

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse .5 -hr exposure

160

RT

Stress, ksi

120 900 F

80 Ramberg - Osgood n (RT) = 35 n (900 F) = 12 40

TYPICAL Thickness = 0.048 - 0.085 in.

0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

Figure 5.3.3.1.6(b). Typical tensile stress-strain curves for duplex- and triplexannealed Ti-6Al-2Sn-4Zr-2Mo alloy sheet at various temperatures.

5-49

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.3.3.1.6(c). Typical tensile stress-strain curves (full-range) for duplexannealed Ti-6Al-2Sn-4Zr-2Mo alloy sheet at room and elevated temperatures.

5-50

MIL-HDBK-5H 1 December 1998

5.4 ALPHA-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 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. 5.4.1 TI-6AL-4V 5.4.1.0 Comments 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.

5-51

MIL-HDBK-5H 1 December 1998 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. Table 5.4.1.0(a) Material Specifications for Ti-6Al-4V Specification MIL-T-9046 MIL-T-9047 AMS 4934 AMS 4935 AMS 4967 AMS 4928 AMS 4911 AMS 4920 AMS 4962

Form Sheet, strip, and plate Bar Extrusion Extrusion Bar Bar and die forging Sheet, strip, and plate Die forging Investment casting

5.4.1.1 Annealed 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. 5.4.1.2 Solution-Treated and Aged Condition — Elevated temperature curves for solutiontreated 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).

5-52

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.1.0(b). Design Mechanical and Physical Properties of Ti-6Al-4V Sheet, Strip, and Plate

Specification . . . . . . . .

AMS 4911 and MIL-T-9046, Comp. AB-1

Form . . . . . . . . . . . . . .

Sheet

Condition . . . . . . . . . .

Plate

Sheet, strip, and plate

Annealed

Solution treated and aged 2.0014.000

 0.1875

0.18750.750

0.7511.000

1.0012.000

B

S

S

S

S

S

130a 130a

135 138

130 130

160 160

160 160

150 150

145 145

131 131

120 120a

125 131

120 120

145 145

145 145

140 140

135 135

138 141 90

124 130 79

129 142 84

124 130 79

154 162 100

150 ... 93

145 ... 87

... ... ...

213b 221b 272b 283b

206b 260b

214b 276b

206b 260b

236 286

248 308

233 289

... ...

171b 178b 208b 217b

164b 194b

179b 212b

164b 194b

210 232

210 243

203 235

... ...

10 10

... ...

10 10

5d 5d

8 8

6 6

6 6

Thickness, in. . . . . . . .

 0.1875

Basis . . . . . . . . . . . . . .

A

B

A

134 134

139 139

126 126 133 135 87

Mechanical Properties: Ftu, ksi: L ............. LT . . . . . . . . . . . . Fty, ksi: L ............. LT . . . . . . . . . . . . Fcy, ksi: L ............. LT . . . . . . . . . . . . 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): L ............. LT . . . . . . . . . . . .

MIL-T-9046, Comp. AB-1

8c 8c

... ...

0.1875-2.000

E, 103 ksi . . . . . . . . . Ec, 103 ksi . . . . . . . . G, 103 ksi . . . . . . . . . µ ................

16.0 16.4 6.2 0.31

Physical Properties:
, lb/in.3 . . . . . . . . . C, K, and  . . . . . . .

0.160 See Figure 5.4.1.0

a The rounded T99 values are higher than specification values as follows: Ftu(L) = 131 ksi, Ftu(LT) = 132 ksi, and Fty(LT) = 123 ksi. b Bearing values are “dry pin” values per Section 1.4.7.1. c 8%—0.025 to 0.062 in. and 10%—0.063 in. and above. d 5%—0.050 in. and above; 4%—0.033 to 0.049 in. and 3%—0.032 in. and below.

5-53

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.1.0(c1). Design Mechanical and Physical Properties of Ti-6Al-4V Bar Specification . . . . . . . . . . . . .

AMS 4928

Form . . . . . . . . . . . . . . . . . . . .

Bar

Condition . . . . . . . . . . . . . . . .

Annealed <0.500

0.500-1.000

1.001-2.000

2.001-3.000

3.001-4.000

4.001-5.000

5.001-6.000

Basis . . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L .................. LT . . . . . . . . . . . . . . . . . Fty, ksi: L .................. LT . . . . . . . . . . . . . . . . . Fcy, ksi: L .................. LT . . . . . . . . . . . . . . . . . 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): L .................. LT . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . RA, percent (S-basis): L .................. LT . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . µ .................... Physical Properties:
, lb/in.3 . . . . . . . . . . . . . . C, K, and  . . . . . . . . . . . .

S

A

B

A

B

A

B

A

B

A

B

A

B

135 135b

135a 135a

142 144

134 135a

140 143

130a 130a

138 142

130 130a

135 141

128 130a

133 139

125 130a

131 138

125 125b

125a 125a

134 134

125a 125a

131 132

120a 120a

128 131

120 120a

125 129

117 120a

122 127

114 119

119 125

129 ... 83

129 ... 83

138 ... 87

129 ... 82

135 ... 86

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

201 253

201 253

212 266

200 251

209 262

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

177 205

177 205

190 220

177 205

186 215

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

10 10b ...

10 10b ...

... ... ...

10 10b ...

... ... ...

10 10b 10b

... ... ...

10 10 10

... ... ...

10 10 8

... ... ...

10 10 8

... ... ...

25 20b ...

25 20b ...

... ... ...

25 20b ...

... ... ...

25 20b 15b

... ... ... 16.9 17.2 6.2 0.31

25 20 15

... ... ...

20 20 15

... ... ...

20 20 15

... ... ...

a S-basis. The rounded T99 values are shown in Table 5.4.1.0(c2). b Applicable, providing LT or ST dimension is
2.500 inches.

0.160 See Figure 5.4.1.0

MIL-HDBK-5H 1 December 1998

5-54

Thickness or diameter, in. . . .

MIL-HDBK-5H 1 December 1998

Table 5.4.1.0(c2). Rounded T99 Values for Tensile Yield and Ultimate Strength of Ti-6Al-4V Bar

0.5001.000

1.0012.000

2.0013.000

3.0014.000

4.0015.000

5.0016.000

L .....................

137

...

132

...

...

...

LT . . . . . . . . . . . . . . . . . . . .

140

139

138

136

135

134

L .....................

129

126

123

...

...

...

LT . . . . . . . . . . . . . . . . . . . .

129

127

127

123

121

...

Thickness or diameter, in. . . . . Mechanical Properties: Ftu, ksi:

Fty, ksi:

5-55

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.1.0(c3). Design Mechanical and Physical Properties of Ti-6Al-4V Bar and Plate Specification . . . . . . . . . . . .

MIL-T-9047

Form . . . . . . . . . . . . . . . . . .

Bar

Condition . . . . . . . . . . . . . .

Annealed

Cross-sectional area, in.2 . . .

<48

Thickness, in. . . . . . . . . . . . Basis . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L .................. LT . . . . . . . . . . . . . . . . . Fty, ksi: L .................. LT . . . . . . . . . . . . . . . . . Fcy, ksi: L .................. LT . . . . . . . . . . . . . . . . . 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): L .................. LT . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . . RA, percent (S-basis): L .................. LT . . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . .

<0.500 S

0.5001.000 A

B

1.0012.000 A

B

2.0013.000 A

B

3.0014.000 A

B

4.0015.000 A

B

5.0016.000 A

B

130 130b

130a 142 130a 140 130a 138 130 135 128 133 125 130a 144 130a 143 130a 142 130a 141 130a 139 130a

131 138

120 120b

120a 134 120a 131 120a 128 120 125 120a 134 120a 132 120a 131 120a 129

124 ... 80

124 ... 80

138 ... 87

124 ... 80

135 ... 86

... ... ...

... ... ...

... ... ...

194 244

194 244

212 266

194 244

209 262

... ...

... ...

170 197

170 197

190 220

170 197

186 215

... ...

10 10b ...

10 10b ...

... ... ...

10 10b ...

... ... ...

25 25b ...

25 25b ...

... ... ...

25 25b ...

... ... ...

E, 103 ksi . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . µ ...................

117 120

122 127

114 119

119 125

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

10 10b ...

... ... ...

10 10 8

... ... ...

10 10 8

... ... ...

10 10 8

... ... ...

25 25b ...

... ... ...

25 25 15

... ... ...

20 20 15

... ... ...

20 20 15

... ... ...

16.9 17.2 6.2 0.31

Physical Properties:
, lb/in.3 . . . . . . . . . . . . . C, K, and  . . . . . . . . . . .

0.160 See Figure 5.4.1.0

a S-basis. The rounded T99 values are shown in Table 5.4.1.0(c4). b Applicable, providing LT dimension is >3.000 inches.

5-56

MIL-HDBK-5H 1 December 1998

Table 5.4.1.0(c4). Rounded T99 Values for Tesile and Ultimate Strength of Ti-6Al-4V Bar

0.5001.000

1.0012.000

2.0013.000

3.0014.000

4.0015.000

5.0016.000

L .....................

137

134

132

...

...

...

LT . . . . . . . . . . . . . . . . . . . .

140

139

138

136

135

134

L .....................

129

126

123

...

...

...

LT . . . . . . . . . . . . . . . . . . . .

129

127

125

123

121

...

Thickness or diameter, in. . . . . Mechanical Properties: Ftu, ksi:

Fty, ksi:

5-57

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.1.0(d). Design Mechanical and Physical Properties of Ti-6Al-4V Bar Specification . . . . . . . .

AMS 4967a and MIL-T-9047

MIL-T-9047

Form . . . . . . . . . . . . . .

Rectangular bar

Round, square, and hexagon bar

Condition . . . . . . . . . . .

Solution treated and aged

Width, in. . . . . . . . . . . .

0.5018.000

Thickness, in.


0.500

.......

Basis . . . . . . . . . . . . . .

4.0018.000

1.5014.000

4.0018.000

2.0014.000

4.0018.000

3.0018.000

4.0018.000

...

...

...

...

...

2.0013.000

3.0014.000


0.500

0.5011.000

1.0011.500

1.5012.000

2.0013.000

0.501-1.000

1.001-1.500

1.501-2.000

S

S

S

S

S

S

S

S

S

S

S

S

S

S

160 160

155 155

150 150

150 150

145 145

145 145

140 140

135 135

130 130

165 165

160 160

155 155

150 150

140 140

150 150

145 145

140 140

140 140

135 135

135 135

130 130

125 125

120 120

155 155

150 150

145 145

140 140

130 130

... ... 92

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

10 10

10 10

10 10

10 10

10 10

10 10

10 10

10 10

8 8

10 10

10 10

10 10

10 10

10 10

25 25

20 20

20 20

20 20

20 20

20 20

20 20

20 20

15 15

20 20

20 20

20 20

20 20

20 20

E, 103 ksi . . . . . . . . . Ec, 103 ksi . . . . . . . . G, 103 ksi . . . . . . . . . µ ............... Physical Properties:
, lb/in.3 . . . . . . . . . C, K, and  . . . . . . . a For AMS 4967, e and RA values may be different than those shown.

16.9 17.2 6.2 0.31 0.160 See Figure 5.4.1.0

MIL-HDBK-5H 1 December 1998

5-58

Mechanical Properties: Ftu, ksi: L ............ LT . . . . . . . . . . . Fty, ksi: L ............ LT . . . . . . . . . . . Fcy, ksi: L ............ LT . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . (e/D = 2.0) . . . . . Fbry, ksi: (e/D = 1.5) . . . . . (e/D = 2.0) . . . . . e, percent: L ............ LT . . . . . . . . . . . RA, percent: L ............ LT . . . . . . . . . . .

1.0014.000

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.1.0(e). Design Mechanical and Physical Properties of Ti-6Al-4V Extrusion

a b c d

AMS 4935

AMS 4934 Extrusion


2.000 A

Annealed 2.001-3.000 B A B

<0.500 A B

0.501-0.750 A B

Solution treated and aged 0.751-1.000 1.001-2.000 A B S

2.001-3.000 S

130a 130a

137 139

130b 130b

135 139

155 155

163 163

151 151

157 157

147 147

153 155

140 140

130 130

120 120a

124 128

118 120

122 125

138 138

147 147

138 138

143 145

133 133

140 142

130 130

120 120

128 129 83

133 138 89

124 ... ...

128 ... ...

147 147 94

157 157 99

147 147 92

153 155 96

142 139 89

150 152 93

139 139 85

128 128 79

214 264

226 278

... ...

... ...

243 311

256 327

237 303

246 315

231 295

240 307

220 281

204 261

180 210

186 217

... ...

... ...

208 242

222 257

208 242

216 250

201 233

212 245

196 228

182 210

10 8

... ...

10 8

... ...

6 6

... ...

6 6

... ...

6 6

... ...

6 6

6 6

20 15

... ...

20 15

... ...

12 12

... ...

12 12

... ...

12 12

... ...

12 12

12 12

16.9 17.2 6.2 0.31 0.160 See Figure 5.4.1.0

S-basis. The rounded T99 values are higher than specification values as follows: Ftu (L) and (LT) = 132 ksi and Fty (LT) = 121 ksi. S-basis. The rounded T99 values are higher than specification values as follows: Ftu (L) = 132 ksi and Ftu (LT) = 136 ksi. Bearing values are “dry pin” values per Section 1.4.7.1. Applicable, providing LT dimension is
2.500 inches.

MIL-HDBK-5H 1 December 1998

5-59

Specification . . . . . . . . . . . . . . . . . . . Form . . . . . . . . . . . . . . . . . . . . . . . . . Condition . . . . . . . . . . . . . . . . . . . . . Thickness or diameter, in. . . . . . . . . Basis . . . . . . . . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L .................... LTd . . . . . . . . . . . . . . . . . . Fty, ksi: L .................... LTd . . . . . . . . . . . . . . . . . . Fcy, ksi: L .................... LTd . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . . . . . Fbruc, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . Fbryc, ksi: (e/D = 1.5) . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . e, percent (S-basis): L .................... LTd . . . . . . . . . . . . . . . . . . RA, percent (S-basis): L .................... LTd . . . . . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . . . . µ ........................ Physical Properties:
, lb/in.3 . . . . . . . . . . . . . . . . . . C, K, and  . . . . . . . . . . . . . . . .

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.1.0(f). Design Mechanical and Physical Properties of Ti-6Al-4V Die Forging

Specification . . . . . . .

AMS 4928

Form . . . . . . . . . . . . . Condition . . . . . . . . .

AMS 4920 Die forging

Alpha-beta processed, annealed

Alpha-beta or beta processed, annealed

Thickness, in. . . . . . .

2.000

2.001-4.000

4.001-6.000

2.000

2.001-6.000

Basis . . . . . . . . . . . . .

S

S

S

S

S

135 135a ...

130 130a 130a

130 130 130

130 130a ...

130 130a 130a

125 125a ...

120 120a 120a

120 120 120

120 120a ...

120 120a 120a

... ... ... ...

123 128 ... 79

123 128 ... 79

... ... ... ...

123 128 ... 79

... ...

203 257

203 257

... ...

203 257

... ...

171 201

171 201

... ...

171 201

10 10a ...

10 10a 10a

10 10 8

8 8a ...

8 8a 8a

25 20a ...

25 20a 15a

20 20 15

15 15a ...

15 15a 15a

Mechanical Properties: Ftu, ksi: L .......... LT . . . . . . . . . ST . . . . . . . . . Fty, ksi: L .......... LT . . . . . . . . . ST . . . . . . . . . Fcy, ksi: L .......... LT . . . . . . . . . ST . . . . . . . . . Fsu, ksi . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . (e/D = 2.0) . . . Fbry, ksi: (e/D = 1.5) . . . (e/D = 2.0) . . . e, percent: L .......... LT . . . . . . . . . ST . . . . . . . . . RA, percent: L .......... LT . . . . . . . . . ST . . . . . . . . . E, 103 ksi . . . . . . . . Ec, 103 ksi . . . . . . . . G, 103 ksi . . . . . . . µ ..............

16.9 17.2 6.2 0.31

Physical Properties:
, lb/in.3 . . . . . . . . C, K, and  . . . . . .

0.160 See Figure 5.4.1.0

a Applicable providing LT or ST dimension is
2.500 inches.

5-60

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.1.0(g). Design Mechanical and Physical Properties of Ti-6Al-4V Titanium Alloy Casting

Specification . . . . . . . . . . . . . . . . . .

AMS 4962

Form . . . . . . . . . . . . . . . . . . . . . . . .

HIP Casting

Temper . . . . . . . . . . . . . . . . . . . . . .

Annealed

Thickness, in. . . . . . . . . . . . . . . . . .


1.000

Location within casting . . . . . . . . . .

Designated area

Basis . . . . . . . . . . . . . . . . . . . . . . . .

A

B

Mechanical Properties: Ftu, ksi . . . . . . . . . . . . . . . . . . . . . .

125a

128

Fty, ksi . . . . . . . . . . . . . . . . . . . . . .

119

122

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

...

3

E, 10 ksi . . . . . . . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . . . . . . µ ..........................

16.9 16.9 ... ...

Physical Properties:
, lb/in.3 . . . . . . . . . . . . . . . . . . . . C, Btu/(lb)(F) . . . . . . . . . . . . . . . K, Btu/[(hr)(ft2)(F)/ft] . . . . . . . . . , 10-6 in./in./F . . . . . . . . . . . . . .

... ... ... ...

a S-basis. The T99 value is 126.36 ksi.

5-61

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 6

9

5

8

4

7

3

-6

10

, 10 in./in./F

.

6

2

K, Btu/[(hr)(ft )(F)/ft]

K

5

4

- Between 70 F and indicated temperature K - At indicated temperature C - At indicated temperature

0.3

2

0.2

C 1

0

0.1

-400

-200

0

200

400

600

800

1000

1200

1400

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

5-62

0.0 1600

C, Btu/(lb)(F)

3

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 .

Strength at temperature Exposure up to 1/2 hr

Percentage of Room Temperature Strength

180

Fty

160

140

120

100

80

Ftu

60

Fty 40

20

0

-400

-200

0

200

400

600

800

1000

Temperature, F 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).

5-63

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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).

VIEW INTERACTIVE GRAPH

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

5-64

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

VIEW INTERACTIVE GRAPH

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

5-65

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 280 Ramberg - Osgood n (-423 °F) = 20 n (-321 °F) = 21 n (-110 °F) = 20 n (RT) = 33 n (400 °F) = 29 n (700 °F) = 19 n (900 °F) = 9.6

240

Stress, ksi

200

-423 °F

-321 °F -110 °F

160 RT 120 400 °F 700 °F 900 °F

80

40

1/2 -hr exposure TYPICAL

0 0

4

8

12

16

Strain, 0.001 in./in. 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.

5-66

20

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 .5 -hr exposure Longitudinal 160 RT

400 F

Stress, ksi

120

700 F 900 F

80

Ramberg - Osgood n (RT) = 21 n (400 F) = 19 n (700 F) = 14 n (900 F) = 9.8

40

TYPICAL 0 0

4

8

12

16

20

Strain, 0.001 in./in.

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

VIEW INTERACTIVE GRAPH 200 .5 -hr exposure Longitudinal

160 RT

120

Stress, ksi

400 F Ramberg - Osgood n (RT) = 21 n (400 F) = 19 n (700 F) = 14 n (900 F) = 9.8

700 F 80 900 F

TYPICAL

40

0 0

4

8

12

16

20

24

3

Compressive Tangent Modulus, 10 ksi

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

5-67

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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

5-68

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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, 1-1/4-inch diameter Properties: TUS, ksi 137

TYS, ksi 129

Temp.,°F RT

Specimen Details: Unnotched 0.280-inch diameter

Test Parameters: Loading — Axial Frequency — 1800 cpm Temperature — RT Environment — Air No. of Heats/Lots: Not specified

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

Equivalent Strain Equation:

Reference: 5.4.1.1.8(a)

Sample Size = 134

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

5-69

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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

Product Form: Bar, 1-inch diameter Properties: TUS, ksi 150

TYS, ksi 143

Temp. °F RT

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

No. of Heats/Lots: Not specified Equivalent Strain Equation: Log Nf = 24.1-10.7 log Seq Seq = Smax(1-R)0.49 Standard Error of Estimate = 0.677 Standard Deviation in Life = 0.920 R2 = 46%

Surface Condition: RMS 100 machined Reference: 5.4.1.1.8(a)

Sample Size = 46 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-70

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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, ksi 143

TYS, ksi 127

Temp. °F RT

Specimen Details: Unnotched 1.50-inch gross width 0.75-inch net width 4.00-inch net section radius Surface Conditions: Reference: 5.4.1.1.8(b)

RMS 63

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) Standard Error of Estimate = 0.41 Standard Deviation in 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.]

5-71

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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, ksi 143

TYS, ksi 127

Temp. °F 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: Reference: 5.4.1.1.8(b)

RMS 63

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 Standard Error of Estimate = 0.41 Standard Deviation in 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.]

5-72

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH

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

Product Form: Extrusion, 0.300- and 0.560-inch thick Properties: TUS, ksi 112 101

TYS, ksi 92 77

Temp.,°F 400 600

No. of Heats/Lots: Not specified 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:

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%

RMS 63

Reference: 5.4.1.1.8(b)

Sample Size = 47 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.] Supersedes page 5-73 of MIL-HDBK-5H

5-73

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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) Test Parameters:

Product Form: Sheet, 0.063, 0.070, 0.078-inch thick Properties: TUS, ksi 147-152

TYS, ksi 136-143

Loading — Axial Frequency — 10-95 Hz Temperature — RT Environment — Air

Temp.,°F RT

Specimen Details: Unnotched, 0.375-inch width

No. of Heats/Lots: 3

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

Equivalent Strain Equation: Log Nf = 12.59-4.89 log (Seq-82.8) Seq = Smax(1-R)0.29 Standard Deviation of Log Life = 0.62 Adjusted R2 = 50.6%

Reference: 5.4.1.1.8(c)

Sample Size:

47

[Caution: The equivalent strain model may provide unrealistic life predictions for strain ratios and ranges beyond those represented above.] REPRINTED WITHOUT CHANGE.

5-74

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.4.1.1.8(g). Best-fit S/N curves for notched, Kt = 3.0, annealed Ti-6Al-4V annealed sheet, longitudinal and long transverse direction. Correlative Information for Figure 5.4.1.1.8(g)

Test Parameters:

Product Form: Sheet, 0.063, 0.070, 0.078-inch thick Properties: TUS, ksi 145-152

TYS, ksi 136-146

Loading — Axial Frequency — 10-95 Hz Temperature — RT Environment — Air

Temp. °F RT

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

No. of Heats/Lots: 3

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

Equivalent Strain Equation: Log Nf = 19.28-8.25 log (Seq) Seq = Smax(1-R)0.57 Standard Deviation of Log Life = 0.53 Adjusted R2 = 62.5%

Reference: 5.4.1.1.8(c)

Sample Size:

141

[Caution: The equivalent strain model may provide unrealistic life predictions for strain ratios and ranges beyond those represented above.]

5-75

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.4.1.1.9. Fatigue-crack-propagation data for 0.025-inch-thick Ti-6Al-4V mill-annealed titanium alloy plate with buckling restraint. [Reference 5.4.1.1.9.] Specimen Thickness: Specimen Width: Specimen Type:

0.250 inch 9.6, 16, 32 inches M(T)

5-76

Environment: Temperature: Orientation:

50% R.H. RT L-T

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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).

5-77

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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).

VIEW INTERACTIVE GRAPH

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).

5-78

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse 160

RT

.5 -hr exposure

200 F 400 F

120

Stress, ksi

600 F 800 F

80 1000 F Ramberg - Osgood n (RT) = 16 n (200 F) = 22 n (400 F) = 15 n (600 F) = 11 n (800 F) = 9.4 n (1000 F) = 6.2

40

TYPICAL

0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

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.

5-79

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 .5 -hr exposure Longitudinal RT 160

200 F

400 F 600 F

Stress, ksi

120

800 F 1000 F 80

Ramberg - Osgood n (RT) = 22 n (200 F) = 27 n (400 F) = 22 n (600 F) = 12 n (800 F) = 11 n (1000 F) = 5.7

40

TYPICAL 0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

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.

VIEW INTERACTIVE GRAPH 200 .5 -hr exposure

RT

Longitudinal 200 F

160

400 F

Stress, ksi

120 600 F

Ramberg - Osgood n (RT) = 22 n (200 F) = 27 n (400 F) = 22 n (600 F) = 12 n (800 F) = 11 n (1000 F) = 5.7

1000 F 80

800 F

TYPICAL

40

0 0

4

8

12

16

20

24

3

Compressive Tangent Modulus, 10 ksi

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

5-80

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 .5 -hr exposure

RT

Long Transverse 200 F 160 400 F 600 F 800 F

Stress, ksi

120

1000 F

80 Ramberg - Osgood n (RT) = 13 n (200 F) = 15 n (400 F) = 14 n (600 F) = 10 n (800 F) = 11 n (1000 F) = 5.7

40

TYPICAL 0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

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

VIEW INTERACTIVE GRAPH 200

RT .5 -hr exposure

200 F

Long Transverse 160 400 F 600 F 120

Stress, ksi

800 F

1000 F

Ramberg - Osgood n (RT) = 13 n (200 F) = 15 n (400 F) = 14 n (600 F) = 10 n (800 F) = 11 n (1000 F) = 5.7

80

40 TYPICAL

0 0

4

8

12

16

20

24

3

Compressive Tangent Modulus, 10 ksi

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

5-81

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse 160

RT

.5 -hr exposure

120

Stress, ksi

400 F 600 F 800 F Ramberg - Osgood n (RT) = 20 n (400 F) = 19 n (600 F) = 15 n (800 F) = 11

80

40

TYPICAL Thickness = 0.250 - 1.000 in.

0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

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.

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse 160

Stress, ksi

120

80 Ramberg - Osgood n (RT) = 26 40

TYPICAL Thickness = 0.250 - 1.000 in.

0 0

4

8

12

16

20

24

Strain, 0.001 in./in. 3 Compressive Tangent Modulus, 10 ksi

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 at room and elevated temperatures.

5-82

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

5-83

MIL-HDBK-5H 1 December 1998

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

_____________________________ a

This equation should only be used in the same temperature ranges indicated in the nomograph. Creep strains computed outside these temperature ranges may yield unreasonable values.

5-84

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH

Figure 5.4.1.2.8(a). Best-fit S/N curves for unnotched solutiontreated 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, ksi 166-177

TYS, ksi 153-167

Temp., °F 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.

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:

[Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

References: 5.4.1.2.8(a) and (b) Supersedes page 5-85 of MIL-HDBK-5H

99

5-85

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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, ksi 166-177

TYS, ksi 153-167

Temp., °F 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)

REPRINTED WITHOUT CHANGE.

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 Standard Error of Estimate = 0.43 Standard Deviation in 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.]

5-86

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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 400°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, ksi 142-143 125-134

Specimen Details:

TYS, ksi 117-121 102-113

Temp.,
F 400
F 600
F

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.

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 Standard Error of Estimate = 0.58 Standard Deviation in 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.]

References: 5.4.1.2.8(a) and (b)

5-87

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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, ksi 142-143 129-133

TYS, ksi 117-121 103-105

Temp., °F 400°F 600°F

Test Parameters: Loading — Axial Frequency — 1500-2200 cpm Temperature — 400°F and 600°F Environment — Air No. of Heats/Lots: 3

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)

Equivalent Stress Equation: Log Nf = 10.64-3.77 log (Seq-20.9) Seq = Smax(1-R)0.51 Standard Error of Estimate = 0.42 Standard Deviation in 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.]

5-88

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH

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, ksi 120-125 110-111

TYS, ksi 93-96 84-86

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

Temp.,°F 800 °F 900 °F

No. of Heats/Lots: 3 Specimen Details: Unnotched 1.000-inch gross width 8.000-inch test section radius 3.00-inch gross width 0.9375-inch net width

Equivalent Stress Equation:

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)

Supersedes page 5-89 of MIL-HDBK-5H

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.]

5-89

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.4.1.2.8(f). Best-fit S/N curves for notched, K t = 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, ksi 120-124 110-111

TYS, ksi 93-96 84-88

Temp.,°F 800°F 900°F

Test Parameters: Loading — Axial Frequency — 1500-2200 cpm Temperature — 800°F and 900°F Environment — Air No. of Heats/Lots: 3

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)

REPRINTED WITHOUT CHANGE.

Equivalent Stress Equation: Log Nf = 11.75-4.45 log (Seq-15.0) Seq = Smax(1-R)0.62 Standard Error of Estimate = 0.43 Standard Deviation in 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.]

5-90

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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, ksi 158 155

TYS, ksi 149 145

Temp.,°F RT RT

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

Specimen Details: Unnotched, rounded

No. of Heats/Lots: 2

Uniform Gage Hourglass --3.25 Reduced section radius of curvature, inch 0.195 0.250 Diameter, inch

Equivalent Stress Equation:

Surface Condition: Longitudinally polished with No. 000 emery paper removing all circumferential marks. References: 5.4.1.2.8(c) and (d)

REPRINTED WITHOUT CHANGE.

Log Nf = 24.6-9.35 log (Seq) Seq = Smax(1-R)0.48 Standard Error of Estimate = 0.39 Standard Deviation in 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.]

5-91

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH

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) Test Parameters: Loading — Axial Frequency — Unspecified Temperature — RT Environment — Air

Product Form: Plate, 0.50-inch thick Properties: TUS, ksi 173

TYS, ksi 164

Temp., °F 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:

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%

Machined to 63 RMS

Reference: 5.4.1.2.8(d)

Sample Size: 14

Supersedes page 5-92 of MIL-HDBK-5H

5-92

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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) Test Parameters:

Product Form: Plate, 1.025 and 0.750-inch thick Properties: TUS, ksi 155 187

TYS, ksi 145 —

Temp.,°F RT (unnotched) RT (notched)

Loading — Axial Frequency — 1,800-18,000 cpm Temperature — RT Environment — Air No. of Heats/Lots: 2

Specimen Details: Circumferentially notched, Kt = 3.0

Equivalent Stress Equation:

Ref. (c) 0.195 0.136 0.005 60


Log Nf = 14.4-5.51 log (Seq) Seq = Smax(1-R)0.58 Standard Error of Estimate = 0.24 Standard Deviation of Life = 0.81 R2 = 92%

Ref. (e) 0.430 Gross diameter, inch 0.300 Net section, inch 0.016 Notch radius, r, inch 60
Flank angle,


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

Sample Size: 31 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

References: 5.4.1.2.8(c) and (e)

5-93

MIL-HDBK-5H 1 December 1998 5.4.2 Ti-6Al-6V-2Sn 5.4.2.0 Comments 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 stresscorrosion 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 solutiontreated 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. 5.4.2.1 Annealed 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). 5.4.2.2 Solution-Treated and Aged Condition — Elevated temperature curves are shown in Figures 5.4.2.2.1 and 5.4.2.2.2.

5-94

MIL-HDBK-5H, Change Notice 1 1 October 2001

Table 5.4.2.0(a). Material Specifications for Ti-6Al-6V-2Sn

Specification AMS-T-9046 AMS 4979 AMS-T-81556 AMS 4971 AMS 4978 AMS 4918

Supersedes page 5-95 of MIL-HDBK-5H

Form Sheet, strip, and plate Bar and forging Extruded bar and shapes Bar and forging Bar and forging Sheet, strip, and plate

5-95

I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.2.0(b). Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Sheet, Strip, and Plate

Specification . . . . . . . . . Form . . . . . . . . . . . . . . . Condition . . . . . . . . . . .

5-96

Thickness, in. . . . . . . . . Basis . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ............... LT . . . . . . . . . . . . . . Fty, ksi: L ............... LT . . . . . . . . . . . . . . Fcy, ksi: L ............... LT . . . . . . . . . . . . . . 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): L ............... LT . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . Ec, 103 ksi . . . . . . . . . G, 103 ksi . . . . . . . . . µ ................ Physical Properties:
, lb/in.3 . . . . . . . . . . C, K, and  . . . . . . . .

AMS-T-9046, Comp.AB-3 -T-9046, Comp. AB-3, and AMS 4918 Sheet, strip, and plate Annealed Solution treated and aged 0.18750.5011.0011.5012.0010.18751.5012.501
0.1875 1.500 <0.1875 0.500 1.000 1.500 2.000 4.000 2.500 4.000 A B S S S S S S S S S

160 150

150 150

150 150

150 150

150 150

145 145

170 170

170 170

160 160

150 150

145a 152 145a 154

140 140

140 140

140 140

140 140

135 135

160 160

160 160

150 150

140 140

155 155

... ... ...

... ... ...

139 151 91

142 147 93

146 141 95

148 136 95

... ... ...

... ... ...

170 170 101

... ... ...

... ... ...

... ...

... ...

236 294

241 303

247 312

250 317

... ...

... ...

264 324

... ...

... ...

... ...

... ...

193 215

196 223

199 234

202 240

... ...

... ...

237 266

... ...

... ...

10b 8b

... ...

10 8

10 8

10 8

10 8

8 6

8 6

8 8

6 6

6 6

16.0 16.4 6.2 0.31 0.164 See 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.

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.2.0(c). Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Bar

Specification . . . . . . . . . . . . . . . . . Form . . . . . . . . . . . . . . . . . . . . . . . . Condition . . . . . . . . . . . . . . . . . . . . Thickness or diameter, in. . . . . . . . Basis . . . . . . . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ........................ LTb . . . . . . . . . . . . . . . . . . . . . . STb . . . . . . . . . . . . . . . . . . . . . . . Fty, ksi: L ........................ LTb . . . . . . . . . . . . . . . . . . . . . . STb . . . . . . . . . . . . . . . . . . . . . . . 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): L ........................ LTb . . . . . . . . . . . . . . . . . . . . . . STb . . . . . . . . . . . . . . . . . . . . . . . RA, percent (S-basis): L ........................ LTb . . . . . . . . . . . . . . . . . . . . . . STb . . . . . . . . . . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . . . . . . µ ......................... Physical Properties:
, lb/in.3 . . . . . . . . . . . . . . . . . . . C, K, and  . . . . . . . . . . . . . . . . .

AMS 4978 Bar Air-cool annealeda 1.5013.001
1.500 3.000 4.000 A B A B A B

AMS 4971 and AMS 4979 Bar and forging Solution treated and aged
1.000 1.001- 2.001- 3.0012.000 3.000 4.000 S S S S

144 150 139 145 136 142 147 152 143 148 140 145 ... ... ... ... ... ...

175 175 ...

170 170 ...

155 155 155

150 150 150

131 138 126 132 123 129 136 141 131 136 127 132 ... ... ... ... ... ...

160 160 ...

155 155 ...

145 145 145

140 140 140

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

... ... ... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

... ...

10 8 ...

... ... ...

10 8 8

... ... ...

10 8 8

... ... ...

8 6 ...

8 6 ...

8 6 6

8 6 6

20 15 ...

... ... ...

20 15 15

... ... ...

15 15 15

... ... ... 16.0 16.4 6.2 0.31

20 15 ...

20 15 ...

20 15 15

20 15 15

0.164 See 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.

5-97

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.2.0(d). Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Forging

Specification . . . . . . . . . . . . . . .

AMS 4978

Form . . . . . . . . . . . . . . . . . . . . . .

Forging

Condition . . . . . . . . . . . . . . . . . .

Annealed

Thickness, or diameter, in. . . . . .

2.000

2.001-4.000

Basis . . . . . . . . . . . . . . . . . . . . . .

S

S

150 150 ...

145 145 145

140 140 ...

135 135 135

... ... ... ...

... ... ... ...

... ...

... ...

... ...

... ...

10 8 ...

10 8 7

20 15 15

20 15 15

Mechanical Properties: Ftu, ksi: L ....................... LTa . . . . . . . . . . . . . . . . . . . . . STa . . . . . . . . . . . . . . . . . . . . . Fty, ksi: L ....................... LTa . . . . . . . . . . . . . . . . . . . . . STa . . . . . . . . . . . . . . . . . . . . . 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: L ...................... LTa . . . . . . . . . . . . . . . . . . . . . STa . . . . . . . . . . . . . . . . . . . . . RA, percent: L ...................... LTa . . . . . . . . . . . . . . . . . . . . . STa . . . . . . . . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . . . .  .......................

16.0 16.4 6.2 0.31

Physical Properties:
, lb/in.3 . . . . . . . . . . . . . . . . . C, K, and  . . . . . . . . . . . . . . .

0.164 See Figure 5.4.2.0

a Applicable, providing LT or ST dimension is 2.500 inches.

5-98

MIL-HDBK-5H, Change Notice 1 1 October 2001 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.2.0(e). Design Mechanical and Physical Properties of Ti-6Al-6V-2Sn Extruded Bar and Shapes Specification . . . . . . . . . . .

AMS-T-81556, Comp. AB-3

Form . . . . . . . . . . . . . . . . . .

Extruded bar and shapes

Condition . . . . . . . . . . . . . .

Annealed

Thickness or diameter, in. . #2.000

Basis . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fty, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fcy, ksi: L ................... LT . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . Fbrua, ksi: (e/D=1.5) . . . . . . . . . . . . (e/D=2.0) . . . . . . . . . . . . Fbrya, ksi: (e/D=1.5) . . . . . . . . . . . . (e/D=2.0) . . . . . . . . . . . . e, percent (S-basis): L ................... LT . . . . . . . . . . . . . . . . . . RA, percent (S-basis): L ................... LT . . . . . . . . . . . . . . . . . .

Solution treated and aged

2.0013.000

3.0014.000

0.1880.500

0.5011.500

1.5012.500

2.5014.000

A

B

S

S

S

S

S

S

142 141

148 148

145 145

140 140

170 170

165 165

160 160

150 150

129 128

135 135

135 135

130 130

160 160

155 155

150 150

140 140

137 136 93

144 142 97

140 140 ...

135 135 ...

165 165 ...

160 160 ...

155 155 ...

145 145 ...

218 268

229 281

... ...

... ...

... ...

... ...

... ...

... ...

196 227

203 235

... ...

... ...

... ...

... ...

... ...

... ...

10 8

... ...

10 8

10 8

8 6

8 6

8 6

8 6

20 15

... ...

20 15

20 15

15 12

15 12

15 12

15 12

E, 103 ksi . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . µ ....................

16.0 16.4 6.2 0.31

Physical Properties: ω, lb/in.3 . . . . . . . . . . . . . . C, K, and α . . . . . . . . . . . .

0.164 See Figure 5.4.2.0

a Bearing values are “dry pin” values per Section 1.4.7.1.

Supersedes page 5-99 of MIL-HDBK-5H

5-99

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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

REPRINTED WITHOUT CHANGE.

5-100

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

5-101

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

5-102

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

5-103

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

5-104

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

5-105

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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.

5-106

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200

160

Longitudinal

Stress, ksi

120

80 Ramberg - Osgood n (L) = 26 TYPICAL 40

0 0

4

8

12

16

20

24

Strain, 0.001 in./in. 3 Compressive Tangent Modulus, 10 ksi

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.

VIEW INTERACTIVE GRAPH 200

160 Longitudinal

Stress, ksi

120

80

Ramberg - Osgood n (L) = 30 TYPICAL

40

0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

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

5-107

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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

5-108

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.4.2.1.8(a) Best-fit S/N curves for annealed Ti-6Al-6V-2Sn plate and die forging, K t = 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, ksi 154.5 159.9

TYS, ksi 148.5 151.5

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

Temp,
F RT RT

No. of Heats/Lot: 3 Specimen Details: Unnotched 0.195-inch diameter Unspecified diameter from forging

Equivalent Stress Equation: Log Nf = 20.90 - 8.10 log (Seq) Seq = Sa + 0.41 Sm

Surface Condition: RMS 32 Unspecified from forging

Standard deviation in log(Life) = 23.5 (1/Seq) Adjusted R2 = 89% Sample Size = 38

References: 5.4.1.2.8(c) and 5.4.2.1.8 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-109

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.4.2.1.8(b). Best-fit S/N curves for annealed Ti-6Al-6V-2Sn plate, K t = 3.0, longitudinal direction.

Correlative Information for Figure 5.4.2.1.8(b) Product Form:

Plate, 1.57-inch thick

Properties: TUS, ksi 154.6

TYS, ksi 148.5

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

Temp,
F 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

No. of Heats/Lot: 1 Equivalent Stress Equation: Log Nf = 8.31 - 2.73 log (Seq - 16.9) Seq = Sa + 0.37 Sm

Surface Condition: RMS 32

Standard deviation in log(Life) = 8.87 (1/Seq)

References: 5.4.1.2.8(c)

Adjusted R2 = 92% Sample Size = 32 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-110

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

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

VIEW INTERACTIVE GRAPH

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

REPRINTED WITHOUT CHANGE.

5-111

MIL-HDBK-5H, Change Notice 1 1 October 2001 5.4.3 TI-4.5AL-3V-2FE-2MO 5.4.3.0 Comments 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 1475EF. 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 1380F-1425EF 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 1/1000”. Diffusion bonding at 1425EF is possible but slightly higher temperatures than the superplastic forming temperature e.g., 1470EF 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 1/2 –1hour 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). Table 5.4.3.0(a). Material Specification for Ti-4.5Al-3V-2Fe-2Mo Titanium Alloy

Specification AMS 4899

Form Sheet, Strip, and Plate

5.4.3.1 Anneal 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.

New Page

5-111a

MIL-HDBK-5H, Change Notice 1 1 October 2001 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.4.3.0 (b). Design Mechanical and Physical Properties of Ti-4.5 Al-3V-2Fe-2Mo Titanium Alloy Sheet Specification

AMS 4899

Form . . . . . . . . . . . . . . . . . . . . . . . . .

Sheet

Condition . . . . . . . . . . . . . . . . . . . . . .

Annealed

Thickness, in. . . . . . . . . . . . . . . . . . .

0.025 to 0.063, exclusive

Basis . . . . . . . . . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ......................... LT . . . . . . . . . . . . . . . . . . . . . . . . Fty, ksi: L ......................... LT . . . . . . . . . . . . . . . . . . . . . . . . Fcy, ksi: L ......................... LT . . . . . . . . . . . . . . . . . . . . . . . . Fsu,b ksi . . . . . . . . . . . . . . . . . . . . . Fbru,c ksi: (e/D = 1.5) . . . . . . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . . . . . . Fbry,c ksi: (e/D = 1.5) . . . . . . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . . . . . . e, percent (S-basis): L ......................... LT . . . . . . . . . . . . . . . . . . . . . . . .

A

B

A

B

134a 134a

145 147

134a 134a

144 144

126a 126a

134 137

126a 126a

132 134

128a 131a 90a

136 143 99

... ... ...

... ... ...

196a 258a

215 283

... ...

... ...

157a 190a

171 207

... ...

... ...

8 8

... ...

10 10

... ...

E, 103 ksi . . . . . . . . . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . . . . . . . µ ..........................

16.0 16.2 ... ...

Physical Properties: ω, lb/in.3 . . . . . . . . . . . . . . . . . . . . C, Btu/(lb)(EF) . . . . . . . . . . . . . . . K, Btu/[(hr)(ft2)(EF)/ft] α, 10-6 in./in./EF . . . . . . . . . . . . . . .

0.164 0.12 4.00 5.17 (60-932 EF)

a Rounded T99 values are shown in Table 5.4.3.0(c). b Determined in accordance with ASTM B769. c Bearing values are “dry pin” values per Section 1.4.7.1.

New Page

0.063 to 0.187, exclusive

5-111b

MIL-HDBK-5H, Change Notice 1 1 October 2001

Table 5.4.3.0(c).Rounded T99 Values for Ti-4.5 Al-3V-2Fe-2Mo Titanium Alloy Sheet Thickness, in. . . . . . . . . . . . . . . . . . Mechanical Properties: F tu, ksi: L ........... LT . . . . . . . . . . F ty , ksi: L ........... LT . . . . . . . . . . F cy , ksi: L ........... LT . . . . . . . . . . F su, a ksi . . . . . . . . F bru, b ksi: (e/D = 1.5) . . . . (e/D = 2.0) . . . . F bry , b ksi: (e/D = 1.5) . . . . (e/D = 2.0) . . . .

0.025 to 0.063, exclusive

0.063 to 0.187, exclusive

........... ...........

140 140

141 140

........... ...........

129 131

128 127

........... ........... ...........

131 136 94

... ... ...

........... ...........

205 270

... ...

........... ...........

164 198

... ...

a Determined in accordance with ASTM B769. b Bearing values are “dry pin” values per Section 1.4.7.1.

New Page

5-111c

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH

160

Long Transverse

Longitudinal

Stress, ksi

120

80 Ramberg-Osgood Longitudinal Long Transverse

TYS (ksi)

41 36

141 145

40 TYPICAL Thickness: 0.031 - 0.059 in. 0 0

4

8

12

16

20

Strain, 0.001 in./in. 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.

VIEW INTERACTIVE GRAPH Long transverse Ramberg-Osgood Longitudinal

160

Stress, ksi

120

80

Ramberg-Osgood TYS (ksi) n (L) = 28 144 n (LT) = 33 156 40

TYPICAL Thickness: 0.031-0.059 in.

0 0

4

8

12

16

20

Strain, 0.001 in./in. Compressive Tangent Modulus, 103 ksi. 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. New Page

5-111d

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH 200 Long Transverse

Stress, ksi

160

120

Longitudinal

80

40

TYPICAL Thickness: 0.031 - 0.059 in.

0 0.00

0.05

Strain, in./in.

0.10

0.15

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

New Page

5-111e

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH . .

150 Ti-4.5Al-3V-2Fe-2Mo Kt=1.0 Stress Ratio 0.05 0.20 + 0.50 Runout →

+ +

Maximum Stress, ksi

++

140

+ +

+ +

+ → + →

++

130

+ → +

→ + → + →

120

→ → →

Note: Stresses are based on net section.

110 103

104

105

106

107

108

Fatigue Life, Cycles 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

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

Properties: TUS, ksi TYS, ksi Temp., EF 148 - 149 135 - 138 RT Specimen Details: Unnotched, 0.252-inch width

No. of Heats : 3 Surface Conditions: Lightly polished with 400 grit emery paper

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%

References: 5.4.3.1.8

Sample Size : 43 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.] New Page

5-111f

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH . .

110 Ti-4.5Al-3V-2Fe-2Mo Kt=2.8 Stress Ratio 0.05 0.20 + 0.50 Runout →

+

100

Maximum Stress, ksi

++

90 + +

80

+

+

+

+ + → + →

70 60

+ →

→ → →

50 40

→

Note: Stresses are based on net section.

30 103

104

→

105

106

107

108

Fatigue Life, Cycles Figure 5.4.3.1.8 (b) Best-fit S/N curves for notched, K t = 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

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

Properties: TUS, ksi TYS, ksi Temp., EF 148 - 149 135 - 138 RT Specimen Details: Notched, Kt=2.8 0.466-inch net width

No. of Heats : 3

Surface Conditions: HF/HNO3 pickled

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%

References: 5.4.3.1.8

Sample Size : 41 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.] New Page

5-111g

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH

Figure 5.4.3.1.9 Fatigue-crack-propagation data for 1-inch thick Ti-4.5Al-3V-2Fe-2Mo millannealed titanium alloy plate.

Specimen Thickness: Specimen Width: Specimen Type:

New Page

0.25 inch 2.0 inches C(T)

5-111h

Environment: Temperature: Orientation:

50% RH RT L-T

MIL-HDBK-5H 1 December 1998

5.5 BETA, NEAR-BETA, AND METASTABLE-BETA TITANIUM ALLOYS There is no clear-cut definition for beta titanium alloys. Conventional terminology usually refers to near-beta alloys and metastable-beta alloys as classes of beta titanium alloys. A near-beta alloy is generally one which has appreciably higher beta stabilizer content than a conventional alpha-beta alloy such as Ti-6Al4V, but is not quite sufficiently stabilized to readily retain an all-beta structure with an air cool of thin sections. For such alloys, a water quench even of thin sections is required. Due to the marginal stability of the beta phase in these alloys, they are primarily solution treated below the beta transus to produce primary alpha phase which in turn results in an enriched, more stable beta phase. This enriched beta phase is more suitable for aging. The Ti-10V-2Fe-3Al alloy is an example of a near-beta alloy. On the other hand, the metastable-beta alloys are even more heavily alloyed with beta stabilizers than near-beta alloys and, as such, readily retain an all-beta structure upon air cooling of thin sections. Due to the added stability of these alloys, it is not necessary to heat treat below the beta transus to enrich the beta phase. Therefore, these alloys do not normally contain primary alpha since they are usually solution treated above the beta transus. These alloys are termed “metastable” because the resultant beta phase is not truly stable—it can be aged to precipitate alpha for strengthening purposes. Alloys such as Ti-15-3, B120VCA, Beta C, and Beta III are considered metastable-beta alloys. Unfortunately, the classification of an alloy as either near-beta or metastable beta is not always obvious. In fact, the “metastable” terminology is not precise since a near-beta alloy is also metastable—i.e., it also decomposes to alpha plus beta upon aging. There is one obvious additional category of beta alloys—the stable beta alloys. These alloys are so heavily alloyed with beta stabilizers that the beta phase will not decompose to alpha plus beta upon subsequent aging. There are no such alloys currently being produced commercially. An example of such an alloy is Ti-30Mo. The interest in beta alloys stems from the fact that they contain a high volume fraction of beta phase which can be subsequently hardened by alpha precipitation. Thus, these alloys can generate quite highstrength levels (in excess of 200 ksi) with good ductilities. Also, such alloys are much more deep hardenable than alpha-beta alloys such as Ti-6Al-4V. Finally, many of the more heavily alloyed beta alloys exhibit excellent cold formability and as such offer attractive sheet metal forming characteristics. 5.5.1 Ti-13V-11Cr-3Al 5.5.1.0 Comments and Properties — Ti-13V-11Cr-3Al is a heat-treatable alloy possessing good workability and toughness in the annealed condition and high strength in the heat-treated condition. It is noted for its exceptional ability to harden in heavy sections (up to 6-inch diameter or greater) to tensile strength of 170 ksi Ftu. Manufacturing Considerations — This alloy possesses very good formability at room temperature; stretch forming is usually conducted at 500
F. Ti-13V-11Cr-3Al is readily fusion or spot welded. Arc-welded joints are very ductile in the as-welded condition, but have low strengths. Environmental Considerations — Ti-13V-11Cr-3Al is stable for times up to 1000 hours in the annealed condition at 550
F and in the solution treated and aged condition up to 600
F. Prolonged exposure above these temperatures may result in ductility losses. If welding is employed, the stability of the weld should be investigated under the particular exposure conditions to be encountered. While the material is not noted for good creep performance, Ti-13V-11Cr-3Al has exceptional short-time strength at temperatures to 1200
F and above. Oxidation resistance is satisfactory at such temperatures for short-time exposure and for long-time exposure at the lower elevated temperatures. Hot-salt stress corrosion has been shown to be possible in this REPRINTED WITHOUT CHANGE.

5-112

MIL-HDBK-5H 1 December 1998 alloy at temperatures as low as 500
F in highly stressed applications (e.g., rivet heads). It is generally thought that the material is moderately susceptible to aqueous chloride solution stress corrosion. Ti-13V-11Cr-3Al is not noted for good fracture toughness in the aged or high-strength condition and is not recommended in any condition for cryogenic temperature applications. 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. The specified fully heat-treated, or solution-treated and aged, condition is as follows: Solution treat at 1450
F for 15 to 60 minutes, air cool (water quench if material is over 2 inches thick). Age at 900
F for 2 to 60 hours, dependent on strength level. (Note: typical aging time to achieve Ftu = 170 ksi is 24 to 36 hours.) Specifications and Properties — Material specifications for Ti-13V-11Cr-3Al are shown in Table 5.5.1.0(a). Room-temperature mechanical and physical properties for Ti-13V-11Cr-3Al are shown in Table 5.5.1.0(b). The effect of temperature on physical properties is shown in Figure 5.5.1.0. Table 5.5.1.0(a) Material Specifications for Ti-13V-11Cr-3Al Specification

Form

MIL-T-9046

Sheet, strip, and plate

MIL-T-9047

Bar

5.5.1.1 Annealed Condition — Elevated temperature curves for annealed Ti-13V-11Cr-3Al are shown in Figures 5.5.1.1.1 through 5.5.1.1.4. Typical tensile stress-strain curves for annealed material at temperatures ranging from room temperature to 1000
F are shown in Figure 5.5.1.1.6. Unnotched and notched fatigue data at room and elevated temperatures for annealed sheet are shown in Figures 5.5.1.1.8(a) through (d). 5.5.1.2 Solution-Treated and Aged Condition — Elevated temperature curves for solutiontreated and aged Ti-13V-11Cr-3Al are shown in Figures 5.5.1.2.1 through 5.5.2.1.4. Typical tensile stressstrain curves at various temperatures are shown in Figure 5.5.1.2.6. Unnotched fatigue data at room and elevated temperatures for solution-treated and aged sheet are shown in Figures 5.5.1.2.8(a) through (c).

5-113

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.5.1.0(b). Design Mechanical and Physical Properties of Ti-13V-11Cr-3Al

Specification . . . . . . . . . . Form . . . . . . . . . . . . . . . . . Condition . . . . . . . . . . . . . Thickness or diameter, in. Basis . . . . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L ................. LT . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . Fty, ksi: L ................. LT . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . Fcy, ksi: L ................. LT . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . Fbru, ksi: (e/D = 1.5) . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . Fbry, ksi: (e/D = 1.5) . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . e, percent: L ................. LT . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . RA, percent: L ................. LT . . . . . . . . . . . . . . . . ST . . . . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . . . . Ec, 103 ksi . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . µ .................. Physical Properties:
, lb/in.3 . . . . . . . . . . . . C, K, and  . . . . . . . . . .

MIL-T-9046, Comp. B-1 Sheet, strip, and plate Solution treated Annealed and aged 0.012- 0.0500.049 4.000 <4.000 S S S

MIL-T-9047 Bar Solution treated Annealed and aged <7.000a S

<4.000a S

132 132 ...

125 125 125

170 170 170

125 125c 125c

170 170c 170c

126 126 ...

120 120 120

160 160 160

120 120c 120c

160 160c 160c

... ... ... ...

120 120 120 92

162 162 162 105

... ... ... ...

... ... ... ...

... ...

207 270

248 313

... ...

... ...

... ...

169 200

217 247

... ...

... ...

8 8 ...

10 10 10

4b 4b 4b

10 10c 10c

6 2c 2c

... ... ...

... ... ...

... ... ... 15.5 ... ... ...

25 25c 25c 14.5 ... ... ...

10 5c 5c 15.5 ... ... ...

14.5 ... ... ...

0.174 See Figure 5.5.1.0

a Maximum of 16 square-inch cross-sectional area. b Thickness 0.025 inch and above: 3 percent below 0.025 inch. c Applicable, providing LT or ST dimension is >3.000 inches.

5-114

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.0. Effect of temperature on the physical properties of Ti-13V-11Cr-3Al alloy.

5-115

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of annealed Ti-13V-11Cr-3Al alloy sheet.

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.2. Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of annealed Ti-13V-11Cr-3Al alloy sheet.

5-116

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.3(a). Effect of temperature on the bearing ultimate strength (Fbru) of annealed Ti-13V-11Cr-3Al alloy sheet.

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.3(b). Effect of temperature on the bearing yield strength (Fbry) of annealed Ti-13V-11Cr-3Al alloy sheet.

5-117

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.4. Effect of temperature on the tensile and compressive moduli (E and Ec) of annealed Ti-13V-11Cr-3Al alloy sheet.

VIEW INTERACTIVE GRAPH 150 Longitudinal and Long Transverse 125

RT 200 F 400 F 600 F 800 F

.5 -hr exposure

100

Stress, ksi

1000 F

75 Ramberg - Osgood n (RT) = 43 n (200 F) = 30 n (400 F) = 17 n (600 F) = 12 n (800 F) = 11 n (1000 F) = 10

50

TYPICAL

25

0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

Figure 5.5.1.1.6. Typical tensile stress-strain curves for annealed Ti-13V-11Cr-3Al alloy sheet at room and elevated temperatures.

5-118

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.8(a). Best-fit S/N curves for unnotched, annealed Ti-13V-11Cr-3Al alloy sheet, longitudinal direction.

Correlative Information for Figure 5.5.1.1.8(a) Product Form: Sheet, 0.043-inch thick Properties:

TUS, ksi TYS, ksi 138.50 132.80

Specimen Details:

Test Parameters: Loading—Axial Frequency—3600 cpm Temperature—RT Atmosphere—Air

Temp,
F RT

Unnotched, 0.30-inch wide No. of Heats/Lot: Not specified

Surface Condition: As machined, edges polished with emery paper. Reference:

Equivalent Stress Equation: Log Nf = 10.15-3.41 log (Seq-52.2) Seq = Smax (1-R)0.97 Standard Error of Estimate = 0.58 Standard Deviation in Life = 0.82 R2 = 50%

5.5.1.1.8

Sample Size = 27 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-119

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.8(b). Best-fit S/N curves for notched, Kt = 3.0, annealed Ti-13V-11Cr-3Al alloy sheet, longitudinal direction.

Correlative Information for Figure 5.5.1.1.8(b) Test Parameters: Loading—Axial Frequency—3600 cpm Temperature—RT Atmosphere—Air

Product Form: Sheet, 0.043-inch thick Properties: TUS, ksi 138.50

TYS, ksi 132.80

Temp,
F RT

Specimen Details: Notched, edge, K = 3.0 0.448-inch gross width 0.300-inch net width 0.022-inch root radius, r 60
flank angle,


No. of Heats/Lots: Not specified Equivalent Stress Equation: Log Nf = 21.93-11.03 log (Seq) Seq = Smax (1-R)0.53 Standard Error of Estimate = 0.91 Standard Deviation in Life = 1.11 R2 = 33%

Surface Condition: As machined, edges polished with emery paper. Reference: 5.5.1.1.8

Sample Size = 19 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-120

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.8(c). Best-fit S/N curves for unnotched, annealed Ti-13V-11Cr-3Al alloy sheet at 600°F, longitudinal direction.

Correlative Information for Figure 5.5.1.1.8(c) Product Form:

Sheet, 0.043-inch thick

Properties: TUS, ksi 116.00

TYS, ksi 102.61

Temp,
F 600
F

Test Parameters: Loading—Axial Frequency—3600 cpm Temperature—600
F Atmosphere—Air

Specimen Details: Unnotched, 0.300-inch wide No. of Heats/Lot: Not specified Surface Condition: As machined, edges polished with emery paper. Reference: 5.5.1.1.8

Equivalent Stress Equation: Log Nf = 35.63-16.50 log (Seq) Seq = Smax (1-R)0.34 Standard Error of Estimate = 0.35 Standard Deviation in Life = 1.07 R2 = 90% Sample Size = 12 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-121

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.1.8(d). Best-fit S/N curves for unnotched, annealed Ti-13V-11Cr-3Al alloy sheet at 800°F, longitudinal direction.

Correlative Information for Figure 5.5.1.1.8(d) Product Form: Properties:

Sheet, 0.043-inch thick

TUS, ksi TYS, ksi 115.80 98.61

Specimen Details:

Test Parameters: Loading—Axial Frequency—3600 cpm Temperature—800
F Atmosphere—Air

Temp,
F 800
F

Unnotched, 0.300-inch wide

No. of Heats/Lot: Not specified

Surface Condition: As machined, edges polished with emery paper. Reference:

Equivalent Stress Equation: Log Nf = 21.67-8.88 log (Seq) Seq = Smax (1-R)0.42 Standard Error of Estimate = 0.84 Standard Deviation in Life = 1.07 R2 = 39%

5.5.1.1.8

Sample Size = 26 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-122

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.2.1. Effect of temperature on the tensile ultimate strength (Ftu) and the tensile yield strength (Fty) of solution-treated and aged Ti-13V-11Cr-3Al alloy sheet.

VIEW INTERACTIVE GRAPH

Figure 5.5.1.2.2. Effect of temperature on the compressive yield strength (Fcy) and the shear ultimate strength (Fsu) of solution-treated and aged Ti-13V-11Cr-3Al alloy sheet.

5-123

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.2.3. Effect of temperature on the bearing ultimate strength (Fbru) and the bearing yield strength (Fbry) of solution-treated and aged Ti-13V-11Cr-3Al alloy sheet.

VIEW INTERACTIVE GRAPH

Figure 5.5.1.2.4. Effect of temperature on the tensile and compresssive moduli (E and Ec) of solution-treated and aged Ti-13V-11Cr-3Al alloy sheet.

5-124

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200 Longitudinal and Long Transverse

RT 200 F

.5 -hr exposure

160

400 F 600 F 800 F

Stress, ksi

120

1000 F 80 Ramberg - Osgood n (RT) = 23 n (200 F) = 17 n (400 F) = 16 n (600 F) = 15 n (800 F) = 11 n (1000 F) = 10

40

TYPICAL 0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

Figure 5.5.1.2.6. Typical tensile stress-strain curves for solution-treated and aged Ti-13V-11Cr-3Al alloy sheet at room and elevated temperatures.

5-125

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.2.8(a). Best-fit S/N curves for unnotched, solution-treated and aged Ti-13V-11Cr-3Al alloy sheet and plate, longitudinal direction.

Correlative Information for Figure 5.5.1.2.8(a) Test Parameters: Loading—Axial Frequency—3600 cpm, 10,000 cpm Temperature—RT Atmosphere—Air

Product Form: Sheet, 0.043-inch thick and plate, 1.00-inch thick Properties: TUS, ksi 174.5

TYS, ksi 156.7

Temp,
F RT

No. of Heats/Lot: Not specified

Specimen Details: Unnotched, 0.30-inch wide Unnotched, 0.20-inch wide

Equivalent Stress Equation: Surface Condition: As machined, edges polished with emery paper.

Log Nf = 8.37-2.30 log (Seq-20) Seq = Smax (1-R)0.27 Standard Error of Estimate = 0.093 Standard Deviation in Life = 0.31 R2 = 91%

As machined, edges were hand-polished. References: 5.5.1.1.8 and 5.5.1.2.8

Sample Size = 17 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-126

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.2.8(b). Best-fit S/N curves for unnotched, solution-treated and aged Ti-13V-11Cr-3Al alloy sheet at 600°F, longitudinal direction.

Correlative Information for Figure 5.5.1.2.8(b) Product Form: Sheet, 0.043-inch thick Properties: TUS, ksi 156.30 Specimen Details:

TYS, ksi 127.0

Test Parameters: Loading—Axial Frequency—3600 cpm Temperature—600
F Atmosphere—Air

Temp,
F 600
F

Unnotched, 0.310-inch wide

No. of Heats/Lots: Not specified

Surface Condition: As machined, edges polished with emery paper.

Equivalent Stress Equation: Log Nf = 10.39-4.33 log (Seq-48.5) Seq = Smax (1-R)0.40 Standard Error of Estimate = 0.90 Standard Deviation in Life = 1.27 R2 = 50%

Reference: 5.5.1.1.8

Sample Size = 21 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-127

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.1.2.8(c). Best-fit S/N curves for unnotched, solution-treated and aged Ti-13V-11Cr-3Al alloy sheet at 800°F, longitudinal direction.

Correlative Information for Figure 5.5.1.2.8(c) Product Form: Sheet, 0.043-inch thick Properties: TUS, ksi 149.40 Specimen Details:

TYS, ksi 122.30

Test Parameters: Loading—Axial Frequency—3600 cpm Temperature—800
F Atmosphere—Air

Temp,
F 800
F

Unnotched, 0.30-inch wide No. of Heats/Lots: Not specified

Surface Condition: As machined, edges polished with emery paper.

Equivalent Stress Equation:

Reference: 5.5.1.1.8

Log Nf = 30.03-14.03 log (Seq) Seq = Smax (1-R)0.11 Standard Error of Estimate = 0.85 Standard Deviation in Life = 1.01 R2 = 29% Sample Size = 24 [Caution: The equivalent stress model may provide unrealistic life predictions for stress ratios beyond those represented above.]

5-128

MIL-HDBK-5H 1 December 1998 5.5.2 Ti-15V-3Cr-3Sn-3Al (Ti-15-3) 5.5.2.0 Comments — Ti-15V-3Cr-3Sn-3Al is a solute rich (metastable) beta titanium alloy. It was developed primarily to lower the cost of titanium sheet metal parts by reducing materials and processing cost. Contrary to conventional alpha-beta alloys, this alloy is strip producible and has excellent room temperature formability characteristics. It can also be aged to a wide range of strength levels to meet a variety of application needs. Although this alloy was originally developed as a sheet alloy, it has expanded into other areas such as fasteners, foil, plate, tubing, castings, and forgings. Manufacturing Considerations — Ti-15V-3Cr-3Sn-3Al is usually supplied in the solution-annealed condition. In this condition, the alloy has a single phase (beta) structure and, hence, is readily cold formed. After cold forming, the alloy can be resolution-treated in the 1450
F to 1550
F range and subsequently aged in the 900
F to 1100
F range, depending upon desired strength. Care should be exercised to ensure that no surface contamination results from the solution treatment. The alloy can be directly aged after forming; however, strength will vary depending upon the amount of cold work in the part. The alloy can also be hot formed. Heating times prior to hot forming should be minimized in order to prevent appreciable aging prior to forming. Ti-15V-3Cr-3Sn-3Al alloy is readily welded by standard titanium welding techniques. Environmental Considerations — In the aged condition, Ti-15V-3Cr-3Sn-3Al appears to be immune to hot-salt stress corrosion cracking below the 500
F to 440
F range. However, some susceptibility has been noted after 100-hour stressed exposures at 600
F. The presence of salt water does not appear to affect the room temperature crack growth behavior of aged material. Alloy Ti-15V-3Cr-3Sn-3Al should not be used in the solution treated condition. Long time exposure of solution treated and cold worked material to service temperatures above approximately 300
F or solution treated material to service temperatures above approximately 400
F can result in low ductility. 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-STD1568 for restrictions concerning such applications. Heat Treatment — This alloy should be solution treated for 10-30 minutes in the 1450
F to 1550
F range, cooled at a rate approximating an air cool of 0.125 inch thick sheet and subsequently aged. Aging is generally conducted in the 900
F to 1100
F range, followed by an air cool. Aging times will vary depending upon aging temperature. The material can be used in service in the solution treated condition subject to the temperature limitations described above. Specifications and Properties — A material specification for Ti-15V-3Cr-3Sn-3Al is shown in Table 5.5.2.0(a). Room-temperature mechanical properties for Ti-15V-3Cr-3Sn-3Al are shown in Table 5.5.2.0(b). The effect of temperature on physical properties is shown in Figure 5.5.2.0. Table 5.5.3.0(a). Material Specification for Ti-15V-3Cr-3Sn-3Al

Specification

Form

AMS 4914

Sheet and strip

5.5.2.1 Solution Treated and Aged (1000°F) Condition — Typical tensile and compressive stress-strain and compressive tangent-modulus curves are presented in Figures 5.5.2.1.6(a) and (b).

5-129

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.5.2.0(b). Design Mechanical and Physical Properties of Ti-15V-3Cr-3Sn-3Al Sheet

Specification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AMS 4914

Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sheet

Condition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

STA (1000
F/8 Hrs.)

Thickness, in. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

0.125

Basis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

S

Mechanical Properties: Ftu, ksi: L ...................................... LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fty, ksi: L ...................................... LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fcy, ksi: L ...................................... LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fbrua, ksi: (e/D = 1.5) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fbrya, ksi: (e/D = 1.5) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (e/D = 2.0) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . e, percent: L ...................................... LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E, 103 ksi: L ...................................... LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ec, 103 ksi: L ...................................... LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . G, 103 ksi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . µ ....................................... Physical Properties:
, lb/in.3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C, K, and  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . a Bearing values are “dry pin” values per Section 1.4.7.1.

5-130

145 145 140 140 139 144 92 216 276 203 233 7 7 15.2 15.7 15.3 16.0 ... ... 0.172 See Figure 5.5.2.0

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH

Figure 5.5.2.0. Effect of temperature on the physical properties of Ti-15V-3Cr-3Sn-3Al alloy.

REPRINTED WITHOUT CHANGE.

5-131

MIL-HDBK-5H, Change Notice 1 1 October 2001

VIEW INTERACTIVE GRAPH 200

160

Longitudinal

Stress, ksi

Long transverse

120

80

Ramberg-Osgood n (L) = 21 n (LT) = 19 40

TYPICAL Thickness: 0.020-0.076 in. 0 0

4

8

12

16

20

24

Strain, 0.001 in./in.

Figure 5.5.2.1.6(a). Typical tensile stress-strain curves at room temperature for solution treated and aged (1000°F) Ti-15V-3Cr-3Sn-3Al alloy sheet.

VIEW INTERACTIVE GRAPH .

200

Long transverse Longitudinal 160

Stress, ksi

120

80

Ramberg-Osgood n (L) = 23 n (LT) = 21 40

TYPICAL Thickness: 0.020-0.076 in. 0 0

4

8

12

16

20

24

Strain, 0.001 in./in. Compressive Tangent Modulus, 103 ksi. Figure 5.5.2.1.6(b). Typical compressive stress-strain and compressive tangent-modulus curves at room temperature for solution treated and aged (1000°F) Ti-15V-3Cr-3Sn-3Al alloy sheet.

Supercedes page 5-132 of MIL-HDBK-5H

5-132

MIL-HDBK-5H 1 December 1998 5.5.3 Ti-10V-2Fe-3Al (Ti-10-2-3) 5.5.3.0 Comments and Properties — Ti-10V-2Fe-3Al is a solute lean beta (near beta) titanium alloy that was developed primarily as a high-strength forging alloy. It has excellent forging characteristics, possessing flow properties at 1500
F similar to Ti-6Al-4V at 1700
F. This characteristic provides advantages, such as lower die cost and better die fill capability. This alloy also provides the best combination of strength and toughness of any of the commercially available titanium alloys. For example, at the 180 ksi tensile ultimate strength level, the alloy has a KIc value of 40 ksi-in.½ minimum. In addition to this high-strength condition, the alloy can also be processed to intermediate strength levels for higher fracture toughness. This alloy has also been reported to exhibit a shape-memory effect. Manufacturing Considerations — Ti-10V-2Fe-3Al is usually supplied as bar or billet product which has been finish forged (or rolled) in the alpha-beta field. In order to optimize the microstructure for the highstrength condition, the forging is usually given a pre-form forge above the beta transus, followed by a 15 to 25 percent reduction below the beta transus. Ideally, the beta forging operation is finished through the beta transus, followed by a quench. The intent of the two-step forging process is to develop a structure without grain boundary alpha, but with elongated primary alpha needles in an aged beta matrix. The alloy is considered to be deep hardenable, capable of generating high strengths in section thicknesses up to approximately 5 inches. The alloy is also readily weldable by conventional titanium welding techniques. Environmental Consideration — In the solution treated plus aged condition, the material exhibits excellent resistance to stress corrosion cracking, typically exhibiting a K Iscc > 0.8 KIc. In the solution-treated condition, the material should not be subjected to long-term exposure in the 500 to 800
F range, since such exposure could result in high-strength, low-ductility conditions. Exposure to cadmium, silver, mercury, or certain other compounds should be avoided. Refer to MIL-STD-1568 and MIL-S-5002. Heat Treatment — For the high-strength condition, the alloy is generally solution treated approximately 65
F below the beta transus (which is typically 1460 to 1480
F), followed by a water quench and an 8-hour age at 900 to 950
F. Overaging in the 950
F to 1150
F range may also be used to obtain lower strength levels. Beta Flecks — Ti-10V-2Fe-3Al is a segregation prone alloy which can exhibit a microstructural phenomenon known as “beta-flecks”. Certain areas may possess a lower beta transus than the matrix (due primarily to beta stabilizer enrichment) and, as such, can fully transform during heat treatment just below the matrix transus. In severe cases, this condition can lead to lower ductility and a reduction in fatigue strength due to grain boundary alpha formation in the “flecked” region. Care should be exercised to procure only material which has been melted under strict control to prevent severe “fleck” formation. Specifications and Properties — Material specifications for Ti-10V-2Fe-3Al are shown in Table 5.5.3.0(a). Room temperature mechanical properties for Ti-10V-2Fe-3Al are presented in Table 5.5.3.0(b) and (c) for die and hand forging.. 5.5.3.1 Solution Treated and Aged (900 to 950°F) Condition — Typical tensile and compressive stress-strain and compressive tangent-modulus curves are presented in Figure 5.5.3.1.6.

5-133

MIL-HDBK-5H 1 December 1998 Table 5.5.3 Material Specifications for Ti-10V-2Fe-3Al Specification AMS 4983 AMS 4984 AMS 4986

Form Forging Forging Forging

5.5.3.2 Solution Treated and Aged (950 to 1000°F) Condition — Typical tensile and compressive stress-strain and compressive tangent-modulus curves are shown in Figure 5.5.3.2.6.

5-134

MIL-HDBK-5H, Change Notice 1 1 October 2001 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.5.3.0(b). Design Mechanical and Physical Properties of Ti-10V-2Fe-3Al Die Forging

Specification . . . . . . . Form . . . . . . . . . . . . . . Condition . . . . . . . . . . Thickness, in. . . . . . . . Basis . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L .............. LT . . . . . . . . . . . . . ST . . . . . . . . . . . . . Fty, ksi: L .............. LT . . . . . . . . . . . . . ST . . . . . . . . . . . . . Fcy, ksi: L .............. LT . . . . . . . . . . . . . ST . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . Fbrub, ksi: (e/D = 1.5) . . . . . . . (e/D = 2.0) . . . . . . . Fbryb, ksi: (e/D = 1.5) . . . . . . . (e/D = 2.0) . . . . . . . e, percent: L .............. LT . . . . . . . . . . . . . ST . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . Ec, 103 ksi . . . . . . . . G, 103 ksi . . . . . . . . . µ ............... Physical Properties: ω, lb/in.3 . . . . . . . . . a, 10-6 in./in./EF . . . . C and K . . . . . . . . . .

AMS 4983

AMS 4984

Conventional die forging Solution treated and aged (900-950EF) <1.000 <3.000 S S

180 180a ...

173 173a 173a

160 160a ...

160 160a 160a

168 166 ... 101

168 166 166 97

244 295

234 284

227 261

227 261

4 4a ...

4 4a 4a 15.9 16.3 ... ... 0.168 5.4 (68-800EF) ...

a Applicable providing LT or ST dimension is >2.500 inches. b Bearing values are “dry pin” values per Section 1.4.7.1.

Supersedes page 5-135 of MIL-HDBK-5H

5-135

MIL-HDBK-5H 1 December 1998 I n t er act i ve T ab l e - D e s ig n P rop er t i es

Interacti ve T ab le - T yp i c a l P r op ert i es

Table 5.5.3.0(c). Design Mechanical and Physical Properties of Ti-10V-2Fe-3Al Hand Forging

Specification . . . . . . . Form . . . . . . . . . . . . . . Condition . . . . . . . . . . Thickness, in. . . . . . . . Basis . . . . . . . . . . . . . . Mechanical Properties: Ftu, ksi: L .............. LT . . . . . . . . . . . . . Fty, ksi: L .............. LT . . . . . . . . . . . . . Fcy, ksi: L .............. LT . . . . . . . . . . . . . Fsu, ksi . . . . . . . . . . . Fbruc, ksi: (e/D = 1.5) . . . . . . . (e/D = 2.0) . . . . . . . Fbryc, ksi: (e/D = 1.5) . . . . . . . (e/D = 2.0) . . . . . . . e, percent: L .............. LT . . . . . . . . . . . . . RA, percent: L .............. LT . . . . . . . . . . . . . E, 103 ksi . . . . . . . . . Ec, 103 ksi . . . . . . . . G, 103 ksi . . . . . . . . . µ ............... Physical Properties:
, lb/in.3 . . . . . . . . . a, 10-6 in./in./
F . . . . C and K . . . . . . . . . .

AMS 4986 Hand forging Solution treated and aged (950-1000
F) <3.000 3.001-4.000 S S

160 160a

160 160

145 145a

145 145

154 ... 97b

... ... ...

241 293

... ...

218 245

... ...

6 6a

6 6

10 10a

10 10 15.9 16.3 ... ... 0.168 5.4 (68-800
F) ...

a Applicable providing LT dimension is >2.500 inches. b Shear strength determined in accordance with ASTM B 769. c Bearing values are “dry pin” per Section 1.4.7.1.

REPRINTED WITHOUT CHANGE.

5-136

MIL-HDBK-5H 1 December 1998

VIEW INTERACTIVE GRAPH 200

L, LT, and ST - compression L - tension LT - tension ST - tension

160

Stress, ksi

120

Ramberg - Osgood n ( L - tension) = 9.6 n (LT - tension) = 13 n (ST - tension) = 13 n ( L - comp.) = 18 n ( LT - comp.) = 15 n ( ST - comp.) = 18

80

40 TYPICAL Thickness = 3.100 - 3.300 in.

0 0

4

8

12

16

20

24

Strain, 0.001 in./in. 3 Compressive Tangent Modulus, 10 ksi

Figure 5.5.3.1.6. Typical tensile stress-strain, compressive stress-strain, and compressive tangent-modulus curves for solution treated and aged (900-950°F) Ti-10V-2Fe-3Al die forging.

VIEW INTERACTIVE GRAPH 200

L - compression LT - tension

160

L - tension

Stress, ksi

120

Ramberg - Osgood n ( L - tension) = 24 n (LT - tension) = 20 n ( L - comp.) = 21

80

TYPICAL 40

Thickness = 3.000 in.

0 0

4

8

12

16

20

24

Strain, 0.001 in./in. 3 Compressive Tangent Modulus, 10 ksi

Figure 5.5.3.2.6. Typical tensile stress-strain, compressive stress-strain, and compressive tangent-modulus curves for solution treated and aged (950-1000°F) Ti-10V-2Fe-3Al hand forging.

5-137

MIL-HDBK-5H 1 December 1998

5.6 ELEMENT PROPERTIES 5.6.1 BEAMS — See Equation 1.3.2.3, Section 1.5.2.5, and References 1.7.1(a) and (b) for general information on stress analysis of beams. 5.6.1.1 Simple Beams — Beams of solid, tubular, or similar cross sections can be assumed to fail through exceeding an allowable modulus of rupture in bending (Fb). In the absence of specific data, the ratio Fb/Ftu can be assumed to be 1.25 for solid sections. 5.6.1.1.1 Round Tubes — For round tubes, the value of Fb will depend on the D/t ratio as well as

the ultimate tensile stress. The bending modulus of rupture of 6Al-4V titanium alloy is given in Figure 5.6.1.1.1. Unconventional Cross Sections — Sections other than solid or tubular should be tested to determine the allowable bending stress. 5.6.1.1.2

VIEW INTERACTIVE GRAPH

Figure 5.6.1.1.1. Bending modulus of rupture for solution-treated and aged Ti-6Al-4V alloy round tubing manufactured from bar material.

5-138

MIL-HDBK-5H 1 December 1998

  5.1.2(a)

Jaffe, R. I., “The Physical Metallurgy of Titanium Alloys”, Progress in Metal Physics, Vol. 7, Pergammon Press, Oxford, England, pp 65-167 (1958).

5.1.2(b)

“Aircraft Designer's Handbook for Titanium and Titanium Alloys”, AFML-TR-67-142 (March 1967).

5.1.2(c)

Larson, F. R., “Anisotropy in Titanium Sheet in Uniaxial Tension”, ASM Transactions, 57, pp 620-631 (1964).

5.1.2(d)

Larson, F. R., “Textures in Titanium Sheet and Its Effects on Plastic Flow Properties”, Army Materials Research Agency, AMRA-TR-65-24 (October 1965).

5.1.4(a)

VanEcho, J. A., “Low Temperature Creep Characteristics of Ti-5A1-2.4Sn and Ti-6A1-4V Alloys”, DMIC Technical Note, Defense Metals Information Center, Battelle Memorial Institute, Columbus, Ohio (June 8, 1964).

5.1.4(b)

Broadwell, R. G., Hatch, A. J., Partridge, J. M., “The Room Temperature Creep and Fatigue Properties of Titanium Alloys”, Journal of Materials, 2, (1), pp 111-119 (March 1967).

5.1.4(c)

Reimann, W. H., “Room Temperature Creep in Ti-6A1-4V”, AFML-TR-68-171 (June 1968).

5.1.4(d)

White, E. L., and Ward, J. J., “Ignition of Metals in Oxygen”, DMIC Report 224, Defense Metals Information Center, Battelle Memorial Institute, Columbus, Ohio (February 1, 1966).

5.1.4(e)

Jackson, J. D., and Boyd, W. K., “Corrosion of Titanium”, DMIC Memorandum 218, Defense Metals Information Center, Battelle Memorial Institute, Columbus, Ohio (September 1, 1966).

5.1.4(f)

“Accelerated Crack Propagation of Titanium by Methanol, Halogenated Hydrocarbons, and Other Solutions”, DMIC Memorandum 228, Defense Metals Information Center, Battelle Memorial Institute, Columbus, Ohio (March 6, 1967).

5.1.4(g)

Lectures from AICE Materials Conference, “Titanium for the Chemical Engineer”, DMIC Memorandum 234, Defense Metals Information Center, Battelle Memorial Institute, Columbus, Ohio (April 1, 1968).

5.3.1.1.9

Wanhill, R. J. et al, “Fatigue Crack Propagation Data for Titanium Sheet Alloys”, Interim Report NLR-TR-72093U, National Aerospace Laboratory, The Netherlands (July 1972) (MCIC 88911).

5.3.2.2.8(a)

McCulloch, A. J., Melcon, M. A., and Young, L., “Fatigue Behavior of Sheet Materials for the Supersonic Transport, Volume 1—Summary and Analysis of Fatigue and Static Test Data”, Lockheed-California Company, AFML-TR-64-399, Volume 1, January 1965 (MCIC 62421).

5.3.2.2.8(b)

McCulloch, A. J., Melcon, M. A., and Young, L., “Fatigue Behavior of Sheet Materials for the Supersonic Transport: Volume 11—Static Test Data, S/N Test Data and S/N Diagrams”, Lockheed-California Company, AFML-TR-64-399, Volume II, January 1965 (MCIC 62422).

5-139

MIL-HDBK-5H, Change Notice 1 1 October 2001 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-TR67-189 (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).

5.4.1.1.9

Fedderson, 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).

5.4.2.1.8

Marrocco, 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).

5.4.3.1

Unpublished data from NKK, January 2001, (MIL-HDBK-5 Source M-914).

5.5.1

Henning, R. G., “Mechanical Properties of Solution-Treated Titanium Sheet Alloy B120VCA”, ASD TR 61-337 (September 1961).

5.5.1.1.8

Blatherwick, A. A., “Fatigue, Creep, and Stress-Rupture Properties of Ti-13V-11Cr-3Al Titanium Alloy (B120VCA)”, AFML-TR-66-293 (September 1966).

5.5.1.2.8

Schwartzberg, F. R., Kiefer, T. F., and Keys, R. D., “Determination of Low-Temperature Fatigue Properties of Structural Metal Alloys 1 April 1962 through 30 September 1964”, Martin-Cr-64-74 (October 1964), pp 158 (MCIC 58024).

5.6(a)

“Theoretical and Experimental Determination of the Bending Modulus of Rupture for Round Titanium Tubing”, Bendix Products Division (July 31, 1958).

5.6(b)

Cozzone, F. P., “Bending Strength in Plastic Range”, Journal of the Aeronautical Sciences (May 1943).

Supersedes page 5-140 of MIL-HDBK-5H

5-140

MIL-HDBK-5H, Change Notice 1 1 October 2001 5.6(c)

Ades, C. S., “Bending Strength of Tubing in the Plastic Range”, Journal of Aeronautical Sciences (August 1957).

5.6(d)

“Theoretical and Experimental Determination of the Bending Modulus of Rupture of Round Titanium Tubing”, Systems Engineering Report, Bendix Energy Controls Division, South Bend, Indiana, MS-58-3 (July 1958).

Supersedes page 5-141 of MIL-HDBK-5H

5-141

MIL-HDBK-5H, Change Notice 1 1 October 2001

SUBJECT INDEX Alpha and Near-Alpha Titanium Alloys Alpha-Beta Titanium Alloys Beams Beta, Near-Beta, and Metastable-Beta Titanium Alloys Commercially Pure Titanium Element Properties Environmental Considerations General Manufacturing Considerations Material Properties Ti-10V-2Fe-3Al (Ti-10-2-3) Ti-13V-11Cr-3Al Ti-15V-3Cr-3Sn-3Al (Ti-15-3) Ti-4.5Al-3V-2Fe-2Mo Ti-5Al-2.5Sn Ti-6Al-2Sn-4Zr-2Mo Ti-6Al-4V Ti-6Al-6V-2Sn Ti-8Al-1Mo-1V Titanium Titanium Index Unalloyed Titanium

5-15 5-51 5-138 5-112 5-5 5-138 5-2 5-1 5-2 5-1 5-133 5-112 5-129 5-111a 5-15 5-43 5-51 5-94 5-27 5-1 5-1 5-5

Knovel Sample Book From Works Published by: AIChE/Center for Chemical Process Safety Institute of Physics Knovel Corporation McGraw-Hill Plastics Design Library/William Andrew Publishing SciTech Publishing ChemTech Publishing

Norwich, New York 2003

Introduction Welcome to the Knovel Sample Book. This title is a useful Free learning and demonstration tool that contains a cross-section of information available in the following Subject Areas: • • • • • •

Aerospace & Radar Technology Chemistry & Chemical Engineering Mechanics & Mechanical Engineering Metals & Metallurgy Plastics & Rubbers Safety, Health & Hygiene

All of the information in this title is taken from copyrighted reference works currently available on Knovel. Knovel Sample Book illustrates the functionality of the site and the richness of its content, including interactive tables and graphs, and chemical, safety and mechanical properties.

Knovel Content The Knovel Sample Book is based on data from the following reference titles and Publishers: •

Knovel Critical Tables – Knovel Corporation

•

Knovel Solvents - A Properties Database – ChemTec Publishing

•

Lange's Handbook of Chemistry – McGraw-Hill

•

Marks' Standard Handbook for Mechanical Engineers – McGraw-Hill

•

Encyclopedia of Chemical Physics and Physical Chemistry, Volumes 1-3 – Institute of Physics

•

Guidelines for Chemical Process Quantitative Risk Analysis (2nd Edition) – American Institute of Chemical Engineers/Center for Chemical Process Safety

•

Effect of Creep and Other Time Related Factors on Plastics and Elastomers – Plastics Design Library/William Andrew Publishing

•

Military Handbook - MIL-HDBK-5H: Metallic Materials and Elements for Aerospace Vehicle Structures – Knovel Corporation

•

Introduction to Airborne Radar (2nd Edition) – SciTech Publishing

Knovel Productivity Tools Knovel integrates reference books and databases with productivity tools. On Knovel, users may browse and search by keywords or by fields. But the user experience does not stop with cross-site search and seamless navigation. Once the content is located, it may then be manipulated to obtain additional information using Knovel’s productivity tools. We have included examples for each Knovel productivity tool in this sample book. Each tool is fully functional and works right in the Web browser. Knovel’s productivity tools include: •

Interactive Tables – Allow you to find and customize data, as you would do when using spreadsheet applications, such as Microsoft Excel. Features include selecting rows, finding data, sorting, showing and hiding columns, changing column order, and filtering data.

•

Interactive Periodic Table of the Elements – Contains a wealth of data for all known elements, including atomic mass and number, electronic configuration, valencies, historical backgrounds, isotopic compositions and basic properties.

•

Unit Converter – Allows you to convert values from one unit of measurement to another. Contains approximately 800 different units.

•

Equation Plotter – Plots points on a graph curve and automatically displays the corresponding coordinates in an X-Y Table.

•

Excel Spreadsheets – Allow you to calculate various chemical process parameters.

•

Graph Plotter – Displays multiple curves (up to 12) on the same graph.

•

Graph Digitizer – Allows you to digitize one curve or multiple curves by plotting points on a graph, automatically displaying corresponding coordinates.

•

Knovel Reader™ – Designed for convenient viewing of HTML text. The text may be displayed as a continuous HTML file, or broken into pages if it is part (usually a chapter) of a book.

•

Downloadable ZIP files – Files that are compressed in the ZIP format for easy download of information. For the Knovel Sample Book, the ZIP file contains Excel spreadsheets.

As Knovel adds new features and new content, this sample book will expand. Please check back from time to time for new additions. We hope you agree that Knovel’s approach to integrating great science and engineering content with useful productivity tools will help cut your research time and improve your research results.