The Effects of Net-Shape Machining on the Performance of 

Al 2024-T3 Subjected to Axial Tension-Tension

Fatigue Loads

by Cyril Williams

ARL-TR-5277 August 2010

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Army Research Laboratory

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ARL-TR-5277 August 2010

The Effects of Net-Shape Machining on the Performance of 

Al 2024-T3 Subjected to Axial Tension-Tension

Fatigue Loads

Cyril Williams

Weapons and Materials Research Directorate, ARL

Approved for public release; distribution is unlimited.
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The Effects of Net-Shape Machining on the Performance of Al 2024-T3 Subjected 

to Axial Tension-Tension Fatigue Loads

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Cyril Williams

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14. ABSTRACT

Surface texture and process defects resulting from net-shape machining of engineering materials are often ignored in the design 

analysis of machined components parts. In this investigation, the effects of net-shape machining on the fatigue life of 2024-T6

aluminum were studied. Specimens were prepared using Abrasive Water Jet (AWJ) machining and the surface texture resulting 

from machining was characterized using contact profilometry. Based on the results from the surface texture evaluation and 

axial tension-tension fatigue tests performed, it was found that the fatigue life of 2024-T6 aluminum is surface texture 

dependent. As the roughness increases, the fatigue strength of the 2024-T6 aluminum decreases. It was found that the notch 

depth of the machined surface plays an important role in both low and high cycle fatigue. However, the mechanisms involved 

at low cycle fatigue are not well understood.

15. SUBJECT TERMS

axial, tension, fatigue, net-shape, machining, roughness, notch effects

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Contents

List of Figures iv

List of Tables v

1. Introduction 1

2. Background and Literature Survey 1

3. Methods and Materials 4

4. Results 7

5. Discussion 9

6. Conclusion 11

7. References 12

Distribution List 14
iv

List of Figures

Figure 1. A plot of surface factor versus surface roughness (Shigley and Mitchell, 1983)............2

Figure 2. Sawtooth and sinusoidal profile of a machined surface. .................................................3

Figure 3. Tension-tension fatigue test fixture.................................................................................4

Figure 4. Tensile fatigue specimen mounted in the MTS 810-load frame. ....................................4

Figure 5. Surface texture of AWJ machined metals (Arola, 1996). ...............................................5

Figure 6. Geometry and dimensions of Al 2024-T3 specimens. ....................................................5

Figure 7. Censored S-N plot for Al 2024-T3 aluminum with two different levels of surface 

quality. .......................................................................................................................................9
v

List of Tables

Table 1. Experimental surface quality level design matrix for Al 2024-T3. ..................................6

Table 2. AWJ cutting parameters used to achieve the 2 m and 6 m average roughness............6

Table 3. Experimental load level design matrix for fatigue testing of the Al 2024-T3..................6

Table 4. Surface roughness parameters and the profile valley radii for Al 2024-T3......................7

Table 5. Core surface roughness parameters for the Al 2024-T3...................................................7

Table 6. Calculated Weibull parameters for the Al 2024-T3 censored data...................................8
vi

INTENTIONALLY LEFT BLANK.
1

1. Introduction

Military equipment, such as tanks, attack helicopters, armored personnel carriers (APCs), etc.,

are often subjected to repeated or cyclic loads that can lead to the development of physical 

microscopic damage. With an increase in the number of load cycles, the microscopic damage 

can coalesce into a well-defined crack. Cyclic crack growth then continues until catastrophic 

failure. Fatigue failures can occur at cyclic stresses well below the material’s yield or ultimate 

strength. Due to changes in surface integrity and the presence of stress concentrations resulting 

from net-shape machining, fatigue damage usually develops on the surface of a component; 

consequently, surface topography has been found to have an appreciable effect on fatigue 

strength (Hanley and Dolan, 1953). Love (1952) has shown that the fatigue strength of a 

component increases as the surface roughness decreases and is also higher when the direction of 

polishing is parallel to the direction of applied stress.

Fatigue failures of conventional metals have been studied for more than 170 years and they 

account for the majority of mechanical failures in machine components (Dieter, 1991). It has 

been reported that the economic costs of fracture and its prevention are quite large, and it is 

estimated that 80% of these costs can be attributed to fatigue loading (Dowling, 1998). Due to 

the fatigue of materials, the annual cost to the U.S. economy is about 3% of the gross national 

product (GNP) and the same can be expected for other industrial nations (Dowling, 1998). In 

order to eliminate the economic costs associated with fracture and its prevention, the fatigue 

failure mechanisms in engineering materials must be thoroughly understood. 

2. Background and Literature Survey

The fatigue strength of metals has been studied by a number of investigators. Based on the 

extent of literature and diversity of topics, a full review of the work conducted in this area is far 

beyond the scope of this study. The following literature survey will focus on relevant work 

related to the initiation and propagation of damage, analytical treatments of surface topography 

and fatigue damage, and their effects on the strength of metals.

The mechanical performance of engineering components has been found to be dependent on the 

surface integrity resulting from net-shape manufacturing. Therefore, it is important to account 

for the effects of surface integrity when designing engineering components. The effects of 

surface integrity on metals resulting from conventional manufacturing processes have been 

discussed extensively in the literature (Zahavi and Torbilo, 1996; Field et al., 1970; Murakami 

and Endo, 1983, 1987; Fordham et al., 1997; Mitchell, 1977; Arola and Williams, 2002). The 
2

total fatigue life of engineering materials is comprised of the “initiation” life and “propagation” 

life. During fatigue loading, cracks most commonly initiate from surface defects that arise from 

manufacturing flaws. Hence, surface defects and/or a large surface roughness decrease the 

initiation component of fatigue life. Surface roughness, material properties, and the residual 

stress of the component surface layer are all important considerations in fatigue design.

The fatigue strength of metals is often considered in terms of the endurance limit or magnitude of 

applied cyclic stress below which the component exhibits infinite life. Shigley and Mischke 

(1989) have described the effects of surface integrity and other considerations on the endurance 

limit of metallic component using the relationship:

Se kakbkckdkekf Se

'

(1)

where Se is the corrected endurance limit, and S'e is the inherent endurance limit of the material 

under fully reversed cyclic loading. The endurance limit in equation 1 is modified by correction 

factors where ka is the surface factor, kb is the size factor, kc is the reliability factor, kd is the 

temperature factor, ke is the modifying factor for stress concentration, and kf is the miscellaneous 

effects factor. The surface factor ka is often represented in terms of the average roughness (Ra), 

peak-to-valley height roughness (Ry), or 10-point roughness (Rz) of the machined surface in 

question as shown in figure 1. These parameters are defined in terms of the profile height 

distribution (z) recorded over an assessment or traverse length (L) according to equations 2–4. 

0.01 0.1 1 10

0.5

1.0

0.9

0.8

0.7

A

B

C

E D

A = 400 Mpa

B = 500 Mpa

C = 700 Mpa

D = 900 Mpa

E = 1100 Mpa

Surface roughness, R (m) Surface factor, K a

a

Figure 1. A plot of surface factor versus surface roughness (Shigley and Mitchell, 1983).
3

 

L

a

z dx

L

R

0

1

(2) 

max min R z z y

  (3)













   

 

5

1

min

5

1

max ( ) ( )

5

1

j

j

i

z i R z z . (4)

Accordingly, the corrected endurance limit (Se) will decrease in a parabolic manner with increase 

in Ra (Shigley and Mitchell, 1983) according to equation 1. An increase in the ultimate strength 

of the component also reduces the endurance limit through ka due to the changes in critical flaw 

size. Reductions in fatigue life through surface finish are attributed to the magnitude of surface 

stress concentration imposed by peak-to-valley height fluctuations. Furthermore, the notch root 

radius of the machined surface is also of interest as it dictates the shape of the notch. However, 

the quantity Ra does not provide a distribution sensitive description of a surface. For example,

although the sawtooth and sinusoidal surface profiles for the machined surfaces shown in figure

2 have the same Ra, Ry, and Rz; however, the sawtooth profile would be much more detrimental 

to the fatigue life of a component by virtue of the notch root radius, i.e., as the notch root radius 

approaches infinity, the stress concentration factor tends to 1 or as the notch root radius 

approached zero, the stress concentration factor tends to infinity. Note that the surface factor for 

both surfaces in figure 2 would be the same according to figure 1 if based solely on Ra.

R , R , R | = R , R , R | a y z sawtooth a y z sinusoid

 a 

(a) (b)

Figure 2. Sawtooth and sinusoidal profile of a machined surface.

It is therefore necessary to distinguish which surface roughness parameters provide an adequate 

distinction of the effects of surface topography on the fatigue strength of engineering materials. 

With this knowledge, an evaluation of the effects from machined surface topography on the 

fatigue strength of metals becomes more formidable.
4

3. Methods and Materials

Fatigue testing of engineering materials is generally conducted using rotating bending fatigue 

machines because they are reliable, cheap, and require little attention. However, rotating 

bending fatigue machines are not ideal for studying the fatigue characteristics of plate and sheet 

materials due to the complexity of developing stress concentrations at the edges. Because plate 

and sheet materials are widely used in military and aerospace applications, an alternative method 

of fatigue testing was necessary to fulfill the objectives of this study. An axial tension-tension 

fatigue test was conducted to determine the effects of surface texture resulting from Abrasive 

Water Jet (AWJ) machining on the fatigue strength of Al 2024-T3. The fatigue testing was 

conducted in accordance with ASTM E466-82 (ASTM, 1982) using the standard dogbone 

specimen geometry. To use existing equipment for the fatigue study, it was necessary to design 

and fabricate a test fixture for the chosen specimen geometry as shown in figure 3. The 

assembly was mounted within the grips of the MTS 810-tension/torsion load frame as shown in 

figure 4.

Fixture Fixture

Specimen

Figure 3. Tension-tension fatigue test fixture.

Figure 4. Tensile fatigue specimen 

mounted in the MTS 810-

load frame.
5

Metallic materials machined using the AWJ exhibit three distinct macroscopic regions and they

are comprised of the initial damage region (IDR), the smooth cutting region (SCR), and the 

rough cutting region (RCR) as shown in figure 5 (Arola, 1996). The only difference in 

microscopic features resulting from material removal in the SCR and RCR is the increase in 

abrasive particle deflection, whereas material in the IDR exhibits considerable deformation due 

to the nearly normal repeated impact of abrasives on the jet periphery. Hence, it was necessary 

to minimize the IDR in machining the fatigue specimens and extend the SCR over the entire 

thickness of the metal.

Machined Surface

Direction of jet impingement

Traverse cutting direction

RCR

SCR

IDR

Figure 5. Surface texture of AWJ machined metals (Arola, 1996).

The Al 2024-T3 dogbone specimens were machined using an Omax Model 2652 abrasive 

waterjet unit. The dimensions for the metal specimens are shown in figure 6 and are in 

accordance with ASTM E466-82 (ASTM, 1982). 

1.500 2.000 1.500

1.000

0.500

R4.000 (4 Places) Ø0.190 (8 Places)

0.250

0.500

0.375

0.500

0.125

Figure 6. Geometry and dimensions of Al 2024-T3 specimens.
6

A design matrix for fatigue testing based on machined surface quality was developed for the 

Al 2024-T3 specimens as shown in table 1. 

Table 1. Experimental surface quality level design 

matrix for Al 2024-T3.

Quality Levels

Material Ra = 2 μm Ra = 6 μm

Al2024-T3 56 specimens 56 specimens

A total of 112 aluminum specimens were machined using the AWJ machining center. As listed 

in table 1, two surface qualities with average roughness of 2 m, and 6 m were investigated. 

All 112 specimens were first edge trimmed using the AWJ to achieve a 6-m average roughness 

and then 56 were carefully polished using no. 220 and no. 400 grit sandpaper respectively in the 

AWJ traverse direction to achieve a 2-m average roughness. The cutting parameters used to 

obtain the 2- and 6-m average roughness are listed in table 2. The jewel and mixing tube 

diameter used for all AWJ machining were 0.31 mm and 0.76 mm, respectively. The machined 

surface topography of each Al 2024-T3 specimen was evaluated using contact profilometry to 

enable a quantification of the surface texture and apparent notch geometry resulting from the 

material removal process.

Table 2. AWJ cutting parameters used to achieve the 2- and 6-m average roughness.

Average

Roughness

Pressure

(Mpa)

Travel Speed

(mm/s)

Standoff

(mm)

Grit Size

(Granet No.)

Abra. Flow Rate

(g/s)

2 μm 310 7.63 0.8 80 a0.8

6 μm 310 7.63 0.8 80 0.8

a

Polished to final finish using no. 220 and no. 400 grit sandpaper.

The machined specimens were subjected to constant amplitude tension-tension axial fatigue 

loads. Eight specimens were tested at seven load levels that span the expected stress-life fatigue

response; the fatigue load levels are listed in table 3.

Table 3. Experimental load level design matrix for fatigue testing of the Al 2024-T3.

Stress Amplitide (MPa), R = 0.1

Material Level 1 Level 2 Level 3 Level 4 Level 5 Level 6 Level 7

Al2024-T3 83 93 124 140 175 198 206
7

All fatigue tests were conducted in load control at a frequency of 12 Hz and a stress ratio 











 

max

min



 R

of 0.1. The load, displacement, and time were monitored during fatigue testing and 

recorded using Teststar II software, which is a commercially available data acquisition package 

for the MTS. Following failure of each specimen, the number of cycles to failure (N) was 

recorded and the fractured surface was inspected to determine the source of failure. 

4. Results

The effects of net-shape machining on the fatigue strength of Al 2024-T3 was studied using 

tension-tension axial fatigue loading. AWJ machining was used to produce fatigue specimens 

and the roughness parameters, surface profile, and notch root radii for Al 2024-T3 resulting from 

the specified cutting conditions were measured and recorded. The effective notch root radius

(

_



) was determined from the profile of each surface quality using the average radii of three 

prominent valleys as employed by Arola and Williams (2002) for other homogeneous metals. 

The effective notch root radii (

_



) determined for each level of surface quality are listed in table

4 with the conventional surface roughness parameters. Furthermore, the core roughness (Rk), the 

reduced peak height (Rpk), and valley depth (Rvk) as defined according to DIN 4776 for each 

surface quality were calculated and listed in table 5. It is worth noting that all roughness 

measurements for the Al 2024-T3 were made parallel to the traverse cutting direction along the

specimen gage section.

Table 4. Surface roughness parameters and the 

profile valley radii for Al 2024-T3.

Method Ra

(μm)

Ry

(μm)

Rz

(μm)



(μm)

AWJA 1.93 11.95 13.41 8.33

AWJB 6.09 32.71 32.99 7.29

Table 5. Core surface roughness parameters 

for the Al 2024-T3.

Method RK

(μm)

RVK

(μm)

RPK

(μm)

AWJA 5.23 5.81 1.70

AWJB 18.72 12.78 5.47
8

Weibull (1951) statistics were used to conduct a complete statistical analysis and description of 

the fatigue failure distribution of the AWJ machined specimens. A 2-parameter Weibull 

distribution (listed in equation 5) was used to determine the failure parameters for both surface 

qualities. The Weibull modulus or shape parameter () and characteristic life or scale parameter

() for each stress amplitude were determined from the experimental data and are listed in table 

6. Furthermore, F(t) is the cumulative distribution function (CDF) and t in the time to failure. 

  

 

( / )

( ) 1

t F t e . (5)

Table 6. Calculated Weibull parameters for the Al 2024-T3 censored data.

Stress Amplitude 2 μm (AWJA) 6 μm (AWJC)

(MPa) α β α β

83 1227390 4 955892 3

93 487429 3 343967 19

124 85385 12 76450 9

140 60779 6 73325 5

175 14318 9 10485 10

198 6910 32 4506 11

206 5148 6 2904 5

From the Weibull parameters listed in table 6, the characteristic life or scale parameter (α) is 

consistently increasing with decrease in stress amplitude as expected, but the Weibull modulus or 

shape parameter (β) show no apparent trend. Therefore, no conclusive information was obtained 

using Weibull statistics. However, a 95% confidence interval was used in conjunction with 

Weibull statistics to remove all outliers and develop a censored fatigue response for the 

Al 2024-T3 aluminum. The censored fatigue-life diagram for the two surface textures is shown 

in figure 7. 

It is apparent from figure 7 that the fatigue strength of 2024-T3 aluminum increases with 

decreased surface roughness throughout the fatigue-life response. However, at low cycle fatigue 

(LCF) the increase was more prominent when compared to that at high cycle fatigue (HCF). In 

general, the fatigue strength of a notched specimen is lower than that of an unnotched specimen, 

especially at HCF and this is attributed to the stress concentration developed at the notch tip. 

The fatigue response within the HCF regime appears to be contradictory because the fatigue 

strength of the surface with 2-m average roughness even though higher, approaches that of the 

6-m average roughness. 
9

Figure 7. Censored S-N plot for Al 2024-T3 aluminum with two different levels of surface quality.

5. Discussion

The surface texture and surface integrity resulting from net-shape machining have been proven 

to be important considerations in mechanical design (Zahavi and Torbilo, 1996). The strength 

and/or service life of an engineering component is not only dependent on the material’s intrinsic 

mechanical properties, but also on certain aspects of the machined surface such as surface 

texture. 

In general, there is a gradual decrease in notch sensitivity with increasing alternating stress 

amplitude due to the increasing influence of plastic deformation (Frost and Dugdale, 1957). 

However, the contrast of the aforementioned statement is observed in the fatigue response 

diagram shown in figure 8. That is, there is an increase in notch sensitivity with increase in 

stress amplitude. Because the stresses are relatively low at HCF when compared to those at LCF

and fatigue crack growth is usually the dominant failure mode. The Al 2024-T3 aluminum

should become more sensitive to notches (i.e., increase in notch sensitivity) and therefore, the 

fatigue strength of the surface with 2-m average roughness should deviate from that of the 

5 0

10 0

15 0

20 0

25 0

10 00 1 041 051 061 07

6μm 

2μm 

Stress Amplitude (MPa)

No. of Cycles
10

6-m average roughness. Because the AWJ cutting parameters for both surfaces are identical

(see table 2), this implies that the difference in the notch root radii for both profiles would be 

identical and this can be observed in table 4. The characteristic difference between the two 

surface profiles is their notch depth. For the surface with the 2-m average roughness, the notch 

depth was observed to be less than that of the 6 m due to polishing. Because the elastic stress 

concentration is dependent not only on the notch root radius but also on the notch depth, the 

surface with the 6 m exhibited higher stress concentration and hence a lower fatigue strength. 

This is clearly evident when considering elastic stress concentration models such as the Peterson 

(1974), Arola-Ramulu (1998), and Neuber (1958) models. From the Peterson model listed in 

equation 6, it is apparent that the elastic stress concentration is dependent on both the notch 

depth and profile valley radius. For the same notch root radius, the elastic stress concentration 

will decrease with a reduction in notch depth. Similarly, for the Neuber and Arola-Ramulu 

models listed in equations 7 and 8, respectively, the elastic stress concentration decreases with 

decrease in the standard roughness parameters. A decrease in notch depth usually results in a 

decrease in standard roughness parameters because they are directly dependent on both peaks 

and valleys.



t

Kt 1 2

(6)

where t is the notch depth and  is the profile valley notch root radius.





Z

t

R

K  1 n

(7)

where n represent the stress state,  is the spacing factor, Rz is the ten-point roughness and  is 

the notch root radius.





































 

Z

a y

R

R R

n

t

K _

_

1



(8)

where n is an empirical constant, Ra, Ry, Rz, and  are the average roughness, peak to valley 

height, ten-point roughness and effective notch root radius respectively.

Although both surfaces have similar notch root radius, the surface with 2-m roughness 

exhibited superior fatigue strength because of its lower notch depth. The difference in the 

fatigue strength for both surfaces at LCF is large when compared to that at HCF. This behavior 

is not well understood and it is contrary to what is expected for homogeneous materials (Arola 

and Williams, 2002). Using AISI 4130 CR steel Arola and Williams, 2002 were able to show 

that during cyclic loading the material continues to deform plastically in every cycle if the stress

at the notch is to remain reduced. Therefore, the plastic strains that are induced during the cyclic 
11

process can cause the stress amplitude to be less than the actual stress (Kt) due to stress 

concentration at the notch, where Kt is the elastic stress concentration and  is the nominal stress. 

Consequently, the redistribution of near-notch stress causes the fatigue life to be longer than 

expected. This redistribution of near-notch stress typically occurs at high stress amplitudes 

(corresponding to short fatigue lives) and is sometimes referred to as reversed yielding. 

6. Conclusion

Based on the results from the surface texture evaluation and axial tension-tension fatigue tests 

performed with Al 2024-T3 it can be concluded that the axial tension-tension fatigue response of 

Al 2024-T3 is surface texture dependent. As the surface roughness of the machined surface 

increases, the fatigue strength of the Al 2024-T3 aluminum decreases. It was found that the 

notch depth of the surface texture plays an important role in both LCF and HCF. However, the 

mechanisms involved at LCF (plasticity dominated regime) are not well understood at this point

and more research is required to resolve the unanswered questions.
12

7. References

Arola, D. The Influence of Net-Shape Machining on the Surface Integrity of Metals and Fiber 

Reinforced Plastics, Ph.D. Dissertation: University of Washington, 1996.

Arola, D.; Williams, C. L. Estimating the Fatigue Stress Concentration Factor of Machined 

Surfaces. International Journal of Fatigue 2002, 24, pp. 923–930.

Arola, D.; Ramulu, M., Net-Shape Manufacturing and the Process-Dependent Failure of FiberReinforced Plastics Under Static Loads, Journal of Composites Technology and Research, 

JCTRER, Vol. 20, October 1998b, pp. 210–220.

Standard practice for conducting constant amplitude axial fatigue tests of metallic materials, 

ASTM E466-82. American Society for Testing and Materials, Philadelphia, 1982.

Dowling, N. E. Mechanical Behavior of Materials: Engineering Methods for Deformation, 

Fracture, and Fatigue, Prentice Hall, 1999.

Field, M. Machining of High Strength Steels with Emphasis on Surface Integrity, Air Force 

Machinability Data Center, Metcut Research Assoc., 1970, pp. 1–229.

Fordham, J. D.; Pilkington, R.; Tang, C. C. The Effect of Different Profiling Techniques on the 

Fatigue Performance of Metallic Membranes of AISI 301 and Inconel 718. International 

Journal of Fatigue 1997, 19 (6) pp. 487–501.

Hanley, B. C.; Dolan, T. J. Surface Finish. ASME: Metals Engineering-Design, 1953, p. 100.

Juvinall, R. C.; Marshek, K. M. Fundamentals of Machine Component Design, John Wiley and

Sons, 1991.

Love, R. J. The Influence of Surface Condition on the Fatigue Strength of Steel. Symposium 

Properties of Metallic Surface, Institute of Metals, 1952, p. 161.

Mitchell, M. R. Review of the Mechanical Properties of Cast Steels With Emphasis on Fatigue 

Behavior and the Influence of Microdiscontinuities. Journal of Engineering Materials and 

Technology October 1977, pp. 329–343.
13

Murakami, Y.; Endo, M. Effects of an Artificial Small Defect on Torsional Fatigue Strength of 

Steels. Journal of Engineering Materials and Technology 1987, 109, pp. 124–129.

Murakami, Y.; Endo, M. Quantitative Evaluation of Fatigue Strength of Metals Containing 

Various Small Defects or Cracks. Engineering Fracture Mechanics 1983, 17 (1), pp. 1–15.

Neuber, H. Kerbspannungsleshre. Springer-Verlag 1958, pp. 159–163.

Peterson, R. E. Stress Concentration Factors, John Wiley and Sons, 1974.

Shigley, J. E.; Mischke, C. R. Mechanical Engineering Design. McGraw-Hill, 5th Edition, 

1989.

Shigley, J. E.; Mischke, C. R. Mechanical Engineering Design. McGraw-Hill, 4th Edition, 

1983.

Weibull, W. Journal of Applied Mechanics 1951, 18, pp. 293–297.

Zahavi, E.; Torbilo, V. Fatigue Design: Life Expectancy of Machine Parts, 1st Edition, CRC 

Press, 1996, p. 193.
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15

1 DPTY ASSIST SCT FOR R&T

(CD SARD TT

only) ASA (ACT)

J PARMENTOLA

THE PENTAGON RM 3E479

WASHINGTON DC 20310-1714

1 PRIN DPTY FOR TCHNLGY HQ

US ARMY MATCOM

AMCDCGR

R PRICE

9301 CHAPEK RD

FT BELVOIR VA 22060-5527

3 AIR FORCE ARMAMENT LAB

AFATL DLJW

W COOK

D BELK

J FOSTER

EGLIN AFB FL 32542

2 NSF

S MCKNIGHT

G PAULINO

4201 WILSON BLVD, STE 545 

ARLINGTON VA 22230-0002

2 DARPA

W COBLENZ

3701 N FAIRFAX DR

ARLINGTON VA 22203-1714

1 DIRECTOR 

US ARMY ARDEC

AMSRD AAR AEE W

E BAKER

BLDG 3022

PICATINNY ARSENAL NJ

07806-5000

2 US ARMY TARDEC

AMSTRA TR R MS 263

K BISHNOI

D TEMPLETON MS 263

WARREN MI 48397-5000

1 COMMANDER

US ARMY RSRCH OFC

RDRL ROE N

B LAMATTINA

PO BOX 12211

RESEARCH TRIANGLE PARK NC

27709-2211

1 COMMANDER

US ARMY RSRCH OFC

RDRL ROI M

J LAVERY

PO BOX 12211

RESEARCH TRIANGLE PARK NC

27709-2211

1 COMMANDER

US ARMY RSRCH OFC

RDRL ROE M

D STEPP

PO BOX 12211

RESEARCH TRIANGLE PARK NC

27709-2211

5 NAVAL RESEARCH LAB

E R FRANCHI CODE 7100

M H ORR CODE 7120

J A BUCARO CODE 7130

J S PERKINS CODE 7140

S A CHIN BING CODE 7180

4555 OVERLOOK AVE SW

WASHINGTON DC 20375

1 DTRA

M GILTRUD

8725 JOHN J KINGMAN RD

FORT BELVOIR VA 22060

1 ERDC

US ARMY CORPS OF ENGINEERS

USACEGSL

P PAPADOS

7701 TELEGRAPH RD

ALEXANDRIA VA 22315

1 AFOSR NL

875 NORTH RANDOLPH ST

SUITE 325 RM 3112

F FAHROO

ARLINGTON VA 22203

5 SOUTHWEST RSRCH INST

C ANDERSON

K DANNEMANN

T HOLMQUIST

G JOHNSON

J WALKER

PO DRAWER 28510

SAN ANTONIO TX 78284
NO. OF

COPIES ORGANIZATION

16

1 COMPUTATIONAL MECH

CONSULTANTS

J A ZUKAS

PO BOX 11314

BALTIMORE MD 21239-0314

1 APPLIED RSCH ASSOCIATES

D E GRADY

4300 SAN MATEO BLVD NE

STE A220

ALBUQUERQUE NM 87110

1 INTERNATIONAL RSRCH

ASSOC INC

D L ORPHAL

4450 BLACK AVE

PLEASANTON CA 94566

3 ORNL

ENVIRONMENTAL SCI DIV

W DOLL

T GAMEY

L BEARD

PO BOX 2008

OAK RIDGE TN 37831

1 NATIONAL INST OF

STANDARDS & TECHLGY

BLDG & FIRE RSRCH LAB

J MAIN

100 BUREAU DR MS 8611

GAITHERSBURG MD 20899-8611

3 DIR USARL

RDRL D

V WEISS

RDRL SE

J PELLEGRINO

RDRL SES P

A EDELSTEIN

2800 POWDER MILL RD

ADELPHI MD 20783-1197

ABERDEEN PROVING GROUND

103 DIR USARL

RDRL WM

B FORCH

S KARNA

J MCCAULEY

P PLOSTINS

J SMITH

RDRL WML

J NEWILL

M ZOLTOSKI

RDRL WML B

I BATYREV

B RICE

N WEINGARTEN

RDRL WML D

P CONROY

M NUSCA

RDRL WML G

M BERMAN

W DRYSDALE

RDRL WML H

T FARRAND

R SUMMERS

M FERMEN-COKER

L MAGNESS

B SORENSON

E KENNEDY

T EHLERS

C MEYER

D SCHEFFLER

S SCHRAML

B SCHUSTER

RDRL WMM

R DOWDING

J ZABINSKI

RDRL WMM A

M MAHER

J TZENG

E WETZEL

RDRL WMM B

T BOGETTI

B CHEESEMAN

C FOUNTZOULAS

D HOPKINS

B POWERS

C RANDOW

M VANLANDINGHAM

R WILDMAN

C F YEN

RDRL WMM D

E CHIN

K CHO

R HOWELL

RDRL WMM E

M COLE

T JESSEN

J LASALVIA

J SANDS

RDRL WMM F

L KECSKES

S MATHAUDHU

RDRL WML G

J ANDZELM

A RAWLETT
NO. OF

COPIES ORGANIZATION

17

RDRL WMP

P BAKER

S SCHOENFELD

RDRL WMP B

R BECKER

S BILYK

D CASEM

J CLAYTON

M GREENFIELD

C HOPPEL

R KRAFT

B LEAVY

B LOVE

M SCHEIDLER

T WEERASOOYIA

C WILLIAMS (10 CPS)

RDRL WMP C

T BJERKE

S SEGLETES

G BOYCE

R MUDD

T DIGLIANI

N BRUCHEY

W WALTERS

RDRL WMP D

R DONEY

J RUNYEON

B SCOTT

D KLEPONIS

K STOFFEL

RDRL WMP E

M BURKINS

W GOOCH

T JONES

M LOVE

RDRL WMP F

R BITTING

M CHOWDHURY

E FIORAVANTE

A FRYDMAN

N GNIAZDOWSKI

R GUPTA

RDRL WMP G

N ELDREGE

R EHLERS

W BUKOWSKI

B KRZEWINSKI

S KUKUCK

R BANTON

D KOOKER

G PEHRSON 
18

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