NASA Technical Memorandum 101645 

AVSCOM Technical Memorandum 89-B-007 

I. 

. 

Five Year Ground Exposure of Composite Materials Used on The Bell Model 206L 

Flight Service Evaluation 

Donald J. Baker 

July 1989 

- __ - ~~ 

~ 

- (NASA-TM-101645) FIVE YEAR GROUND EXPOSURE N89-28579 Of COMPOSITE MATERXALS USED ON THE BELL 

MOOEL LO6C FLTGYT SERVICE EVAtU4TIQN 

9 

L (NASA. 

langley Research Center) 93 p CSCL 110 Uncl dS 

63/24 0231755 

Nallonal Aeronautics and 

Space Administration 

Langley Research Center 

Hamptor! Virginia 23665 

US ARMY 

AVIATION 

SYSTEMS COMMCdD 

AVIATION RLT ACTNm 
FIVE YEAR GROUND EXPOSURE OF COMPOSITE 

MATERIAIS USED ON THE BELL MODEL 206L 

FLIGHT SERVICE EVALUATION 

. 

Donald J. Baker 

Aerostructures Directorate 

Langley Research Center 

Hampton.VA.23665-5225 

U.S. Army Aviation Research and Technology Activity(AVSC0M) 

Introduction 

During the past ten years, NASA has sponsored programs to build a data 

base and establish confidence in the long-term durability of advanced 

composite materials(reference 1). Flight service experience is being 

obtained on primary and secondary structural components installed on 

commercial aircraft and from material specimens exposed at different 

locations. 

environment the behavior of composite materials on each vehicle may differ 

substantially. Most of the projected usage for composites in helicopter 

fuselage is Kevlar-49@/epoxy with selective reinforcement of 

graphite/epoxy using 250°F curing epoxies. Most commercial aircraft are 

using 350°F cure graphite/epoxy systems with very little use of 

Kevlar/epoxy. Considering only the effects of moisture, materials in the 

minimum gage structure in most helicopter fuselage would reach equilibrium 

moisture content in a short time whereas the heavier gage structure on a 

commercial aircraft could take months to reach an equilibrium condition. 

activity initiated the first major program to evaluate composite helicopter 

components in flight service. 

components per aircraft. There are three secondary structural components 

fabricated from Kevlar-49/epoxy and one primary structural structural 

component fabricated from graphite/epoxy per aircraft. 

flight program, specimens from materials used to fabricate the components 

are being exposed in outdoor ground racks and are being returned for testing 

at prescribed intervals. 

Although commercial aircraft and helicopters may fly in the same 

Therefore, in 1978, NASA and the U.S. Army Research and Technology 

The flight service program includes four 

Concurrent with the 

This paper describes the results of tests on specimens that have been 

exposed for the first five years of a planned ten year ground exposure 

program 

Use of commercial products or names of manufactures in this report does 

not constitute official endorsement of such products or manufactures, either 

expressed or implied, by the National Aeronaut-ics and Space Administration 

or the U.S. Army Research and Technology Activity. 

@ Registered trademark of Dupont Corp. 
Exposure Specimens 

Composite material systems are being exposed on the North American 

Continent in areas that have varying environmental conditions. The 

composite systems are: 1.) Kevlar-49 fabric(sty1e 281) /F-185 epoxy, 2.) 

Kevlar-49 fabric(sty1e 120) /LRF-277 epoxy , 3.) Kevlar-49 fabric (style 

281) /CE-306 epoxy , and 4.) T-300 Graphite tape/ E-788 epoxy . The F-185 

epoxy 

resin. The CE-306 is cured at 200°F for five hours. The E-788 is a 350°F 

cure epoxy. Style 281 Kevlar-49 fabric is a plain weave with 17 ends/inch 

of 1140 denier yarn in each direction and has a weight of 5.0 ounces per 

square yard. Style 120 fabric is a plain weave with 34 ends/inch of 195 

denier yarn in each direction and has a weight of 1.8 ounces per square 

yard. The material suppliers, specimen nominal thicknesses, and fiber 

lay-up patterns are given in Table I. 

locations on the North American Continent as shown in figure 2. 

at Toronto, Canada and Hampton, VA are installed on the roofs of buildings. 

Racks at Cameron, LA and Ft. Greely, AK are installed on stands 

approximately 18 inches above the ground. The remaining rack is on a 

working oil platform in the Gulf of Mexico. 

1980 and contain five panels each for removal after 1, 3, 5, 7, and 10 years 

of exposure. A panel contains 24 each of tension, short-beam-shear (SBS), 

IITRI compression specimens and four 2.0 inch wide specimens to observe the 

weathering characteristics of each material system. The specimen design is 

shown in figure 3 and is also given in reference 2. The tension, 

compression and SBS specimens are painted with a polyurethane 

paint(1MIRON') that is used on the flight service helicopters. The 

remaining specimens were left unpainted to determine the weathering effect 

on bare composites. 

is a 250°F cure system. The LRF-277 is a 250°F cure proprietary 

The materials are exposed outdoors in racks (figure 1) at five 

The racks 

The racks were installed in 

The specimens used for moisture determination were cut from the tested 

tension specimens. A 0.5 inch long section was cut from the undamaged area 

of the tension specimens as soon as possible after completion of testing. 

The paint was removed by sanding, using caution not to remove an excessive 

amount of the outer ply. 

A 0.5 inch long specimen was also removed from the unpainted 

specimen and weighed prior to being used for moisture determination. 

specimens were stored in sealed plastic bags between different operations. 

Each specimen was weighed after the paint removal. 

exposure 

All 

Test Methods 

Each panel was received at Langley Research Center sealed in a plastic 

bag. The panel remained in the sealed bag until testing was initiated. All 

tests were performed at room temperature on six replicates for each specimen 

type. The tests were performed in accordance with the following ASTM 

standards; 1.) Tension-D3039, 2.) SBS-D2344, 3.) Compression-D3410 using the 

IITRI test fixture. 

The specimens used for moisture determination were placed in a vacuum 

oven at 140°F. Each specimen was weighed periodically to determine weight 

loss as a function of drying time. 

Manufactured by Dupont Corp., Wilmington, DE 

8 

2 
Results and Discussion 

In the summer of 1985, the exposure racks (figure 1) located at 

Cameron, LA and on the Off Shore Oil Platform were destroyed by hurricanes. 

All the following data for five year exposure will be from the three 

remaining sites; Hampton, Virginia; Toronto, Canada; and Ft. Greely, Alaska. 

Residual Compression Strength - Compression tests were conducted to 

determine the effect of exposure and exposure site on the residual strength. 

The baseline strengths for the as-fabricated ground exposure specimens are 

given in Table 11. The actual specimen size, maximum failure load and 

failure stress for each specimen are given in Table 11. The mean strength 

and standard deviation are also given for each material. The results of 

tests on compression specimens that have been exposed up to 5 years are 

tabulated in Tables 111-VI. These tables include the specimen size, failure 

load, and failure stress for each specimen that has been tested. The mean 

compression strength and standard deviation for each set of replicate 

specimens (same exposure site and exposure time) are also given in Tables 

111-VI. A summary of the mean strengths and standard deviations for the 

baseline and exposed specimens are given in Table VII. 

exposure time and exposure location are presented in figures 4-7. 

failure stress and range of failure stress are presented for each set of six 

replicate specimens. Also shown in each figure is the scatter in the 

baseline strength for each material. 

failure stress to the mean baseline compressive strength for the material 

type * 

figure 4. 

+3 percent). 

for specimens exposed for 5 years at Toronto, Canada. 

strength of specimens exposed at Hampton, VA and in the Gulf of Mexico 

equalled or exceeded the minimum baseline strength of 98 percent. 

compressive strength for Kevlar-49/F-185 is presented in figure 5. 

baseline scatter for this material is 5 percent(-1 percent to 4 percent). 

The minimum mean residual compression strength was 90 percent for specimens 

exposed one year at Ft. Greely, AK. Residual strength of specimens from 

Cameron, LA, Gulf of Mexico, and Hampton, VA all equalled or exceeded the 

minimum baseline scatter band of 97 percent. Residual compressive strength 

for Kevlar-49/LRF-277 is presented in figure 6. The baseline scatter for 

this material is 11 percent(-4 percent to +7 percent). 

residual compression strength was 84 percent for specimens exposed for one 

year at Ft. Greely, AK. The residual strengths for all exposure sites are 

below the minimum baseline scatter band. 

made for all Kevlar-49/epoxy materials is that all residual strengths for 

specimens from Toronto, Canada and Ft. Greely, AK are below the minimum 

baseline scatter indicating a possible effect from the cold climate. 

Residual compression strength for T300/E-788 graphite/epoxy is presented in 

figure 7. 

minimum mean residual compressive strength was 91 percent for specimens 

exposed for 3 years at Cameron, LA. 

averages are within 3 percent of the baseline scatter band. 

each material is presented in figures 8-11. 

comparison of the mean compression strength at each exposure site with the 

mean baseline compression strength value for that material system. 

data point is the average of six tests. 

(figure 9) has lower compression strength retention than the other 

The residual compressive strength for each material as a function of 

The mean 

The residual strength is the ratio of 

Residual compressive strength for Kevlar-49/CE-306 is presented in 

The baseline scatter for this material is 5 percent(-2 percent to 

The minimum mean residual compressive strength was 93 percent 

Residual mean 

Residual 

The 

The minimum mean 

A general observation that can be 

L 

The baseline scatter is 7 percent(-4 percent to +3 percent). The 

All of the mean residual strength 

The effect of exposure location on the residual compression strength of 

The data points represent a 

Each 

The Kevlar-49/LRF-277 material 

3 
materials. The Kevlar-49/LRF-277 varies from 84 to 94 percent after one 

year of exposure, 84 to 91 percent after three years of exposure, and 87 to 

95 percent after five years of exposure. 

(figs. 8,10,11) exceeded 90 percent after one year of exposure, 93 percent 

after three years and five years of exposure. 

The data points shown in figure 12 represent a comparison of the mean 

baseline compression strength with the mean compression strength data of 

specimens exposed at the five different locations shown in Fig. 2. Also 

shown in figure 12 is the scatter band in the baseline strength for all 

materials tested. Each point shown for 1 or 3 years of exposure is the 

average of thirty tests(5 racks and 6 replicates of each material) while 

points at 5 years of exposure are the average of eighteen tests(3 racks and 

6 replicates of each material). 

exposed painted specimens shown in figure 12 vary between 88 and 101 percent 

of the average baseline strength. The T-300/E-788 graphite is at the upper 

bound and varies between 98 and 101 percent of the average baseline 

strength. Kevlar-49/LRF-277 material is at the lower bound and varies 

between 88 and 90 percent of the average baseline strength. 

compression strengths for all materials except Kevlar-49/LRF-277 fall within 

the baseline scatter band. 

The other material systems 

The residual compression strengths of 

Residual 

Residual Short-Beam Shear Strength - Short-beam-shear(SBS) tests were 

conducted to determine degradation of the fiber-to-matrix bond as a function 

outdoor exposure time and exposure site. Generally interlaminar failures 

occured at the mid-plane of the specimens. The baseline strengths for the 

as-fabricated ground exposure specimens are given in Table VIII. The actual 

specimen size, maximum failure load and failure stress for each baseline 

specimen are given in Table VIII. The mean strength and standard deviation 

are also given for each material. The results of tests on SBS specimens 

that have been exposed up to 5 years are tabulated in Tables IX-XII. These 

tables include the specimen size, failure load, and failure stress for each 

specimen that has been tested. The mean SBS strength and standard deviation 

for each set of replicate specimens (same exposure site and exposure time) 

are also given in Tables IX-XII. 

standard deviations for the baseline and exposed specimens are given in 

Table XIII. 

time and exposure location are presented in figures 13-16. The mean failure 

stress and range of failure stress are presented for each set of six 

replicate specimens. Also shown in each figure is the scatter in the 

baseline strength for each material. 

failure stress to the mean baseline SBS strength for the material type. 

The baseline scatter for this material is 11 percent(-7 percent to +4 

percent). The minimum mean residual SBS strength was 93 percent for 

specimens exposed for 1 year at Ft. Greely, AK and 3 years at Cameron, LA. 

The mean residual SBS strength for all other exposure sites and exposure 

times exceeded the baseline minimum of 93 percent. Residual SBS strength 

for Kevlar-49/F-185 is presented in figure 14. The baseline scatter for 

this material is 10 percent (2 5 percent). The minimum mean SBS strength 

was 85 percent for specimens exposed for one year at Ft. Greely, AK. The 

mean residual SBS strength for all other exposure sites and exposure times 

exceeded the baseline minimum of 95 percent. 

Kevlar-49/LRF-277 is presented in figure 15. 

material is 9 percent(-5 percent to +4 percent). The minimum mean SBS 

strength was 87 percent for specimens exposed for one year at Cameron, LA 

and five years at Ft. Greely, AK. Eight of the eleven remaining data points 

are between 87 percent and 95 percent, the baseline minimum. The Kevlar49/LRF-277 exhibited poor SBS strength retention when compared to the other 

A summary of the mean strengths and 

The residual SBS strength for each material as a function of exposure 

The residual strength is the ratio of 

Residual SBS strength for Kevlar-49/CE-306 is presented in figure 13. 

Residual SBS strength for 

The baseline scatter for this 

4 
two Kevlar-epoxy systems. 

graphite/epoxy is presented in figure 16. The baseline scatter for this 

material is 7 percent (-4 percent to +3 percent). The minimum mean SBS 

strength was 96 percent, the baseline minimum, for specimens exposed for 

five years at Ft. Greely, AK. Specimens exposed at sites other than Ft. 

Greely exceeded 100 percent strength retention after exposure. 

material is shown in figure 17-20. 

of the average SBS strength at each exposure site with the average baseline 

SBS strength for that material system. The Kevlar-49/LRF-277 has lower SBS 

strength retention than the other materials. 

Kevlar-49/LRF-277 (figure 18) varies from 87 to 97 percent after one year of 

exposure, 87 to 95 percent after three years of exposure, and 87 to 96 

percent after five years of exposure. The other material systems (figures 

17,19,20) strength retention exceed 92 percent after one year of exposure, 

93 percent after three years of exposure, and 91 percent after five years of 

exposure. 

exposure are shown in figure 21. 

the average baseline SBS strength with the average SBS strength data of 

specimens exposed at five different locations shown in figure 2. 

shown for 1 or 3 years of exposure is the average of thirty tests(5 racks 

and 6 replicates of each material) while points at 5 years of exposure are 

the average of eighteen tests(3 racks and 6 replicates of each material). 

The SBS strengths vary between 91 and 103 percent of baseline strength. 

Like the compression strength, the T-300/E-788 SBS strength is at the upper 

bound, between 100 and 103 percent of the average baseline strength, while 

the Kevlar-49/LRF-277 is at the lower bound between 91 and 92 percent of the 

average baseline strength. Residual short beam shear strengths for all 

materials except Kevlar-49/LRF-277 fall within the baseline scatter band. 

Residual SBS strength for T300/E-788 

Effects of different environments on the residual SBS strength for each 

The data points represent a comparison 

The strength retention of 

Residual SBS strengths of painted specimens with up to five years of 

The data points represent a comparison of 

Each point 

Residual Tension Strength - Tension tests were conducted to determine the 

effect of environmental exposure and exposure site on the residual strength. 

The baseline strengths for the as-fabricated ground exposure specimens are 

given in Table XIV. The actual specimen size, maximum failure load and 

failure stress for each specimen are given in Table XIV. 

and standard deviation are also given for each material. 

tests on tension specimens that have been exposed up to 5 years are 

tabulated in Tables XV-XVIII. 

failure load, and failure stress for each specimen that has been tested. 

The mean tension strength and standard deviation for each set of replicate 

specimens (same exposure site and exposure time) are also given in Tables 

XV-XVIII. A summary of the mean strengths and standard deviations for the 

baseline and exposed specimens are given in Table XIX. 

The residual tensile strength for each material as a function of 

exposure time and exposure location are presented in figures 22-25. The 

mean failure stress and range of failure stress are presented for each set 

of six replicate specimens. Also shown in each figure is the scatter in the 

baseline strength for each material. 

failure stress to the average baseline compressive strength for the material 

type - 

22. The baseline scatter for this material is 11 percent(-6 percent to +5 

percent). The minimum mean residual tension strength was 99 percent for 

specimens exposed for 3 years at Cameron, LA. The mean residual tension 

strength for all other exposure sites and exposure times exceeded 100 

percent of baseline mean. Residual tension strength for Kevlar-49/F-185 is 

presented in figure 23. The baseline scatter for this material is 11 

percent (-3 percent to +8 percent). 

The mean strength 

The results of 

These tables include the specimen size, 

The residual strength is the ratio of 

Residual tension strength for Kevlar-49/CE-306 is presented in figure 

The mean tension strength for all 

5 
exposure sites exceeded 100 percent of the baseline mean strength. 

tension strength for Kevlar-49/LRF-277 is presented in figure 24. The 

baseline scatter for this material is 7 percent(-4 percent to +3 percent). 

The minimum mean SBS strength was 99 percent for specimens exposed for one 

year in the Gulf of Mexico. All other exposure sites exceeded 100 percent 

of the baseline mean strength. 

graphite/epoxy is presented in figure 25. The baseline scatter for this 

material is 8 percent (54 percent). The minimum mean tension strength was 

97 percent for specimens exposed for one year at Cameron, LA and in the Gulf 

of Mexico. 

at Toronto, Canada, exceeded 100 percent of baseline mean strength. 

each material is shown in figures 26-29. The data points represent a 

comparison of the average tension strength at each exposure site with the 

average baseline tension strength for that material system. All data points 

are above the baseline minimum strength. The minimum value for all 

exposures is 97 percent for one year exposure of T-300/E-788 at Cameron, LA. 

Most of the remaining points exceed 100 percent of baseline mean strength. 

The data points shown in figure 30 represent a comparison of the 

average baseline tension strength with the average tension strength data of 

specimens exposed at the five different locations shown in Fig. 2. Also 

shown in figure 30 is the scatter band in the baseline strength for all 

materials tested. Each point shown for 1 or 3 years of exposure is the 

average of thirty tests(5 racks and 6 replicates of each material) while 

points at 5 years of exposure are the average of eighteen tests(3 racks and 

6 replicates of each material). The average of all specimens exceed 100 

percent of the baseline mean strength. 

Moisture AbsorDtion - Temperature, relative humidity, exposure conditions, 

type of fiber and matrix determine the amount of moisture that a composite 

material will absorb. The object of these tests is to determine the 

moisture absorption of composite materials when exposed to various outdoor 

realtime environments. A summary of moisture absorption as a fraction of 

composite specimen weight for painted specimens that were exposed for three 

and five years are tabulated in Table XX and shown in figures 31-34. Each 

data point for the painted specimens is the average of six replicates. 

Kevlar-49/epoxy materials absorb four to five times more moisture than 

graphite/epoxy because the Kevlar fibers absorb moisture. All materials 

show an increase in moisture absorption from the third to fifth years. The 

average values, for each material, shown in Table XX compare well with 

published values for other Kevlar/epoxy and graphite/epoxy systems 

(reference 1). A summary of the weight loss for the unpainted specimens is 

given in Table XXI and shown in figures 31-34. Each data point for the 

unpainted specimens is from a single specimen. All values in Table XXI 

appear reasonable except for the 0.74 percent weight loss for the T-300/E788 material exposed in the Gulf of Mexico. Since there is only one 

specimen available it is not possible to determine if this is a valid data 

point. Comparing the average weight loss shown in Table XX and XXI 

indicates the Kevlar-49/F-185 (figure 32) retains approximately 0.6 percent 

more moisture when painted. The Kevlar-49/LRF-277(figure 33) material 

retains 0.1 to 0.3 percent less moisture when painted. Paint has little 

effect on moisture absorption of Kevlar-49/CE-306(figure 31) and T-300/E788(figure 34) after three years of exposure. 

the Kevlar-49/CE-306 and T-300/E-788 retains 0.15 to 0.4 percent more 

moisture when painted. 

Weathering - Effects of weathering on the bare composites that were exposed 

at Hampton, VA are shown in figures 35-38. Each figure shows the asfabricated, one year, three year and five year specimens exposed at Hampton, 

Residual 

Residual tension strength for T300/E-788 

All other specimen exposures, except after five years exposure 

Effects of different environments on the residual tension strength for 

After five years of exposure 

6 
VA. 

exposed surface. Figure 35 indicates the surfaces of Kevlar-49/CE-306 after 

exposure. The photograph of the specimen after one year of exposure 

indicates some resin has been washed away by the reduced definition of the 

pattern of the peel ply used in fabrication. 

the high spots of the warp fibers after 3 years of exposure as can be seen 

in the photograph(figure 35). Some resin still exists in the low areas 

around the fill fibers. 

remains on the surface. 

figure 36 for Kevlar-49/F-185 material indicate the surface fibers are 

coated with epoxy. The three year exposure view has the surface fibers 

exposed due to ultraviolet degradation of the surface layer of epoxy. 

five years of exposure of the Kevlar-49/F-185 material all resin has 

disappeared and it appears some of the fiber on the humps in the fill yarns 

has also disappeared. The as-fabricated views of Kevlar-49/LRF-277 material 

in figure 37 indicate most of the surface fibers are coated with epoxy. The 

one year exposure view(figure 37) indicates most of the surface resin is 

missing. All the resin is missing and some fiber damage is indicated in the 

three year exposure view shown in figure 37. After five years of exposure 

only fiber fragments remain of the outer ply and the resin shown is from 

between the plies. The T-300/E-788 Graphite/epoxy exposed for three and 

five years, shown in figure 38, has bare surface fibers. Some resin loss is 

indicated after one year of exposure. The specimens exposed at the other 

locations had similar resin loss. 

composites protected from ultraviolet exposure. 

The photographs shown in these figures is a 15X magnification of the 

Additional resin is lost on 

After five years of exposure very little resin 

The as-fabricated and one year exposure views in 

After 

This emphasizes the need to keep 

ConcludinP Remarks 

Results after five years of ground exposure indicates that all material 

systems exhibit good strength retention in compression and short beam shear. 

All material systems exceeded 85 percent strength retention after one and 

three years of exposure and 87 percent after five years of exposure, 

independent of exposure site. Residual tensile strength of all materials 

did not show a significant reduction. 

The Kevlar-49/F-185 material absorbs approximately 0.6 percent more 

Paint has little effect on moisture 

moisture when painted. 

percent less moisture when painted. 

absorption of Kevlar-49/CE-306 and T-300/E-788 after three years of 

exposure. All materials show an increase in moisture absorption from the 

third to the fifth years of outdoor exposure. 

Kevlar-49/LRF-277 material absorbs approximately 0.3 

The exposure of unpainted specimens demonstrate the need to protect 

composites from ultraviolet exposure. 

7 
REFERENCES 

1. Dexter, H.Benson and Baker,Donald J., "Worldwide flight and 

Ground-Based Exposure of Composite Materials," NASA CP-2321, 

August 1984,p.17-49. 

2. Zinberg,Herbert,"Flight Service Evaluation of Composite 

Components on the Bell Model 206L: Design, Fabrication and 

Testing,'' NASA CR-166002, November 1982. 

8 

A 
Material m? 

K-49/F-185 

W1=-49/ 

epaxy 

K-49/IRF-277 

WlW/ 

epoxy 

T-3OO/E-788 

Graphite/ 

I epoxy 

'I!ABLE I.- DESCRIPITON OF EXFOSURF: SPECIMENS 

Material 

supplier 

U.S. 

polymeric 

co. 

Ncuninal specimen thickness, in. 

mrt-beam 

shear ~ 

.070 

.080 

.070 

072 

.070 

.080 

- 

.070 

.072 

knsion 

.070 

.080 

.070 

ZZ-1 Fiber lay-up 

1 

r 01 

1 

fabric I 

+ fabric 

I 

'0/45/-45/01 2s 

*tape 1 

* The 0 degree fiber direction is oriented along the length of the test 

specimen 

9 
Material 

type 

K-49/cE-3 06 

=lar/ePoxy 

.lo13 

.loo0 

.0948 

.0987 

.0965 

.lo17 

.0790 

.0772 

.0772 

.0783 

.0776 

.0772 

K-4 9/F-18 5 

Kevlar/epxy 

rMean = 18257. 

S.D. = 337. 

525. 19979. 

510. 19600. 

510. 19977. 

509. 19981. 

515. 20937. 

515. 20585. 

Mean = 20176. 

S.D. = 489. 

416. 21467. 

425. 23822. 

420. 22640. 

402. 21718. 

407. 22853. 

410. 21677. 

Mean = 22363. 

S.D. = 909. 

r 

K-49/IRF-277 

Kevlar/epoxy 

T300/E-788 

Graphite/ 

ePw 

specnumber 

313F 

314F 

315F 

316F 

3 17F 

3 18F 

317 

3 18 

319 

320 

321 

322 

326B 

327B 

328B 

329B 

330B 

331B 

158V 

159V 

160V 

161V 

162V 

163V 

Width 

in. 

.2616 

.2667 

.2606 

.2613 

.2570 

.2541 

.2594 

.2602 

.2693 

.2581 

.2549 

.2460 

.2453 

.2311 

.2403 

.2364 

.2295 

.2450 

.2553 

.2573 

.2526 

.2562 

.2556 

.2552 

Thickness 

in. 

.0986 

.lo02 

.0974 

.0971 

.0987 

.0985 

Maximum Failure 

load stress 

lbf. psi 

463. 17950. 

481. 17999. 

476. 18753. 

472. 18603. 

460. 18135. 

453. 18099. 

.0716 

.0714 

.0684 

.0669 

.0693 

.0701 

2210. 120901. 

2315. 126012. 

2240. 129646. 

2215. 129232. 

2305. 130130. 

2185. 122139. 

Mean = 126343. 

S.D. = 4025. 

, 

S.D. = Standard Deviation 

10 
, 

IAad 

lbf. 

456. 

462. 

?'ABIE 111. - OOklPRESSION OF PAINTED Kevl~~-49/CE-306 

AFTER~ALJEXFOSURE 

Failure 

Stress,psi 

17711. 

17633. 

specNumber 

319F 

32 OF 

32l.F 

322F 

323F 

324F 

325F 

326F 

327F 

328F 

329F 

330F 

Width 

in. 

.2606 

.2660 

,2629 

.2551 

.2572 

.2616 

3 .2544 .0993 

3 .2602 .lo17 

3 .2602 .0973 

3 .2621 .0988 

3 .2563 .0973 

3 .2586 .0990 

Thiclcness 

in. 

.0988 

.0985 

.0988 

,0965 

.lo12 

.lo08 

spec* 

Number 

349F 

350F 

351F 

3523 

353F 

354F 

355F 

356F 

357F 

3581" 

359F 

360F 

m?=== Width Mckness Load Failure 

Ti.me,yr in. in. lbf. Stress,psi 

1 .2672 0962 464. 18051. 

1 2553 0 0901 429. 18650. 

1 .2667 .0967 462. 17914. 

1 .2665 .0973 454. 17508. 

1 .2575 .0996 447. 17429. 

1 .2578 s 0998 446. 17335. 

Mean = 17815. 

S.D. = 497. 

3 .2489 .0998 404. 16264. 

3 2489 1005 438. 17510. 

3 .2551 .0997 476. 18715. 

3 .2526 .0989 459. 18373. 

3 .2532 .lo05 470. 18470. 

3 .2627 .0947 434. 17445. 

Mean = 17796. 

S.D = 915. 

IA 

17902. 

465*72. I 19174. 

18134. 

16800. 

Mean = 17892. 

S.D = 774. 

Mean= 

S.D = 

16032. 

16930. 

18288. 

19308. 

16441. 

17929. 

17488. 

1239. 

(b.) exposed h the Gulf of 

11 
I 

5 

379F 

380F 

38l.F 

382F 

383F 

384F 

Thickness 

in. 

.0980 

.0973 

.0956 

.0953 

.0972 

.0987 

385F 

386F 

387F 

388F 

389F 

4 OOF 

.2560 

.2657 

.2656 

.2546 

.2662 

.2624 

.2665 

.2548 

.2629 

.2649 

.2632 

2535 

401F 

402F 

403F 

404F 

405F 

406F 

.0916 475. 20256. 

.0978 480. 18472. 

.0950 483. 19142. 

.0993 480. 18986. 

.0950 474. 18743. 

.0964 473. 18699. 

Mean = 19050. 

S.D. = 635. 

.0972 461. 17797. 

.0966 438. 17795. 

.0834 412. 18791. 

.0957 459. 18106. 

.lo07 448. 16903. 

.0962 454. 18617. 

Nean = 18001. 

S.D. 679. 

i 

-~ ~ 

Width 

in. 

.2532 

.2565 

.2573 

.2523 

.2574 

2650 462. 

463. 

468. 

Stress,psi 

20755. 

19313. 

19148. 

18294. 

18880. 

18421. , 

S.D. = 887. I -= 

12 
TABUE 111. - a"mD 

(d.) exposed at Tormto,Ontario,caMda 

ThiCkIleSS Load 

in. lbf. 

.0962 439. 

.0862 379. 

.lo08 447. 

.lo02 415. 

.0893 423. . 0963 404. 

419F 

420F 

42lF 

422F 

4231" 

424F 

Failure 

Stress,psi 

18145. 

17975. 

17155. 

16016. 

18790. 

17415. 

425F 

426F 

427F 

428F 

429F 

430F 

0980 

.loo9 

.0968 

.0950 

0960 

0955 

.0963 

.lo02 

.0942 

.0983 

.0955 

.0980 

43lF 

432F 

433F 

434F 

435F 

436F 

Mean = 17583. 

S.D. = 958. 

410. 16317. 

424. 16008. 

436. 17068. 

438. 18159. 

421. 16462. 

457 18004 

Mean = 17003. 

S.D. = 905. 

449. 18051. 

469. 18420. 

430. 17713. 

467. 18616. 

429. 17165. 

454. 17977. 

Mean = 17990. 

S.D. = 517. 

- 

.2515 

.2446 

.2585 

.2586 

.2521 

.2409 

.2564 

.2625 

.2639 

.2539 

.2664 

.265a 

.2583 

.2577 

.2552 

.2617 

2541 

13 
TABLE 111. - rn- 

(e) exposed at Ft. Greely,AK 

Load 

lbf. 

441. 

407. 

424. 

386. 

444. 

435. 

Failure 

Stress,psi 

18254. 

17780. 

15963. 

16091. 

17242. 

17756. 

Width 

in. 

4 

.2535 

.2521 

.2635 

2585 

.2652 

399F .0963 

4 67F 

468F 

390F 

39lF 

392F 

3931;’ 

46lF 

462F 

463F 

464F 

465F 

466F 

.2648 

.2646 

.2590 

.2527 

.2645 

.2610 

.2548 

.2680 

.2638 

.2630 

.2507 

.2660 

.0953 

.0908 

.lo08 

.0928 

.0971 

.2544 

S.D. = 950. I -= 

.lo06 

.0964 

.0993 

.0971 

.0883 

.loo0 

472. 

427. 

463. 

440. 

420. 

439. 

17718. 

16740. 

18002. 

17932. 

17983. 

16820. 

I -= S.D. = 17533* 592 1 

.0972 

.0934 

.0976 

.0963 

.0954 

.0953 

431. 

455. 

433. 

474. 

385. 

458. 

17402. 

18177. 

16818. 

18715. 

16097. 

18067. 

1 Mean = 17546. 

S.D. = 968. I 

14 
specMrmber 

323 

324 

325 

326 

327 

328 

329 

330 

331 

332 

333 

334 

&* 

.2566 

.2615 

.2481 

.2559 

.2585 

.2573 

'Ihiclaress mad 

in. lbf. 

0988 506. 

.0975 485. 

0970 491. 

.0992 502. 

0976 482. 

0994 490. 

2548 

.2580 

2528 

.2503 

.2582 

.2458 

Failure I 

Stress,psi 

20668. 

19623. 

20321. 

20105. 

19520. 

19438. 

michess 

in. 

c 

specimer: 

Number 

353 

354 

355 

356 

357 

358 

L 

359 

360 

361 

362 

3 63 

364 

0 

.0944 

.0971 

.0963 

.0966 

.0909 

.loo1 

.0974 

.0924 

.0949 

.0968 

.0941 

.0950 

510. 

492. 

522. 

Mean= 

S.D. = 

510. 

465. 

490. 

491. 

472. 

489. 

~ 

Mean = 20446. 

S.D. = 542. 

(b.) exposed in the Gulf of Mexico 

xndard dev 

width 

in. 

.2478 

2535 

.2491 

.2517 

.2530 

.2536 

~- 

, Failure 

Stress,psi 

20765. 

19967. 

21346. 

19903. 

20428. 

20267. 

.lo11 

.0980 

.0949 

,0930 

Mean 

S.D. 

19060. 

19459. 

18572. 

18998. 

19875. 

20036. 

= 19333. 

- 560. 

.2593 

.2505 

2559 

.2452 

.2468 

.2492 

ltion 

19946. 

496. 

20193. 

20090. 

20177. 

20686. 

20324. 

20656. 

S.D. = 257. I I - = 203540 

15 
.0993 

.0992 

,1008 

.0961 

.lo03 

.0920 

1 19786. 

' 19427. 

18810. 

19829. 

19524. 

20550. 

490. 

492. 

478. 

468. 

507. 

484. 

.lo05 

.0938 

.0961 

.lo19 

.0996 

.0974 

.lo08 

.lo15 

.0976 

.loo0 

.0969 

.lo14 

Mean = 19654. 

S.D. = 571. 

508. 19877. 

479. 20121. 

495. 21382. 

505. 20436. 

503. 20088. 

495. 20634. 

Mean = 20423. 

S.D. = 541. 

502. 19825. 

499. 20240. 

464. 19867. 

482. 19203. 

484. 19797. 

495. 19212. 

Mean = 19691. 

S.D. = 407. 

16 
TAmEIv. -mm 

(a) exposed at Toronto, canada 

Mrmber T-tYr ;peck Exposure 

413 1 

414 1 

415 1 

416 1 

417 1 

418 1 

419 3 

420 3 

421 3 

422 3 

423 3 

424 3 

425 5 

426 5 

427 5 

428 5 

429 5 

430 5 

Width ?hichess Load Failure 

in. in. lbf. Stress,psi 

.2563 .0999 477. 18630. 

.2673 .0958 500. 19526. 

.2429 0945 454. 19779. 

.2524 1020 482. 18722. 

.2563 1013 503. 19374. 

.2530 1005 493. 19389. 

Mean = 19236. 

S.D. = 459. 

.2539 .loo1 483. 19004. 

.2507 .loo9 495. 19569. 

.2489 .lo15 492. 19475. 

.2569 .0969 467. 18760. 

.2597 .lo06 500. 19138. 

.2454 .0993 485. 19903. 

Mean = 19308. 

S.D. = 417. 

.2437 .0978 482. 20223. 

2580 .0934 461. 19131. 

,2576 .0961 463. 18703. 

.2527 .0935 471. 19934. 

2499 .loo0 487. 19488. 

.2601 .0981 486. 19047. 

Mean = 19421. 

S.D. = 575. I I I I 

17 
TABIE IV. - OXCLLJDED 

Width 

Mrmber 

467 1 .2476 

468 1 .2551 

469 1 .2445 

470 1 .2600 

471 1 .2511 

472 1 .2543 

(e) exposed at Ft. Greely,AK 

'Ihickness Imd Failure 

in. Ibf. Stress,psi 

.loo0 460. 18578. 

.lo15 458. 17688. 

.lo12 453. 18308. 

.0979 456. 17915. 

.0987 448. 18076. 

.lo06 467. 18255. 

Mean = 18137. 

S.D. = 314. 

I .lo10 

.0939 

.lo13 

.0953 

.0950 

.0943 

461 

4 62 

463 

464 

465 

466 

455 

456 

457 

458 

459 

460 

5 

5 

5 

5 

5 

5 

.2534 

.2616 

.2528 

.2611 

.2488 

.2487 

.2542 

.2471 

.2585 

.2451 

.2481 

.2563 

.0942 

.0945 

.0995 

.0988 

.0991 

.0969 

463. 

461. 

486. 

481. 

453. 

447. 

18091. 

18767. 

18978. 

19331. 

19166. 

19060. 

455. 

452. 

477. 

= 18899. 

438. - 

18672. 

18273. 

18789. 

18384. 

19206. 

I - S.D. = 350. = 18714* 

18 
Failure 

Stress,psi 

19796. 

21553. 

21748. 

22104. 

20149. 

20963. 

= 21052. 

921. - 

1 

ThiCkneSS 

in. 

Load Failure 

Ibf. Stress,psi 

Laad 

Ibf. 

332B 

333B 

334B 

335B 

336B 

337B 

.2387 

.2539 

.2229 

2510 

2558 

2294 

.0783 

.0773 

.0788 

.0779 

.0785 

.0759 

370. 

423. 

382. 

395. 

397. 

407. 

Mean 

S.D. 

338B 

339B 

340B 

341B 

342B 

343B 

3 

3 

3 

3 

2512 

.2364 

.2539 

.2194 

.0777 

.0814 

.0789 

0778 

368. 

361. 

376. 

355. 

393. 

355. 

18854. 

19628. 

18193. 

20508. 

20024. 

19392. 

Mean 

S.D. 

= 19433. 

- 827. 

(b.) expc6ed in the Gulf of Mexi00 

Width 

in. spec* 

Number 

362B 

363B 

364B 

365B 

366B 

367B 

.2263 

.2300 

.2438 

.2365 

.2326 

.2288 

.0769 

.0777 

.0788 

.0774 

.0787 

.0767 

359. 

372. 

396. 

366. 

382. 

385. 

20629. 

20816. 

20613. 

19994. 

20868 

21939. 

Mean = 20810. 

S.D. = 635. 

.0796 

.0797 

.0790 

0773 

.0782 

.0786 

404. 

352. 1 

370. 

20465. 

18175. 

20834. 

18018. 

18203. 

19147. 

.2480 

.2430 

370B .2248 

.2398 334. 

317. 

349. 

Mean= 

S.D. = 

I 

I 373B 1 3 I .2319 

19140. 

1241. 

19 
TABLE v. - a3lTmmD. 

J 

Number 

392B 

393B 

394B 

395B 

396B 

ExJ?-= 

T-fF 

1 

1 

1 

1 

1 

398B 

399B 

400B 

401B 

402B 

403B 

Width 

in. 

.2517 

.2375 

.2551 

.2524 

.2317 

.2445 

404B 

405B 

406B 

407B 

408B 

409B 

Thickness 

in. 

.0769 

.0789 

.0785 

.0799 

.0793 

.0783 

.2449 

.2253 

.2483 

.2393 

2461 

.2509 

.2386 

.2266 

2683 

.0793 

.0779 

.0797 

.0785 ~ .0788 ~ .0837 

.0810 

.0781 

.0761 

.2237 .0771 

.2245 I .0778 

.2377 .0778 

Imd 

lbf. 

412. 

380. 

360. 

404. 

364. 

386. 

Failure 

Stress,psi 

20279. 

17977. 

20033. 

19811. 

20163. 

Mean = 19925. 

S.D. = 1082. 

403. 

376. 

373. 

407. 

402. 

370. 

21453. 

19389. 

17762. 

21059. 

19185. 

21456. 

Mean = 20051. 

S.D. = 1509. 

394. 

349. 

375. 

343. 

321. 

347. 

20288. 

19885. 

18949. 

19887. 

18378. 

18764. 

Mean = 19359. 

S.D. = 762. 

20 
TABIEV. -- 

(a) exposed at Toronto, Canada 

-* 

Nilmber 

422B 

423B 

424B 

425B 

426B 

w0-e 

T-,yr 

1 

1 

1 

1 

1 

Width 

in. 

428B 3 

429B 3 

430B 3 

43lB 3 

432B 3 

433B 3 

.2429 

.2243 

.2226 

.2410 

.2200 

.2355 

.2578 .0799 362. 

.2498 .0773 372. 

.2508 .0775 384. 

.2490 .0779 368. 

.2366 .0774 346. 

.2276 . 0788 343. 

michess 

in. 

.0798 

.0772 

.0772 

.0787 

.0790 

.0802 

434B 

435B 

436B 

437B 

438B 

439B 

Lbad 

lbf. 

b 

Mean = 18931. 

S.D. = 731. 

5 .2526 .0768 415. 21392. 

5 .2498 .0780 412. 21145. 

5 .2407 .0795 403. 21060. 

5 .2510 .0800 440. 21912. 

5 .2377 .0816 401. 20674. 

5 .2385 0787 387. 20618. 

Mean = 21134. 

S.D. = 481. 

397. 

345. 

352. 

364. 

346. 

368. 

20481. 

19924. 

20483. 

19192. 

19908. 

19484. 

= 19912. 

- 520. 

17574. 

19265. 

19756. 

18972. 

18894. 

19125. 

21 
TABLE v. - mmm 

(e) exposed at Ft. Greely,AK 

5 

5 

5 

5 

5 

5 

476B 

477B 

478B 

479B 

480B 

48lB 

,2298 

.2527 

,2218 

,2283 

.2469 

.2374 

470B 

47lB 

472B 

473B 

474B 

475B 

464B 

465B 

466B 

467B 

468B 

469B 

.2317 

.2581 

.2360 

.2529 

.2526 

.2414 

.2531 

.2363 

.2339 

.2206 

.2375 

.2279 

Failure 

.0772 18840. 

.0767 18286. 

.0786 19246. 

.0799 

.0812 

.0770 

I 374. I 18509. 

385. 18770. I 366. I 19690. 

.0792 

.0770 

.0759 

.0790 

.0777 

.0769 

Mean = 18890. 

S.D. = 509. I 

1 

391. 

373. 

360. 

361. 

384. 

366. 

19506. 

20500. 

20278. 

20715. 

20809. 

20884. 

Mean = 20449. 

S.D. = 512. I 

.0810 

.0785 

.0767 

.0778 

.0788 

.0792 

360. 

349. 

360. 

361. 

376. 

382. 

19340. 

17593. 

21161. 

20325. 

19326. 

20317. 

22 
(a) exposed at Cameron, LA 

Lioad 

lbf. 

2320. 

2500. 

2375. 

2485. 

2205. 

2140. 

164V 

165V 

166V 

167V 

168V 

169V 

Failure 

Stress,psi 

127382. 

138866. 

130494. 

136998. 

127316. 

121564. 

I 17OV 171V 

19 10 

1970. 

1980. 

1960. 

2280. 

2225. 

172V 

173V 

174V 

175v 

105964. 

110858. 

112005. 

106234. 

129374. 

126174. 

.2558 

.2550 

.2567 

.2562 

.2562 

.2555 

. 

.2575 

.2568 

.2562 

.2584 

.2569 

* 

Width Thickness bad Failure 

Number T-,yr in. in. lbf. Stress,psi 

194V 1 .2564 .0660 2250. 132960. 

195v 1 .2555 .0719 2180. 118669. 

196V 1 2552 .0708 2245. 124252. 

197v 1 2460 .0688 2365. 139736. 

198V 1 .2440 .0690 2205. 130969. 

199v 1 2543 .0708 2055. 114139. 

Mean = 126787. 

S.D. = 9546. 

20ov 3 2578 0668 2085. 121073. 

201v 3 2558 .0715 2345. 128214. 

202v 3 .2559 .0687 2170. 123433. 

203V 3 2560 0714 2140. 117078. 

204V 3 2557 0690 1950. 110524. 

205v 3 .2445 0650 1685. 106025. 

Mean = 117724. 

S.D. = 8282 

spec* Ex3pc 

I 

-. 

m&S 

in. __ 

.0712 

.0706 

.0709 

,0708 

.0676 

.0689 

.0700 

.0692 

.0690 

.0714 

.0686 

.0691 

~ ~- 

Mean = 130437. 

S.D. = 6510. 

Mean = 115102. 

S.D. = 10159. 

(b.) exposed in the Gulf of wco 

23 
Specimen 

Number 

224V 

225v 

226v 

227v 

228V 

229V 

230V 

231V 

Width 

in. 

.2568 

.2607 

.2560 

.2556 

.2570 

.2559 

.2559 

.2551 

.2552 

.2557 

.2549 

.2548 

.2566 

.2582 

.2569 

.2552 

.2543 

.2555 

-?os== 

T=,yr 

1 

1 

1 

1 

1 

1 

3 

3 

Mclmess md Failure 

in. lbf. Stress,psi 

.0692 2470. 138994. 

.0690 2290. 127305. 

.0703 2285. 126967. 

.0714 2270. 124385. 

.0718 2250. 121934. 

.0680 2230. 128152. 

MEAN = 127956. 

S.D. = 5870. 

.0693 2195. 123774. 

.0714 2350. 129021. 

.0688 2225. 126725. 

.0692 2085. 117834. 

.0692 2240. 126991. 

.0706 2375. 132026. 

Mean = 126062. 

S.D. = 4870. 

.0715 2215. 120729. 

.0712 2300. 125110. 

.0710 2345. 128564. 

.0716 2130. 116570. 

.0713 2190. 120784. 

.0685 2440. 139415. 

Mean = 125195. 

S.D. = 8091. 

7 

- 

24 
TABLEVI. -0 

(d) exposed at Tbmnto, Canada 

ThiCkneSS 

in. 

.0717 

.0683 

0693 

.0672 

.0716 

.0709 

254V 

255V 

256V 

257V 

258V 

259V 

Load 

lbf. 

2340. 

2305. 

2275. 

2140. 

2360. 

2215. 

26OV 

261V 

262V 

263V 

264V 

26% 

.0714 

.0678 

.0680 

.0705 

0715 

.0689 

~ ~~~ 

266V 

267V 

268V 

26971 

27OV 

271V 

Eizean = 127306. 

S.D. = 3489. 

2085. 114561. 

2095. 123698. 

2030. 116933. 

2385. 133293. 

2375. 129905. 

2215. 125138. 

Mian = 123921. 

S.D. = 7234. 

1 

.2549 

.2563 

.2550 

.2562 

2555 

.2559 

.2549 

.2498 

.2553 

.2538 

,2557 

2569 

2554 

2565 

2515 

.2564 

.2565 

.2549 

Failure 

Stress,psi 

128034. 

131674. 

128738. 

124298. 

129005. 

122084. 

.0719 

0708 

.0696 

.0716 

.0710 

.0709 

2180. 

2290. 

2220. 

2460. 

2390. 

2300. 

Mean= 

S.D. = 

118715. 

126100. 

126825. 

134000. 

131236. 

127266. 

127357. 

5210. 

25 
(e) exposed at Ft. Greely,AK 

L 

308V 1 .2558 .0713 

309V 1 .2563 .0688 

31OV 1 .2549 .0689 

311V 1 .2553 0711 

3 12V 1 .2553 .0695 

3 13V 1 .2557 ,0699 

5 

302V 

303V 

304V 

305V 

306V 

307V 

296V 

297V 

298V 

299V 

300V 

3 01V 

- 

.2575 .0676 

2521 

.2557 

.2525 

.2555 

.2650 

.2550 

2395. 

1970. 

2080. 

2450. 

2470. 

2550. 

0710 

.0695 

.0686 

.0715 

.0694 

.0705 

137588. 

112593. 

112364. 

134793. 

135049. 

141456. 

Mean = 128974. 

S.D. = 13000. 

* 

.0684 1 .0720 

.2560 

.2576 

.2557 

.0710 

.0710 

.0705 

Imd 

Ibf. 

2340. 

2090. 

2270. 

2095. 

2010. 

2200. 

Failure 

Stress,psi 

128300. 

118525. 

129252. 

115415. 

113282. 

123088. I 1 

Mean= 

S.D. = 

2040. 

2265. 

2185. 

2140. 

2150. 

121310. 

6664. 

117045. 

114793. 

130762. 

119606. 

116361. 

119594. 

I Mean = 119694. 

S.D. = 5739. 

26 
ln* 

E 

cp 

al 

.t: 

*. 

*IC 

*m 

Pm 

VI 

m 

co 

w 

m 

0 

m 

ln 

cv 

0 

w I I I I 

I. I. I. I. 

4 

c Is; I: 
T3 OO/E-788 

Graphite/ 

epoxy 

.2625 

.2628 

.2613 

.2612 

.2630 

.2650 

.2425 

.2343 

.2467 

.2634 

.2364 

.2474 

.2568 

.2562 

.2557 

.2563 

.2564 

.2541 

1F 

2F 

3F 

4F 

5F 

6F 

.0905 190. 5998. 

.0965 202. 5974. 

.0991 205. 5937. 

.0908 195. 6166. 

.0950 210. 6304. 

.0963 195. 5731. 

MEAN = 6018. 

S.D. = 197. 

.0775 95. 3791. 

.0776 95. 3919. 

,0774 103. 4046. 

,0769 105. 3888. e 0773 95. 3899. e 0779 95. 3697. 

MEAN = 3873. 

S.D. = 119. 

.0720 286. 11601. 

.0723 266. 10770. 

.0730 280. 11250. 

.0734 285. 11362. 

.0715 270. 11046. 

.0713 273. 11301. 

MEAN = 11222. 

S.D. = 285. i 

IB 

2B 

3B 

4B 

5B 

6B 

1v 

2v 

3v 

4v 

5v 

6v 

ThiCkneSS *"I in. 

.2542 

.2493 

.2505 

.2575 

.2347 

.2461 

.0853 

.0946 

.0877 

.0940 

,0848 

.0946 

Maximum Failure 

load stress 

Ibf. Psi 

145. 5015. 

170. 5406. 

157. 5360. 

178. 5515. 

130. 4899. 

170. 5477. 

MEAN = 5279. 

S.D. = 258. 

S.D. = Standard Deviation 

28 
ThidUESS , in. 

I .0905 

.0881 

.0942 

.0931 

.0905 

I .0911 

TARlX IX. - SHOKT EBM SHEAR STRE" OF KEVLAR-49/CE-306 

AFTER-ALJM#xsuRE: 

Width 

in. 

Thic)mesS 

in. 

Failure 

lbf. 

7F 

8F 

9F 

10F 

1lF 

12F 

176. 

146. 

165. 

165. 

170. 

137. 

5420. 

5011. 

5079. 

5279. 

5348. 

4795. 

.2577 

.2483 

.2595 

.2457 

.2520 

.2524 

.2576 

2594 

.2594 

.2580 

.2590 

.2426 

.0945 

.0880 

.0939 

.0954 

.0946 

.0849 

.0943 

0905 

.0893 

.0927 

.0863 

0891 

Mean= 5156. 

S.D. = 236. 

13F 

14F 

15F 

16F 

17F 

18F 

~~ 

3 

3 

3 

3 

3 

3 

155. 

154. 

144. 

170. 

143. 

144. 

4786. 

4920. 

4662. 

5331. 

4798. 

4996. 

I 

Mean= 4916. 

S.D. = 234. 

(b.) exposed in the Gulf of Mexico 

Failure 

Stress,psi 

4805. 

5046. 

5170. 

5485. 

2449 

38F .2578 

39F 

40F 

41F 

42F 

1 

1 

1 

1 

.2470 

.2511 

.2443 

.2490 

150. 

173. 

156. 5144. I 

,,,. 

159. 1 5292. 

5157. 

43F 

44F 

45F 

46F 

47F 

48F 

.2469 

.2597 

.2564 

.2611 

.2593 

.2475 

.0931 

.0902 

.0863 

.0943 

.0951 

,0851 

179. 

159. 

137. 

185. 

163. 

148. 

5840. 

5091. 

4709. 

4926. 

5674. 

5194. 

5239. 

S.D. = 437. 

S.D. = stanaardl deviation 

29 
specimen 

Number 

.0928 

.0881 

.0901 

.0967 

.0941 

.0847 

67F 

68F 

69F 

70F 

71F 

72F 

Mean= 5413. 

S.D. = 265. 

174. 5400. 

138. 4843. 

168. 5486. 

175. 5373. 

168. 5196. 

142. 4904. 

Mean= 5200. 

S.D. = 271. 

73F 

74F 

75F 

76F 

77F 

78F 

79F 

80F 

81F 

82F 

83F 

84F 

I I I 

.2604 

.2442 

.2586 

.2584 

.2542 

.2572 

.0940 

.0811 

.0961 

.0901 

.0946 

.0904 

180. 

129. 

184. 

167. 

180. 

165. 

5515. 

4885. 

5553. 

5380. 

5614. 

5322. 

Mean= 

S.D. = 5378. 

265. 

.2473 

.2594 

.2563 

.2457 

.2485 

.2595 

.2604 

.2426 

.2549 

.2526 

.2577 

.2564 

30 
'spec* Expo== Number T=,yr 

97F 1 

98F 1 

99F 1 

lOOF 1 

l0lF 1 

102F 1 

103F 3 

104F 3 

105F 3 1 106F 13 

.0928 

.0931 

.0881 

.0898 

.0826 

.0946 

TABllEM. -axvlmwm 

exposed at Toronto, Canada 

178. 

190. 

155. 

154. 

140. 

180. 

Mean= 

S.D. = 

Width lqckness I Load I Failure I 

in. In. lbf. Stress,psi 

.2576 

.2306 

.2501 

.2597 

.2495 

.2431 

.2488 

.2511 

4 

.0944 190. 5860 

.0868 123. 4609. 

126. 

175 

168. 

148. 

5752. 

5894. 

4849. 

5578. 

5491. 

5075. 

I 5289. 

5291. 

I 

Mean= 5041. 

S.D. = 344. 

L 

5109. 

5683. 

5503. 

.2301 .0847 

.2577 I .0913 

.2596 .0884 

.2474 I .0884 

2455 

2528 

.2442 

.2595 

.2558 

.2544 

.0945 

.0831 

.0828 

.0857 

.0951 

0832 

170. 

133. 

132. 

156. 

170. 

130. 

5496. 

4748. 

4896. 

5261. 

5241. 

4606. 

31 
TABLE IX. - CONCLLJDED 

(e) exposed at Ft. Greely,AK 

139. 

164. 

131. 

142. 

155. 

169. 

15lF 

152F 

153F 

154F 

155F 

156F 

4921. 

5222. 

4699. 

4942. 

5081. 

5316. I 

145F 

146F 

147F 

148F 

149F 

150F 

139F 

14 OF 

14 lF 

142F 

143F 

144F 

Width 

in. 

.2562 

.2574 

.2595 

.2572 

.2517 

.2498 

.2443 

.2602 

.2586 

.2574 

.2575 

.2592 

.2402 

.2544 

.2510 

.2584 

.2568 

.2529 

- 

Thickness 

in. 

.0851 

.0926 

.0900 

.0883 

.0882 

.0886 

.0915 

.0941 

.0912 

.0935 

.0883 

.0968 

.0882 

,0923 

.0833 

.0834 

.0891 

.0940 

129. 

156. 

160. 

153. 

147. 

143. 

4438. 

4909. 

5138. 

5053. 

4966. 

4846. 

Mean= 4892. 

S.D. = 245. 

158. 

183. 

175. 

183. 

161. 

184. 

5284. 

5606. 

5565. 

5703. 

5311. 

5500. 

32 
TABLE X. - SHOKT BEAM SHEAR OF KEXTAR-49/F-185 

2PIER-m 

17 

18 

3 

3 

miin. 

.0930 

.0881 

.0901 

.0996 

.0953 

.0927 

mad 

Ibf. 

190. 

173. 

176. 

205. 

190. 

190. 

37 

38 

1 . 2627 

1 .2634 

IA 

y Failure 10 

width 

in. 

Thickness 

in. 

. 2600 

. 2618 

.2625 

.2614 

.2622 

.2620 

.0942 

.0938 

.0893 

.0946 

.0946 

.0978 

5879. 

5894. 

5951. 

5884. 

5866. 

5971. 

5908. 

43. 

Mean= 

S.D. = 

. 2581 

.2607 

.2668 

.2597 

.2592 

.ma 

.0934 

.0968 

.lo52 

.0965 

.0947 

.089a 

186. 

209. 

177. 

225. 

199. 

206. 

5787. 

6211. 

5690. 

6012. 

5955. 

6294. 

I 3 

234. 5992. I Mean= 

S.D. = 

(b.) exposed in the Gulf of Mexico 

I Failure 

Stress,psi 

5833 . 5591. 

5596. 

5675. 

5744. 

5863. 

1 

1 

1 

1 

39 

40 

41 

42 

.ma 

.2720 

.2603 

2622 

116. I -=- 5717* I S.D. = 

.0977 

.0977 

.0959 

.0893 

.0913 

,0938 

201. 

220. 

192. 

172. 

190. 

196. 

- 5883. 

6436. 

5668. 

5877. 

6199. 

6004. 

43 

44 

45 

46 

47 

48 

.2623 

.2624 

.2649 

.2458 

.2518 

e 2610 

6011. 

S.D. = 

S.D. = stardarcz deviation 

33 
Width 

Number 

67 1 .2469 

68 1 .2600 

72 

i- Thickness L&d Failure 

in. lbf. Stress,psi 

.0894 178. 6048. 

0918 190. 5970. 

73 

74 

75 

76 

77 

78 

79 

80 

81 

82 

83 

84 

.2657 

.2743 

.2455 

.2598 

1 

1 

1 

1 

,1039 

.lo05 

0923 

0923 

225. 

191. 

230. 

194. 

6113. 

6322. 

6257. 

6068. 

3 

3 

3 

3 

3 

3 

5 

5 

5 

5 

5 

5 

34 

1 

Mean= 6130. 

S.D. = 134. 

,2788 1012 226. 6008. 

.2620 0940 208. 6334. 

.2606 .0909 194. 6142. 

.2603 0956 218. 6570. 

.2662 e 0960 202. 5928. 

2581 0922 195. 6146. 

Mean= 6188. 

S.D. = 233. 

.2534 .lo15 209. 6094. 

.2519 .0920 201. 6505. 

2651 .lo50 210. 5658. 

.2636 .lo19 196. 5473. 

.2573 .lo30 205. 5801. 

.2625 .lo32 217. 6008. 

Mean= 5923. 

S.D. = 364. 
TABLE X. - CWITNWl 

- 

97 

98 

99 

100 

101 

102 

103 

104 

105 

106 

107 

108 

109 

110 

111 

112 

113 

114 

(a) exposedatToront0, Canada 

Width Thi- Load Failure -*- T-tyr in. in. lbf. Stress,psi 

1 2571 .lo20 180. 5148. 

1 2565 0877 183. 6101. 

1 2503 1036 195 . 5640. 

1 e 2643 e 0971 205. 5991. 

1 .2630 s 0961 196. 5816. 

1 .2644 1034 220. 6035. 

Mean= 5789. 

S.D. = 356. 

3 .2622 .0961 201. 5983. 

3 2583 .0929 206. 6439. 

3 .2607 0828 164. 5698. 

3 .2533 .lo19 209. 6073. 

3 .2641 .0893 186. 5915. 

3 .2695 .0812 164. 5621. 

Mean= 5955. 

S.D. = 293. 

5 .2602 e 0900 179. 5733. 

5 2602 .0927 194. 6032. 

5 2602 .0968 206. 6134. 

5 .2593 .0971 208. 6196. 

5 .26U 0971 209. 6180. 

5 .26U .lo22 217. 6097. 

Mean= 6062. 

S.D. = 172. 

35 
I 

Width 

in. 

.2587 

.2674 

.2570 

.2647 

1 

1521 I 1 

RLickness 

in. 

.0907 

.0996 

.lo18 

.0931 

153 I 1 

.0850 

.0922 

.0923 

.0910 

.lo50 

.0901 

.0914 

.lo21 

.0970 

.0968 

.0923 

,1040 

1 

155 I 1 

162. 5820. 

186. 5793. 

191. 6335. 

184. 5833. 

217. 5853. 

184. 5813. 

Mean= 5908. 

S.D. = 210. 

180. 5610. 

194. 5517. 

193. 5718. 

178. 5258. 

183. 5671. 

190. 5194. 

Mean= 5495. 

S.D. = 220. 

TABLE X. - CONCLUDED 

(e) exposed at Ft. Greely,AK 

149 

I 

139 

140 

14 1 

142 

5 

5 

5 

5 

Mean= 

S.D. = 

5626. 

5829. 

5504. 

5387. 

5823. 

5223. 

5565. 

242. 

2456 

.2612 

.2450 

.2600 

.2648 

.2635 

.2633 

.2583 

.2610 

.2623 

.2622 

.2638 

36 
(a) exposed at Cameron, LA 

, 82. 3463. 

85. 3428. 

79. 3246. 

81. 3215. 

87. 3598. 

83. 3354. 

Mean= 3384. 

S.D. = 143. 

7B 

8B 

9B 

10B 

1lB 

12B 

Width 

37B 1 .2479 

38B 1 2559 

39B 1 .2414 

40B 1 .2427 

41B 1 .2470 

42B 1 .2339 

Number 

43B 3 2247 

44B 3 .2434 

45B 3 .2417 

46B 3 .2445 

47B 3 .2419 

48B 3 2514 

13B 

14B 

15B 

16B 

17B 

18B 

r 

Thickness Uad Failure 

.0784 90. 3473. 

.0770 95. 3616. 

.0810 87. 3337. 

.0778 85 3376. 

.0774 90. 3531. 

.0768 88. 3674. 

Mean= 3501. 

S.D. = 132. 

.0807 80. 3309. 

0773 91. 3627. 

0762 86. 3482. 

.0779 89. 3505. . 0784 83. 3282. 

.0780 97. 3691. 

Mean= 3483. 

S.D. = 164. 

in. Ibf. Stress,psi 

Width 

in. 

.2419 

.2327 

.2476 

.2309 

.2285 

.2607 

.2277 

.2352 

.2473 

.2325 

.2367 

2409 

Thickness 

in. 

.0779 

.0776 

.0774 

.0775 

0780 

e 0784 

Load 

lbf. 

~~~ 

95. 

83. 

92. 

85. 

85. 

98. 

Failure 

Stress,psi 

3781. 

3447. 

3600. 

3562. t 3559. 

3615. 

109. 3594. I S.D. = 

.0780 

,0772 

.0776 

.0764 

.0780 

.0784 

(b.) exposed in the Gulf of Mexico 

37 
Nulnber 

67B 

68B 

69B 

70B 

71B 

72B 

73B 

74B 

75B 

76B 

77B 

78B 

79B 

80B 

81B 

82B 

83B 

84B 

38 

Width Thickness lhd Failure 

T=t yr in. lbf. Stress,psi 

1 .2313 .0782 90. 3732. 

1 .2429 0784 96 c 3781. 

1 s 2583 .0778 103. 3844. 

1 .2358 0795 90. 3601. 

1 .2468 .0789 97. 3736. 

1 .2278 .0780 91. 3841. 

Mean= 3756. 

S.D. = 90. 

3 ,2402 .0782 86. 3434. 

3 .2396 .0800 93. 3639. 

3 .2470 .0774 89. 3492. 

3 .2352 .0795 86. 3449. 

3 .2550 .0780 95. 3582. 

3 .2410 .0770 85. 3435. 

Mean= 3505. 

S.D. = 86. 

5 .2288 .0796 81. 3336. 

5 .2429 .0788 88. 3448. 

5 .2528 .0773 94. 3608. 

5 .2390 .0785 86. 3438. 

5 .2310 .0784 88. 3644. 

5 .2398 .0790 88. 3484. 

Mean= 3493. 

S.D. = 115. 

-in=nEw== 

- 
!mBLExI. -a3NTmmD 

(d) expo6ed at Tbmto, Canada 

Number 

97B 

98B 

99B 

lOOB 

l0lB 

102B 

103B 

104B 

105B 

106B 

107B 

108B . 

109B 

llOB 

lllB 

112B 

113B 

114B 

Width T1.lid)mess Lroad ' Failure 

T=,Yr in. Ibf. Stress,psi 

1 ,2484 .0790 100. 3822. 

1 .2398 .0779 90. 3613 

1 2279 .0780 85. 3586. 

1 .2548 0787 96. 3591. 

1 .2242 .0782 85. 3636. 

1 .2461 .0769 94. 3725. 

Mean= 3662. 

S.D. = 93 

3 2508 .0788 89. 3378. 

3 .2273 .0804 84. 3447. 

3 .2291 ,0787 87. 3619. 

3 .2456 .0828 95. 3504. 

3 .2488 .0776 93. 3613. 

3 2453 .0770 86. 3415. 

Mean= 3496. 

S.D. = 102 

5 .2437 .0793 96. 3726. 

5 .2373 .0790 89. 3561. 

5 .2393 .0792 97. 3839. 

5 2303 .0802 85. 3452. 

5 -2439 .0780 101. 3982. 

5 2300 .0784 93. 3868. 

Mean= 3738. 

S.D. = 200. 

--%==e in. 

39 
(e) exposed at Ft. Greely,~~ 

spec* Expo== Number T=,yr 

15lB 1 

152B 1 

153B 1 

154B 1 

l55B 1 

156B 1 

145B 3 

146B 3 

147B 3 

148B 3 

149B 3 

150B 3 

139B 5 

14 OB 5 

14lB 5 

142B 5 

143B 5 

144B 5 

Width ' lWkkness Load Failure 

.2411 .0778 84. 3359. 

.2580 .0780 95. 3541. 

.2338 .0766 78. 3266. 

.2452 .0779 88. 3455. 

.2492 .0798 86. 3243. 

.2454 .0776 89. 3505. 

Mean= 3395. 

S.D. = 125. 

,2343 .0777 93. 3811. 

2446 .0788 100. 3891. 

.2473 .0784 86. 3327. 

.2333 .0786 94. 3824. 

.2233 .0772 a7. 3785. 

.2373 .0772 89. 3623. 

Mean= 3710. 

S.D. = 208. 

.2342 .0784 82. 3349. 

.2372 .0762 78. 3237. 

.2576 .0773 93. 3484. 

.2515 .0770 86. 3331. 

.2322 .0779 83. 3421. 

,2473 .0761 87. 3467. 

Mean= 3381. 

S.D. = 94. 

in. in. lbf. Stress,psi 

. I 

. 

40 
TABU3 XI. - SFERT BEAM SHEAR S"GTH OF T-3OO/E-788 

AFTER-ALEXFOSURE 

277. 

268. 

303. 

287. 

295. 

258. 

SpeciFaen Numbe!r 

7v 

8v 

9v 

1OV 

11v 

12v 

11418. 

10728. 

12171. 

11462. 

11830. 

10314. 

13V 

14V 

1RI 

16V 

17v 

18V 

.- + 

sPec*'wPo== Width ?hickness Load Failure 

Number Ti-=,yr in. in. Ibf. Stress,psi 

37v 1 .2563 .0720 270. 10973. 

38V 1 e 2564 .0724 286. 11555. 

39v 1 .2576 .0726 302. 12111. 

40V 1 .2579 0727 298. 11920. 

41V 1 .2572 .0701 281. 11689. 

42V 1 .2571 .0723 258. 10410. 

Mean = 11443. 

S.D. = 638. 

43v 3 .2570 .0715 289. 11796. 

44v 3 .2560 .0719 280. 11409. 

45v 3 .2569 .0720 289. 11718. 

46v 3 2567 .0710 286. 11769. 

47v 3 2563 .0722 295. 11956. 

4av 3 .2554 .0718 274. 11206. 

Mean = 11642. 

S.D. = 279. b L 

(a) exposed at -n, LA 

width 

in. 

.2570 

.2570 

. 2579 

.2562 

. 2569 

. 2570 

mcluless 

in. 

.0708 

.0729 

.0724 

.0733 

.0728 

.0730 1 

Mean = 11320. I S.D. = 689. 

.2569 

.2565 

.2571 

.2565 

.2573 

.2562 

.0731 

,0726 

.0714 

.0732 

.0730 

0721 

284. 

284. 

293. 

254. 

303. 

279. 

11342. 

11438. 

11971. 

10146. 

12099. 

11328. 1 

Mean = 11387. 

S.D. = 692. 

(b.) exposed in the Gulf of Mexico 

41 
TABLE XII. - 

.0733 

.0709 

.0729 

.0710 

.0731 

.0725 

-- 

Specimen 

Number 

67V 

68V 

69V 

70V 

71V 

72V 

73v 

74v 

75v 

76v 

77v 

78V 

79v 

80V 

81V 

82V 

83V 

84V 

1 Mean = 11686. 

S.D. = 505. 

281. 11218. 

299. 12336. 

316. 12577. 

284. 11646. 

282. 11284. 

256. 10313. 

lvbm = 11562. 

S.D. = 824. 

1 1 

Width 

in. 

.2555 

.2562 

.2558 

.2576 

.2535 

.2563 

.2569 

.2569 

.2570 

.2558 

.2570 

.2562 

.2563 

.2564 

.2585 

.2576 

.2564 

.2568 

Thickness 

in. 

.0730 

.0713 

.0725 

.0726 

.0726 

.0730 

.0728 

.0728 

.0731 

.0735 

.0723 

.0726 

Icad 

lbf. 

281. 

265. 

282. 

280. 

301. 

284. 

Failure 

Stress psi 

11299. 

10880. 

11412. 

11229. 

12266. 

11384. 

l4fa.n = 11412. 

S.D. = 460. 

271. 

294. 

295. 

311. 

284. 

293. 

10868. 

11790. 

11777. 

12406. 

11463. 

11814. 

42 
97V 

98V 

99v 

l0ov 

l0lV 

102v 

3 

3 

3 

3 

3 

3 

103V 

104V 

105v 

106v 

107v 

108V 

.2575 .0725 300. 12052. 

.2562 .0728 263. 10576. 

.2580 .0723 308. 12384. 

.2562 .0705 291. 12083. 

.2567 .0725 302. 12170. 

.2535 .0729 309. 12540. 

Mean = 11968. 

S.D. = 707. 

109v 

llov 

l1lV 

112v 

113V 

114V 

.0732 

.0733 

0765 

.0725 

.0724 

.0740 

TABLEXII. -0oNmMJED 

(d) exposed at Toronto, Canada 

309. 

296. 

258. 

290. 

306. 

302. 

~ 

.2563 

.2571 

.2566 

.2579 

.2562 

.2570 

.0725 

.0714 

.0728 

.0727 

.0734 

.0723 

~~ 

260. 

292. 

275. 

285. 

305. 

260. 

10494. 

11930. 

11041. 

11400. 

12164. 

10495. 

Mean = 11254. I I I S.D. = 708. 

.2563 

.2580 

.2572 

.2564 

.2563 

5 .2573 

12353. 

11739. 

9834. 

11700. 

12368. 

11896. 1 

Mean = 11648. 

S.D. = 936. 

43 
TWIE XII. - CONCUTDED 

251. 

264. 

304. 

273. 

275. 

271. 

(e) exposed at Ft. Gree1yJ.K 

10254. 

10601. 

12321. 

10963. 

11100. 

10966. 

151V 

152V 

153V 

154V 

155V 

156V 

145V 

14 6V 

147V 

148V 

149V 

150V 

139V 

14OV 

14 1V 

142V 

143V 

144V 

Width 

in. 

.2564 

.2564 

.2570 

.2569 

.2563 

2570 

.2557 

.2569 

.2563 

.2569 

.2560 

2570 

.2563 

.2569 

.2570 

.2583 

.2566 

2559 

.0731 

.0712 

.0712 

.0726 

.0722 

.0727 

.0718 

.0727 

.0722 

.0727 

.0723 

.0724 

10604. I 9;;: I 11149. I 268. I 11010. 

271. 10893. I 255. I 10311. I 275. I 11069. 

Mean = 10839. 

S.D. = 321. I 

.0736 

.0718 

.0712 

.0722 

.0730 

.0722 

I 265. 1 10536. 

265. 10775. I 251. I 10332. 

10428. 

10700. 

11861. 

Mean = 10772. 

S.D. = 1 

44 
u)* I 

c I 

a I 

al I 

E 

m 

ar 

mc: 

** 

m 

al 

E 

- 

c 

4J 

F 

c 

al 

k 

4J 

VI 

rl 

I 

5 

a 

-4 

al tx 

- 

I z. ... I I*NO 

I I\oPN 

I ImdN 

... I lmod 

I Idom 

I Id(v 

... 

OdO 

I o*m 

I moo 

I lolnu) 

I 

... 

Ocod 

I Imma) 

IIWr-Fl 

I lmmm 

II 

5 

4J 

VI 

k 

F 

c 

al 

hl 

I 

I 

k 

m 

al 

a 

d 

al 

4J 

k 

0 

m 

3 

ccc 

0 

h 

k 

1 i 

VI 

I 

H 

H 

H 

X 

al 

r-4 

A 

nl 

E-c 

..... 

cnc0Oa)d 

com\oocu 

I 

\oIow'pIm 

I--" 

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d 

co In 

N 

ta\ 

d 

m 

d 

d 

al 

c 

d 

crI I ----+-- 

a) 

d 

0 

\o 

m 

Q) 

rm 

I 

I" 

oa 

x c- 

-2 ? 5 

c 

0 

-4 

+J 

a 

u 

s 

13 c 

m 

>.a, 

Oa) 

mtcr 

4 

k 

al 

m 

II E-cw I* I 

45 
F Material 

.0700 

.0696 

.0702 

.0705 

Graphite/ 

- 

Mean = 83658. 

S.D. = 2198. 

9210. 131152. 

8710. 124769. 

8580. 121650. 

9180. 129051. 

157F 

158F 

159F 

160F 

16lF 

162F 

160 

161 

162 

163 

164 

165 

157B 

158B 

159B 

160B 

16lB 

162B 

325V 

326V 

327V 

328V 

329V 

330V 

width 

in. 

.9868 

.9752 

.9827 

.9952 

.9960 

.9895 

L .0075 

L. 0070 

L. 0046 

L .0058 

.9966 

L. 0053 

~ ~~ 

.9857 

.9842 

.9710 

1.0002 

.9955 

9728 

. .0032 

-. 0030 

-. 0047 

. .0090 

. .0048 

. 0057 

Thickness 

in. 

.0969 

.0897 

.0967 

.0979 

.0994 

.0966 

.lo63 

.lo42 

.lo42 

.lo45 

.0969 

.lo04 

r 

Maximum 

~ E. 

1 5520. 

6120. 

5790. 

5790. 

6125. 

, 5460. 

Failure 

Stress 

- Psi 

57728. 

62418. 

64403. 

59427. 

58483. 

64079. 

1 Mean S.D. = 61090* 2917. ~~ 

6020. 

5890. 

5870. 

6080. 

6000. 

5630. 

56211. 

56133. 

56076. 

57846. 

62131. 

55780. 

.0865 7100. 

.0884 7150. 

.0868 7140. 

.0868 6970. 

.0863 7320. 

.0872 7320. 

83272. 

82181. 

84715. 

80283. 

85204. 

86292. 

.0684 130223. 

.0722 I 8950*860. I 122019. 

S.D. = Standard Deviation 

46 
(a) exposed at Cameron, LA 

Width 

in. 

.9971 

.997a 

.9812 

.9800 

1.0027 

.9970 

.9952 

.9994 

.9963 

.9944 

.9963 

,9948 

193F 

194F 

195F 

196F 

197F 

198F 

Thicloless Load Failure 

in. Ibf. Stress,psi 

.0975 5890. 60586. 

.0995 6160 62046. 

.0988 6090. 62821. 

.0974 5800. 60764. 

0966 5760. 59467. 

.0974 6080. 62611. 

Mean = 61382. 

S.D. = 1319. 

.0966 5950. 61891. 

.0976 5650. 57924. 

.0909 5700. 62939. 

.0998 6000. 60459. 

.0985 6000. 61140. 

,0962 6150. 64263. 

Mean = 61436. 

S.D. = 2183. 

I 

- 

199F 

200F 

201F 

202F 

203F 

204F 

S.D. = 

.9756 

.9915 

.9949 

.9937 

.9901 

.gag6 

.0894 

.0982 

.0972 

.0958 

0980 

.loo1 

5080. 

5900. 

6030. 

5780. 

6030. 

6260. 

1724. I 

58244. 

60597. 

62355. 

60968. 

61921. 

63163. 

.9932 .0969 

.9807 .0922 

.9943 .0980 

1.0020 .0930 -I- 9968 .0973 

9864 .0973 

5425. 

5820. 

5780. 

5800. 

5690. 

(b.) exposed in the Gulf of Mexico 

itandard dev 

61876. 

59997. 

59728. 

62026. 

59801. 

59285. 

1185. 1 

I I 

47 
223F 

2241" 

225F 

226F 

227F 

228F 

229F 

230F 

231F 

232F 

233F 

234F 

235F 

236F 

237F 

238F 

239F 

240F 

Tb,yr 

.9934 

.9461 

.9750 

.9848 

.9848 

.9828 

.9833 

3 

3 

3 

3 

.9771 

.9850 

.9798 

.9863 

.9973 

1.0102 

.9854 

.9980 

.9958 

.9801 

.0987 

.0979 

.0988 

.0962 

.0973 

.0978 

6350. 

5760. 

6080. 

6150. 

6240. 

6060. 

64764. 

62187. 

63116. 

64916. 

65121. 

63048. 

1 Mean = 63859. 

S.D. = 1227. I 

.0982 

.0969 

.0964 

.0970 

.0961 

.0994 

6170. 

6080. 

6010. 

6150. 

5960. 

6150. 

' 63440. 

63811. 

63806. 

64368. 

63297. 

62731. 

S.D. = 556. 

.0977 

.0971 

.0974 

.0923 

.0915 

.0982 

6055. 

6200. 

5700. 

5830. 

5525. 

5900. 

62143. 

63207. 

59389. 

63290. 

60637. 

61301. 

S.D. = 1524. I 

48 
TABU3 IN. - 

(a) aposed at Wmnto, Canada 

3pecimen Width 

Mnnber 

?hichess Load Failure 

in. lbf. Stress,psi 

253F 

254F 

255F 

2563 

257F 

258F 

259F 

260F 

261F 

262F 

263F 

2 64F 

265F 

266F 

267F 

268F 

269F 

1 .9857 .0975 

1 .9960 0965 

1 .9865 .0978 

1 .9870 .0989 

1 .9844 .0970 

1 .9892 .0967 

3 .9964 .0963 

3 .9970 .0950 

3 .9929 .0982 

3 ,9877 .0973 

3 .9903 .loo0 

3 .9852 .0991 

.9828 

.9941 

.9945 

.9833 

.9931 

.9919 

6000. 

6300. 

6000. 

6100. 

6250. 

6000. 

62431. 

65547. 

62189. 

62491. 

65454. 

62725. 

Mean = 63473. 

S.D. = 1580. 

6290. 

6050. 

6100. 

6200. 

6150. 

6250. I 

Mean= 

S.D. = 

65553. 

62562. 

64514. 

62102. 

64015. 

63770. 

1268. 

63876. 

.0944 

.0967 

.0981 

.0974 

.0995 

,0982 

5600. I 

5925. 6150* I 

6080. 

5990. 

6200. 

Mean= 

S.D. = 

60360. 

63976. 

60732. 

63483. 

60619. 

63652. 

- 

62137. 

1728. 

49 
;pecimen 

Number 

.0903 

.0983 

.0962 

.0992 

.0992 

.0972 

.0997 

.0982 

.0937 

.0942 

.0984 

.0974 

307F 

308F 

3 09F 

3 10F 

31lF 

312F 

Mean = 62688. 

S.D. = 1408. 

5750. 64385. 

6300. 64528. 

6110. 63974. 

6060. 61501. 

6010. 60907. 

6050. 62455. 

Mean = 62958. 

S.D. = 1557. 

5920. 59611. 

6050. 61517. 

5300. 57239. 

5500. 59354. 

6080. 61820. 

6300. 65467. 

301F 

302F 

303F 

304F 

305F 

306F 

295F 

296F 

297F 

298F 

299F 

300F 

TABU3 XV. -CONCLUDED 

exposed at Ft. Greely, AK 

1 

1 

1 

1 

1 

1 

3 

3 

3 

3 

3 

3 

Width 

in. 

.9941 

.9905 

9926 

.9795 

1.0008 

.9931 

.9890 

.9932 

.9928 

.9933 

9947 

.9966 

.9961 

1.0015 

.9882 

.9837 

.9995 

.9880 

!i?hickness 

in. 

.0895 

.0961 

.0978 

.0901 

.0989 

.0978 

Imd 

lbf. 

5580. 

5870. 

6090. 

5720. 

6280. 

5900. 

Failure 

Stress,psi 

61668. 

62734. 

64814. 

63448. 

60746. 

Mean = 60834. 

S.D. = 2811. 1 

I 

50 
TABLE XVI. - TENSION SEE" OF KEVLAF+49/F-185 

AFTER-ExpasuRE 

(a) exposed at Qmeron, LA 

md 

lbf. 

6080. 

6000. 

5940. 

6010. 

5850. 

5825. 

56534. 

59250. 

58196. 

56910. 

60731. 

59671. 

169 

170 

17 1 

P 

172 

173 

174 

175 

17 6 

177 

1 

1 

1 

3 

3 

3 

3 

3 

3 

1.0041 

1.0047 

1.0040 

1.0043 

.9971 

.9924 

.lo40 

.0967 

,1032 

.loo0 

.0947 

.0993 

Width 

in. Stress,psi Failure I Thickness 

in. 

.lo73 

.lo20 

.lo14 

.lo51 

.0960 

.0967 

1.0023 

.9928 

1.0066 

1.0048 

1.0034 

1.0095 

166 1 

1 

5860. 

5900. 

5830. 

6030. 

5750. 

6025. 

56116. 

60728. 

56267. 

60042. 

60895. 

61139. 

Mean = 59198. 

S.D. = 2357. 1 1 I 

(b.) exposed in the Gulf of Mexico 

Width 

in. 

196 

197 

198 

199 

200 

201 

~ --~ 

1.0013 

1.0063 

9859 

1.0040 

.9983 

1 0034 

.lo58 

.lo29 

.0978 

.lo42 

.lo85 

.lo29 

6240. 

6030. 

5840. 

5950. 

5880. 

6000. 

58903. 

58234. 

60568. 

56874. 

54286. 

58111. 

1 

1 

1 

1 

1 

1 

3 

3 

3 

3 

3 

3 

~- ~ 

57829. 

2115. 

60760. 

61238. 

58577. 

56586. 

59535. 

58665. 

S.D. = 

202 .0932 5630. 

203 

204 

205 

206 

207 

9942 

1.0079 

1.0049 

1.0027 

1.0011 

a 9942 

.0964 

.lo21 

.lo24 

.loo0 

.0991 

5950. 

6010. 

5810. 

5960. 

5780. 

S.D. = 1686. I - = 59227. 

51 I 
WXVI. -- 

(c) exposed at Hampton, VA 

238 

239 

240 

241 

242 

243 

- 

226 

227 

228 

229 

230 

231 

5 1.0030 

5 1.0050 

5 1.0055 

5 1.0020 

5 1.0070 

5 1.0025 

Width 

1.0040 

.9999 

1.0041 

1.0000 i .9998 

1.0003 

232 

233 

234 

235 

236 

237 

1.0006 

,9998 

1.0000 

1.0007 

1.0050 

1.0020 

I I 

Thic3mesS 

in. 

.0946 

.lo03 

.loo0 

.lo04 

.loo1 

.lo06 

.lo08 

.lo22 

.0999 

.lo03 

.loo1 

.lo06 

.0992 

.lo08 

.loo0 

0997 

.0899 

.0992 

6190. 

6060. 

6020. 

5810. 

5730. 

6000. 

~~ 

65173. 

60425. 

59954. 

57869. 

57254. 

59624. 

Mean= 

S.D. = 

6180. 

6100. 

5990. 

5990. 

6240. 

~ 

60050. 

2798. 

61967. 

60482. 

61061. 

59679. 

59542. 

61904. 

1057. 

Mean= 

S.D. = 

6100. 

6025. 

5930. 

6000. 

5500. 

5880. 

Mean= 

S.D. = 

61308. 

59474. 

58976. 

60060. 

60754. 

59126. 

59950. 

933. 

52 
(d) exposed at Toronto, Canada 

r v 

Width Mckness LDad Failure 

Number T=,w in. lbf. Stress,psi -i=n ExPure in. 

1 

256 1 1.0000 .lo05 6100. 60697. 

257 1 1.0000 1004 6150. 61255. 

258 1 1.0040 .lo05 6250. 61941. 

259 1 1.0040 .0999 5950. 59322. 

260 1 1.0035 0 0999 5950. 59352. 

261 1 1.0000 .lo03 5500. 54835. 

Mean = 59567. 

S.D. = 2540. 

262 3 1.0035 .0998 6250. 62407. 

263 3 1.0000 .lo05 6020. 59900. 

264 3 1.0010 .lo04 6090. 60597. 

265 3 1.0040 .loo0 5850. 58267. 

266 3 1.0055 .lo05 6050. 59870. 

267 3 1.0080 .0998 6080. 60438. 

Mean = 60247. 

S.D. = 1342. 

268 5 1.0015 .loo0 6075. 60659. 

269 5 .9998 .0991 5900. 59548. 

270 5 1.0011 .lo03 5800. 57763. 

271 5 1.0035 .lo04 6125. 60793. 

272 5 1 0055 .lo04 5890. 58344. 

273 5 1.0040 .0989 5975. 60174. 

Mean = 59547. 

S.D. = 1250. 1 -.. 

53 
TABLE XVI. - CONCLUDED 

(e) expcsed at Ft. Greely,AK 

~~ 

Ibad Failure 

Ibf. Stress,psi 

6050. 60247. 

4880. 48635. 

6120. 60986. 

6220. 61983. 

6150. 61414. 

6075. 60382. 

Mean = 58941. 

S.D. = 5090. 

r 

3 10 

3 11 

3 12 

313 

314 

1.0002 

1.0000 

1.0007 

1.0002 

1.0003 

1.0001 

304 

305 

306 

307 

I 

Mean = 60062. 

S.D. = 1309. 

.lo07 6190. 61457. 

.loo1 6060. 60539. 

.lo08 6055. 60027. 

.0998 6120. 61310. 

.lo05 6155. 61225. 

.loo1 5990. 59834. 

Mean = 60732. 

S.D. = 699. 

3 00 

302 5 

Width 

in. 

1.0002 

1.0004 

1.0005 

1.0005 

1.0004 

1.0001 

micknesS 

in. 

.lo04 

.lo03 

.lo03 

,1003 

.loo1 

.lo06 

1.0003 

1.0002 

1.0000 

1.0007 

1.0000 

1.0001 

.lo08 

.0997 

.0994 

.lo04 

.lo04 

,1005 

6080. 

5790. 

5850. 

6150. 

6140. 

6110. 

60299. 

58063. 

58853. 

61212. 

61155. 

60790. 

54 
TABLE XVII. - TENSION STRE" OF KEvlAR-49/LRF-277 

AFTERm-- 

Mrmber 

193B 

194B 

195B 

19 6B 

197B 

198B 

199B 

200B 

201B 

202B 

203B 

204B 

(a) exposed at Cameron, LA 

t 

width Thickness md ' Failure 

T=,yr in. lbf. Stress,psi --ExF-- in. 

1 9948 .0880 7360. 84074. 

1 1.0094 .0882 6290. 70651. 

1 .9980 .0881 8025. 91272. 

1 .9808 .0894 7580. 86447. 

1 9791 .0869 7410. 87091. 

1 1.0024 .0885 6990. 78794. 

Mean = 83055. 

S.D. = 7326. 

3 .9813 .0853 7020. 83866. 

3 .9926 .0879 7600. 87106. 

3 .9967 .0882 7790. 88614. 

3 1.0046 .0856 7000. 81401. 

3 ,9838 .0875 7790. 90495. 

3 1.0119 .0865 7250. 82829. 

Mean = 85719. 

S.D. = 3565. 

166B 

1678 

168B 

169B 

170B 

17lB 

172B 

173B 

174B 

1 

1 

1 

.9813 

1.0060 

9813 

.9925 r .9905 

.9829 

9792 

.9902 

9965 

1.0052 

.9820 

.9678 

.0887 

.0873 

0874 

.0870 

.0855 

.0859 

7780. 

7210. 

7650. 

6910. 

7480. 

7600. 

89383. 

82096. 

89197. 

80025. 

88324. 

90014. 1- 4303. 

.0870 7320. 

.0886 7450. 

.0857 7740. 

.0874 7760. 

.0883 7590. 

.0864 7090. 

85925. 

84918. 

90632. 

88328. 

87533. 

84790. 

(b.) exposed in the Gulf of Mexico 

1 1 1 I .. 

55 
223B 

224B 

225B 

226B 

227B 

228B 

Expure 

T-,yr 

229B 

230B 

23l.B 

232B 

233B 

234B 

Width Thichess Imd Failure 

in. in. Ibf. Stress,psi 

235B 

236B 

237B 

238B 

239B 

240B 

1 

1 

1 

1 

1 

1 

.9892 .0891 

.9841 .0922 

.9875 .0874 

1.0011 .0864 

.9935 .0880 

1.0054 0 0847 

, 7810. 

7850. 

6950. 

7260. 

7300. 

6870. 

3 

3 

3 

3 

3 

3 

88611. 

86517. 

80526. 

85254. 

84398. 

78579. 

.9810 .0883 

.9776 .0892 

.9803 .0872 

.9834 .0895 

.9907 .0867 

.9938 .0866 

ll 3763. 

7820. 

6630. 

7700. 

7390. 

7980. 

7150. 

90277. 

76030. 

90077. 

83964. 

92906. 

83079. 

II 6240. 

.9740 

.9898 

.9798 

.9866 

9992 

.9942 

0868 

.0868 

.0871 

.0871 

,0875 

0861 

7520. 

7700. 

7260. 

7600. 

7975. 

7490. 

88949. 

89624. 

85071. 

88441. 

91216. 

87499. 

56 
I 

7500. 

7650. 

7700. 

7600. 

7100. 

7500. 

TABLE XVII. - OONTINUED 

86145. 

87176. 

88831. 

86737. 

83161. 

88530. 

(d) expc6ed at Toronto, Canada 

3 

I 3 

3 

3 

3 

3 

I 

253B 

254B 

255B 

256B 

257B 

258B 

7800. 

7300. 

7675. 

7730. 

7190. 

8080. 

259B 

260B 

26lB 

262B 

263B 

264B 

88820. 

85727. 

87388. 

89542. 

82924. 

90844. 

265B 

266B 

267B 

268B 

269B 

270B 

Width 

in. 

.9871 

9952 

9812 

9972 

9916 

9682 

9823 

9833 

.9835 

.9900 

9853 

.9949 

.9866 

1.0022 

.9843 

.9730 

.9785 

.9793 

0882 

-0880 

.0871 

.0893 

0861 

0875 

0894 

0866 

0893 

.0872 

.0880 

.0894 

.0857 

.0862 

.0885 

.0853 

.0873 

.0879 

6930. 

7110. 

7575. 

7110. 

7490. 

7395. 

81962. 

82302. 

86958. 

85666. 

87681. 

85908. 

I S.D. = 85079* 2399. 

57 
4 

TABLE XVII. - CONCLUDED 

(e) exposed at Ft. Greely,AK 

b 

specimen 

Number 

307B 

308B 

309B 

310B 

311B 

312B 

301B 

302B 

303B 

304B 

305B 

306B 

295B 

296B 

297B 

298B 

299B 

300B 

.9862 

1.0124 

.9880 

.9922 

.9968 

.9762 

7650. 

7340. 

7610. 

7060. 

7560. 

6290. 

.0867 

0851 

.0901 

.0887 

.0873 

.0887 

88021. 

84223. 

88406. 

78993. 

85760. 

76199. 

6450. 

7570. 

8020. 

7830. 

7750. 

7070. 

.0885 

.0882 

.0885 

.0870 

.0867 

.0893 

75435. 

87865. 

90093. 

88969. 

89059. 

81650. 

I J 

Eaean = 83600. 

S.D. = 4974. 

7830. 91541. 

8015. 90828. 

7480. 85877. 

7850. 91123. 

7450. 87308. 

7660. 86689. 

Mean = 88894. 

S.D. = 2538. 

1-1 5788. 

.9910 .0877 

.9960 .0875 

.9940 .0866 

.9986 ,0895 

.9916 .0889 

.9700 .0851 

.9665 

1.0005 

.9842 

.9902 

.9842 

.9895 

58 
TABLE XVIII. - TENSION OF T-300/E-788 

AFTER-ALExposuRE 

9080. 129232. 

8130. 113911. 

9300. 134810. 

8540. 118318. 

8980. 125070. 

8410. 117177. 

Mean = 123086. 

S.D. = 8012. 

9660. 131993. 

8420. 117246. 

9250. 129345. 

9390. 135686. 

9400. 132377. 

8650. 118832. 

Mean = 127580. 

S.D. = 7676. 

b 

IA 

Width 

in. 

Load 

lbf. 

lhiclrness 

in. 

.0710 

.0703 

.0726 

.0742 

.0708 

.0718 

Stress,psi 

' 119782. 

126613. 

123854. 

125959. 

119241. 

121182. 

331V 

332V 

333V 

334V 

335v 

336v 

1.0030 

.9999 

.9998 

1.0079 

1.0021 

.9999 

8530. 

8900. 

8990. 

9420. 

8460. 

8700. 

Mean= 

S.D. = 

122772. 

3163. 

337v 

338V 

339V 

340V 

341V 

342V 

.9998 

1.0048 

1.0095 

1.0058 

1.0039 

.9997 

.0716 

.0712 

.0702 

.0707 

.0705 

.0680 

9380. 

8230. 

9770. 

9610. 

8440. 

8660. 

131032. 

115038. 

137864. 

135143. 

119251. 

127391. 

Mean = 127620. 

S.D. = 8962. 

(b.) exposed in the Gulf of Mexico 

specNumber ~~~ 

1.0023 

1.0010 

.9998 

.9997 

1.0000 

1.0010 

.0701 

,0713 

.0690 

.0722 

.0718 

.0717 

361V 

362V 

363V 

364V 

365V 

3 66V 

367V 

368V 

369V 

370V 

371V 

372V 

1.0053 

1.0030 

1.0030 

1.0015 

1.0058 

1.0068 

.0728 

.0716 

.0713 

,0691 

.0706 

.0723 

59 
391V 

392V 

393v 

394v 

395v 

396v 

Width 

in. 

1.0010 

1.0037 

1.0018 

1.0080 

1.0016 

1.0010 

39% 

398V 

399v 

40OV 

401V 

4 02V 

Thickness Load Failure 

in. Ibf. Stress,psi 

.0691 9090. 131417. 

.0699 8840. 126000. 

.0723 8840. 122049. 

.0697 9150. 130235. 

.0709 9060. 127581. 

.0707 9220. 130280. 

Mean = 127927. 

S.D. = 3505. 1 

4 03V 

404V 

405v 

406V 

407V 

408V 

I 

.0726 

.0703 

.0714 

.0692 

.0705 

.0703 

.0714 

.0724 

.0713 

8650. 119218. 

9270. 131877. 

8660. 120769. 

9600. 138451. 

8810. 124219. 

9490. 135101. 

Mean = 128272. 

S.D. = 7974. 

9550. 133420. 

9230. 126814. 

9650. 135520. 

.9994 

.9999 

1.0043 

1.0020 

1.0060 

.9992 

1.0025 

1.0053 

,9987 

1 1.0033 ,0694 

1.0042 I .0711 

60 
TABLE XVIII. - a3lmmnm 

427V 

428V 

429V 

43w 

431V 

432V 

(d) exposed at Toronto, canada 

3 .9990 .0687 9420. 137255. 

3 1.0065 0727 9490. 129693. 

3 1.0000 .0719 9560. 132962. 

3 1.0060 .0716 9140. 126892. 

3 1.0070 .0693 8640. 123809. 

3 1.0018 .0722 8730. 120697. 

Mean = 128551. 

S.D. = 6057. 

421V 

422V 

423V 

424V 

425V 

426V 

433v 

434v 

43w 

436V 

437V 

438V 

.9995 

1.0062 

1.0000 

.9999 

1.0045 

,9992 

5 

5 

5 

5 

5 

5 

.0689 

.0695 

.0707 

.0692 

.0697 

0692 

9550. 

9450. 

9775. 

9725. 

9570. 

8850. 

138676. 

135133. 

138260. 

140549. 

136688. 

127993. r I 

Mean = 136216. 

S.D. = 4428. 

I 1 

1.0072 

1.0070 

1.0040 

1.0061 

1.0043 

1.0080 

.0719 

,0690 

.0706 

.0703 

.0702 

.0722 

8525. 

8840. 

8525. 

8980. 

117720. 

126964. 

8710. 123543. I 9100. I 125038. 

Mean = 123460. I 

I I I I 

61 
'TABU XVIII. - OONCWDED 

(e) exposed at Ft. Greely,AK 

;peck Number 

475v 

476v 

477v 

478V 

479v 

480V 

469V 

47w 

471V 

472V 

473v 

474v 

463'61 

464V 

465V 

466V 

467v 

468V 

Expure Width ?hidmess lbad Failure 

T-fF in. in. Ibf. Stressfpsi 

1 1.0035 .0725 8160. 112159. 

1 1.0040 .0713 9000. 125724. 

1 1.0065 .0721 10625. 146413. 

1 .9992 e 0698 7990. 114562. 

1 1.0003 .0698 9080. 130047. 

1 1.0030 .0704 9350. 132415. 

Mean = 126887. 

S.D. = 12586. 

3 ,9997 .0697 9450. 135622. 

3 1.0031 .0686 9060. 131662. 

3 1.0010 .0694 9390. 135167. 

3 .9997 .0685 9420. 137560. 

3 1.0062 .0705 9060. 127719. 

3 .9995 .0683 9560. 140041. 

---- 

Mean = 134628. 

S.D. = 4375. 

5 1.0050 .0690 9360. 134977. 

5 1.0030 .0715 9625. 134213. 

5 1.0060 .0714 9790. 136297. 

5 1.0027 .0706 9100. 128548. 

5 1.0000 0712 9780. 137360. 

5 1.0053 .0722 10580. 145765. 

Mean = 136193. 

S.D. = 5601. 

62 
c 

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al 

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cn 

c 

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0, 

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W 

0 

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2 

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X 

H 

X 

al 

d 

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'I1 

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rl I I I I 

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4J 

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Q, 

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cu 

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rl 

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m 

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eo 

04J 

4Jc 

040 

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00 

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d 

al 

al 

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c 

0 

k 

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W 

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rl 

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tl 

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om 

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-4 a 4 +diS 

- . cY.r c 0 al 

0 0 OJJ k 

k 4Jcw 

alu a0 

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VWXEb 

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v) 

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f: 

* 
TABLE XX. - WEIGHT LOSS OF Pm SPECIMENS AFTEB 

3AND5YEARsOFEXKSURE 

Ontario, Canada 

Hampton,VA 

Gulf of Mexico 

Cameron, LA 

Ft. Greely,AK 

Average 

I Kevlar-491 I Kevlar-49/ 1 Kevlar-49/ 1 T-3001 

F-185 LRF-277 CE-306 E-788 

3yr 5yr 3yr 5yr 3yr 5yr 3yr 5yr 

2.23 2.60 2.03 2.20 2.07 2.20 0.54 0.71 

2.42 2.76 1.81 2.24 1.74 2.29 0.51 0.76 

2.61 - 1.92 1.81 0.49 

2.57 - 1.96 1.95 0.51 

2.18 2.30 1.94 2.10 2.20 2.20 0.67 0.75 

2.40 2.55 1.93 2.18 1.95 2.23 0.56 0.74 

~ -- 

Ontario, Canada 

Hampton, VA 

Gulf of Mexico 

Cameron, LA 

Ft. Greely,AK 

Average 

~ ~~ 

All values are average of 6 replicates 

~~ ~ 

Kevlar-49/ Kevlar-491 Kevlar-491 T-300/ 

F-185 LRF-277 CE-306 E788 

3yr 5yr 3yr 5yr 3yr 5yr 3yr 5yr 

1.60 1.90 2.01 2.40 1.85 1.90 0.51 0.62 

1.69 2.05 2.71 2.11 1.62 1.96 0.47 0.60 

2.03 - 2.36 2.03 0.74 

1.87 2.1 1 1.97 0.50 

1.79 1.80 2.09 2.30 1.59 1.70 0.54 0.61 

1.80 1.92 2.23 2.27 1.81 1.85 0.55 0.61 

TABIE XXI. - WEIGHT I1)6s OF UNPAINTED SPECIMENS AFTER 

3AND5YEARSOFExPomJRETlME 

64 
65 
Offshore oil platform \ 

VA 

Figure 2. - Ucation of Environmental Exposure Racks 

66 
0. 

-*o 1 

075 - 0. 

4.50 i 

- I 

10 

- 00 - 0.075 - 0.10 

2.00 .6O -IF .075 - 0.10 

1.00 1-1 -11- . 05 .25 4 I+4k. 

Tension specimen Compression 

speci men 

All dimensions shown in 

050 4 k.25 

Short beam 

shear specimen 

inches 

Figure 3. - Specimen Geometry 

67 
1 LBasetine Scatter 

Band 

RESIDUAL 

STRENGTH. 6o 

percent 

STRENGTH, 6o 

percent 

baseline 

40 

20 

0 

&-Mean and Range of 6 Replicates 20 

baseline 

- 

- Mean and. Range &-of 6 Replicates 

I I I I I 

- 

012345 

EXPOSURE TIME, years 

STRENGTH, 6o 

percent 

baseline 

40 

20 

(1.) Cwn~'r ort. LA. 

Band - 

- 

Mean and Range h-af 6 Replicates - 

c.) Hampton,VA 

120r 

RESIDUAL 

STRENGTH, 6o 

Der cen t 

Mean and Range 

20 &-of 6 Replicates 

baseline 

0 L -_L- L..U 

012345 

EXPOSURE TIME,years 

b) (:itit 01 Mt.xico 

SOL I 1 LBaseline Scatter Band 

RESIDUAL 

STRENGTH, 6o 

percent 

Mean and Range 

20 &-of 6 Replicates 

baseline 

0 012345 

EXPOSURE TIME.years 

0U-L-J 

012345 

EXPOSURE TIME,yeors 

e.) Ft. Greely,Alaska 

d.) Torunto,Canada 

Figure 4 .-Residual Compressive Strength of Kevlar -49/CE-306 t poxy 

Specimens Exposed at Locations Shown 

68 
RE SI DU AL 

STRENGTH, 6o 

percent 

Mean and, Range &-of 6 Replicates 20 

--L-.-l 

012345 

EXPOSURE TIME.yeors 

baseline 

a.) Cameron, LA. 

sol- / 

RESIDUAL 

Der cen t 

&-Mean and Range of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME, years 

c.) Hampton.VA 

[Baseline Scatter 

STRENGTH, 6o Band 

RESIDUAL 

percent 

baseline 

40 

Mean and, Range 

&-of 6 Replicates 20 

012345 

EXPOSURE TIME.years 

b.) Gulf of Mexico 

RESIDUAL 

STRENGTH, 6o 

Der cen t 

Mean and. Range 

20 &-of 6 Replicates 

012345 

EXPOSURE TIME,years 

d.) Toronto.Canada 

baseline 

RESIDUAL 

STRENGTH, 6o 

percent 

c baseline 

40 2ol Mean and. Range &-of 6 Replicates 

0- 

012345 

EXPOSURE TIME, years 

e.) Ft. Greely.Alaska 

Figure 5 .-Residual Compressive Strength of Kevlar-49/F-185 Epoxy 

Specimens Exposed at Locations Shown 

69 
120r 

100 

RE SlDU AL 

STRENGTH, 6o 

percent 

L baseline 40 

Mean and Range &-of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME.years 

&-Mean and Range 

of 6 Replicates 

0, 

012345 

EXPOSURE TIME.years 

a.) Cameron, LA. b.) Gulf of Mexico 

T- 80 L asetine Scatter 

land c RESIDUAL 

STRENGTH, 6o 

percent 

c baseline 40 

Mean and Range &-of 6 Replicates 20 

baseline 

2ol &-Mean and, Range of 6 Replicates 

0, 

012345 

EXPOSURE TIME,years 

0, 

012345 

EXPOSURE TIME.years 

d.) Toronto.Canada c.) Hampton.VA 

L aseline Scatter 

STRENGTH, !and 6o 

RE SI DU AL 

percent 

baseline 

40 

Mean and Range 

of 6 Replicates 

012345 

EXPOSURE TIME, years 

e.) Ft. Greely,Alaska 

Figure 6 .-Residual Compressive Strength of Kevlar-49/LRF-277 Epoxy Specimens Exposed at Locations Shown 

70 
120 

RESIDUAL lgmsline Scatter 

percent 

baseline 

40 

Mean and Range 

4-0, 6 Replicates 20 

0- 

012345 

EXPOSURE TIME.years 

a.) Cameron, LA. 

SOL / 

RESIDUAL L aseline Scatter 

STRENGTH, Band 

per ccn t 

t baseline 40 

Mean and. Range &-of 6 Replicates 

0- 

012345 

EXPOSURE TIME.years 

c.) Hampton.VA 

------_--____ 

&xJine Scatter 

STRENGTH, 6o 

RESIDUAL 

percent 

baseline 

40 

Mean and Range &-of 6 Replicates 20 

0- 

012545 

EXPOSURE TIME.yeors 

b.) Gulf of Mexico 

RESIDUAL 

STRENGTH. 6o 

percent 

c baseline 

40 

RE SI DU AL 

STRENGTH. 6o 

percent 

c baseline 

40 

0- 

012345 

EXPOSURE TIME.years 

e.) Ft. Greely.Alaska 

Mean and. Range &-of 6 Replicates 

EXPOSURE TIME.years 

d.) Toronto.Canada 

Figure 7 .-Residual Compressive Strength of T-300 Graphite/E-788 Epoxy 

Specimens Exposed at Locations Shown 

71 
1 LBaseline Scatter 

Band 

RESIDUAL 

STRENGTH, 6o 

percent 

100 

80 

RESIDUAL 

STRENGTH, 6o 

percent 

baseline 

40 

20 

OComeron. LA 

:Gulf of Mexico 

Hompton. VA. 

Toronto. Conodo 

hFt. Greely.Alosko 20 

baseline 

--- fg ~ - - - -~ - - - - - - - - - - - - - - i T- - 

- Baseline Scatter 

Band - 

0 Comeron. LA. 

OHompton. VA. a Toronto. Canada 

bl 1. Greely.Aloska 

- 0 Gulf of Mexico 

- 

012345 

EXPOSURE TIME.years 

STRENGTH, 6o 

percent 

baseline 

40 

20 

Figure 8 .-Effect of Exposure Location on 

the Residual Compression Strength of Kevlar-49/F-l85 

- 

0 Comeron. LA. 

Hompton. VA. 

Toronto. Canada 

bFt. Greely.Alasko 

- ZGulf of Mexico 

- 

0 

012345 

A 

EXPOSURE TIME,years 

Figure 10 .-Effect of Exposure Location on 

the Residuol Compression 

Strength of Kevolr-49/CE-306 

1 L Basel in e Scatter Band RESIDUAL 

STRENGTH, 6o 

percent 

0 Comeron. LA. 

0 Gulf of Mexico 

OHampton. VA 

a Toronto. Canada 

bFt. Greely.Alosko 20 

0 L--I I-.J-_I 

012345 

EXPOSURE TIME.years 

the Residual Compression Strength of Kevlar-49/LRF-277 

Figure 9 .-Effect of Exposure Location on 

401 baseline 

0U-I 

012345 

EXPOSURE TIME.years 

Figure 11 .-Effect of Exposure Location on 

the Residual Compression 

Strength of T-300/E-788 

72 
12c 

1 oc 

8C 

RES1 DU AL 

60 STRENGTH, 

percent 

baseline 

40 

20 

0 

LBaseline - Scatter 

Band 

- 

0 Kevlar Fabric(281)/CE-306 Epoxy 

A Kevlar Fabric(l20)/LRF-277 Epoxy 

hKevlar Fabric(281)/F-l85 Epoxy 

0 T-300 Graphite/E-788 Epoxy 

---L--l 

-0 1 2 3 4 5 

EXPOSURE TIM E, year s 

Figure 1 2.-Residual Compressive Stren th of 

Composite Materials after ? xposure 

73 
RESIDUAL 

STRENGTH, 6o 

percent 

Mean and. Range &-of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME.years 

a.) Cameron, LA. 

120r 

SOL / 1 L aseline Scatter 

Band 

RE SI DU AL 

STRENGTH, 6o 

percent 

&-Mean and. Range of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME.years 

c.) Hampton.VA 

1 L aseline Scatter Bond 

RE SI DU AL 

STRENGTH, 6o 

percent 

t baseline 40 

Mean and Range -1 &-of 6 Replicates 

0- 

012345 

EXPOSURE TIME.years 

b.) Gulf of Mexico 

120r 

RE SI DU AL 

STRENGTH. 6o 

percent 

1 LBaseline Band Scatter 

&-Mean and, Range of 6 Replicates 20 

basel in e 

012345 

EXPOSURE TIME.years 

d.) Toronto.Conada 

0- 

012345 

EXPOSURE TIME,yeors 

e.) Ft. Greely.Alasko 

Figure 13.-Residual Short Beam Shear Strength of Kevlar-49/CE-306 Epoxy Specimens Exposed at Locations Shown 

74 
8OC / 

RESIDUAL 1 LB;mgine Scatter 

STRENGTH, 6o 

percent 

Mean and Range 4-of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME.years 

0.1 Cameron. LA. 

120r 

RESIDUAL aseline Scatter 

STRENGTH, 11 , l I , percent 

baseline 

012345 

EXPOSURE TIME, years 

40 

&-Mean and. Range of 6 Replicates 20 

0 

c.) Hamptan.VA 

RESIDUAL 

STRENGTH, 6o 

percent 

c baseline 

40 

012345 

EXPOSURE TIME, years 

b.) Gulf of Mexico 

RESIDUAL 1 LBoseline Band Scatter 

STRENGTH, 6o 

percent 

Mean and Range &-of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME,years 

RESIDUAL 

STRENGTH, 6o 

Dercent 

&-Mean and. Range 

20 of 6 Replicates 

baseline 

012345 

EXPOSURE TIME.years 

e.) Ft. Greely.Alaska 

d.) Toronto.Canada 

Figure 14.-Residual Short Beam Shear Strength of Kevlar-49/F-l85 Epoxy 

Specimens Exposed at Locations Shown 

75 
RESIDUAL 

STRENGTH, 

percent 

baseline 

Mean and Range &-of 6 Replicates 20 

012345 

EXPOSURE TIME, years 

a.) Cameron, LA. 

BOC I 1 LBaseline Scatter 

Band 

RESIDUAL 

STRENGTH, 6o 

percent 

&-Mean and. Range of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME, years 

c.) Harnpton,VA 

- sol- I 

RESIDUAL 1 [Baseline Bond Scatter 

STRENGTH, 6o 

percent 

&-Mean and. Range of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME.yeat-s 

b.) Gulf of Mexico 

sol- I 

RESIDUAL 1 [Baseline Band Scatter 

STRENGTH, 6o 

Dercent 

&-Mean and Range 

20 of 6 Replicates 

baseline 

012345 

EXPOSURE TIME,years 

RESIDUAL Baseline Scatter 

STRENGTH, 6o Band 

percent 

&-Mean and, Range 

of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME, years 

d.) Toronto,Canada 

e.) Ft. Greely.Alaska 

Figure 15.-Residual Short Beam Shear Strength of Kevlar-49/LRF-277 Epoxy 

Specimens Exposed at Locations Shown 

76 
120r 

80C / 

RESIDUAL 1 LB;;jine Scatter 

STRENGTH, 6o 

percent 

L baseline 40 

Mean and, Range 

2:/, &-of , 6 Replicates , , , 

012345 

EXPOSURE TIME.years 

0 

a.) Cameron. LA. 

RE SI DU AL 

STRENGTH, ~~~ land 

percent 

L aseline Scatter 

&-Mean and. Range of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME.years 

c.) Hampton.VA 

RESIDUAL L oseline Scatter 

STRENGTH, ~~~ Band 

percent 

Meon and. Range 

20 &-of 6 Replicates 

012345 

EXPOSURE TIME.yeat-s 

baseline 

b.) Gulf of Mexico 

RESIDUAL 

STRENGTH, 6o 

Der cen t 

Mean and. Ronge 

20 &-of 6 Replicates 

baseline 

012345 

EXPOSURE TIME.years 

1 LBaseline Scatter Band 

RESIDUAL 

STRENGTH, 6o 

percent 

Mean and. Range 

&-of 6 Replicates 20 

40 t baseline 

0- 

012345 

EXPOSURE TIME.years 

e.) Ft. Greely.Alaska 

d.) Toronto,Canoda 

Figure 16.-Residual Short Beam Shear Strength of T-300 Graphite/E-788 Epoxy 

Specimens Exposed at Locations Shown 

77 
STRENGTH. 6o 

percent 

baseline 

40 

20 

0- 

012345 

EXPOSURE TIME.years 

Band 

0 Cameron, LA. 

Hompton. VA. 

Toronto. Canoda 

hFt. Greely.Alasko 

- 

- ZGulf of Mexico 

- 

Figure 17 .-Effect of Exposure Location on 

the Residual Short Beam Shear 

Strength of Kevlar-49/F-l85 

RESIDUAL 

STRENGTH, 6o 

percent 

baseline 0 Cameron, LA. “1 0 Gulf of Mexico 

OHampton. VA. 

A Toronto, Canodo 

20 hFt. Greely.Alosk0 

0- 

012345 

EXPOSURE TIME.years 

Figure 19 .-Effect of Exposure Location on 

the Residual Short Beam Shear 

Strength of Kevalr-49/CE-306 

sol- I 1 LBaseline Scatter 

Band 

RESIDUAL 

STRENGTH, 6o 

percent 

0 Cameron, LA. 

0 Gulf of Mexico 

OHompton. VA. 

A Toronto. Canoda 

hFt. Greely.Alosko 20 

baseline 

012345 

EXPOSURE TIME.yeors 

Figure 18 .-Effect of Exposure Location on 

the Residual Short Beam Shear 

Strength of Kevlar-49/LRF-277 

1 LBaseline Scatter Band 

RESIDUAL 

STRENGTH, 6o 

percent 

baseline 0 Comeron. LA. “k OHompton. VA. 

20 

0 Gulf of Mexico 

A Toronto, Conoda 

kFt. Greely.Alosko 

0 

012345 

EXPOSURE TIME.years 

Fioure 20 .-Effect of ExDosure Location on 2- ~ 

the Residual ‘ Short Beam Shear 

Strength of T-300/E-788 

78 
RE SI DU AL 

STRENGTH, 

percent 

basel in e 

12c 

1 oc 

8C 

60 

40 

20 

0 

0 

---g 

- A- _- 

--- 

--- 

LBasejine n Scatter 

Band 

0 Kevlar Fabric(281)/CE-306 Epoxy 

A Kevlar Fabric( 120)/LRF-277 Epoxy 

hKevlar Fabric(281)/F-i 85 Epoxy 0 T-300 Graphite/E-788 Epoxy 

1 2 3 4 

EXPOSURE TIME,years 

5 

Figure 21 .-Residual Short Beam Shear Strength of 

Composite Materials after Exposure 

79 
sol- / 

RESIDUAL 1 Llgitine Scatter 

STRENGTH, 6o 

percent 

Mean and. Range &-of 6 Replicates 20 

baseline 

012545 

EXPOSURE TIME, years 

a,) Cameron. LA 

120r 

____ ____------- 

RESIDUAL 

STRENGTH, 6o 

percent 

baseline 

012345 

EXPOSURE TIME.years 

c.) Hampton.VA 

RESIDUAL 

STRENGTH. 6o 

per cen t 

baseline 401 Mean and Range 

20 I- of 6 Replicates 

0- 

012345 

EXPOSURE TIME.years 

b.) Gulf of Mexico 

RESIDUAL Eo[ LBgdine Scatter 

STRENGTH, 6o 

percent 

&-Mean and Range of 6 Replicates 20 

boseline 

012345 

EXPOSURE TIME.years 

1 LBaseline Scatter Band 

RESIDUAL 

STRENGTH, 6o 

percent 

Mean and Range &-of 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME,years 

e.) Ft. Greely.Alasko 

d.) Toronto.Canada 

Figure 22.-Residual Tensile Strength of Kevlar-49/CE-306 Epoxy Specimens Exposed at Locations Shown 

80 
RESIDUAL eo[ .&line Scatter 

STRENGTH, 6o 

Der cen t 

Mean and. Range 

20 40 t &-of 6 Replicates 

baseline 

0 

012545 

EXPOSURE TIME.years 

0.) Cameron, LA. 

m-----iD 

7----------- 

- - - - - 

RE SI DU AL 

STRENGTH, 6o 

percent 

Mean and. Range 

20 &-of 6 Replicates 

baseline 

012545 

EXPOSURE TIME,years 

c.) Hampton.VA 

e01 I 

RE SI DU AL 

STRENGTH, 6o 

percent 

1 L %and aseline Scatter 

Mean and. Range &-of 6 Replicates 20 

baseline 

012545 

EXPOSURE TIME.years 

b.) Gulf of Mexico 

120r 

aoC / 

RESIDUAL L aseline Scatter 

STRENGTH, %and 

percent 

Mean and. Range 

20 &-of 6 Replicates 

baseline 

Mean and Range &-of 6 Replicates 20 'L 0 

baseline 

012545 

EXPOSURE TIME.years 

e.) Ft. Greely,Alaska 

012545 

EXPOSURE TIME.years 

d.) Toronto,Canada 

Figure 23.-Residual Tensile Strength of Kevlar-49/F-l85 Epoxy 

Specimens Exposed at Locations Shown 

81 
IIfII ---- &- ----- lZ0I I- -------- -- 

RE SI DU AL 801 Laseline Band Scatter 

STRENGTH, 6o 

percent 

c bo sel in e 

40 2ot Mean and. Range &-of 6 Replicates 

0- 

012345 

EXPOSURE TIME, years 

0.) Cameron, LA. 

RE SI D U AL 

STRENGTH, 6o 

percent 

Mean and Range 

20 &-of 6 Replicates 

basel in e 

012345 

EXPOSURE TIME,years 

c.) Hampton,VA 

RESIDUAL 

STRENGTH, 6o Band 

percent 

Mean and Range 

&-of 6 Replicates 20 

baseline 

012545 

EXPOSURE TIME.years 

b.) Gulf of Mexico 

80 c/ 

RE SI D U AL 

STRENGTH, 6o 

percent 

1 iB;;ziine Scatter 

Mean and. Range &-of 6 Replicates 20 

baseline 

Mean and Range 

&-of 6 Replicates 20 

012345 

EXPOSURE 

u 

TIME.years 

baseline 

e.) Ft. Greely,Alaska 

O 012345 LEXPOSURE TIME.years 

d.) Toranto,Canada 

Figure 24.-Residual Tensile Strength of Kevlar-49/LRF-277 Epoxy 

Specimens Exposed at Locations Shawn 

82 
12or -I-' 

RE SI DU AL 

STRENGTH, 6o 

percent 

1B;aztine Scatter 

SOL / 1 L aseline Scatter 

Bond 

RESIDUAL 

STRENGTH, 6o 

percent 

Mean and. Range &-of 6 Replicates 20 

basel in e 

Mean and. Range 

20 &-of 6 Replicates 

basel in e 

012345 

EXPOSURE TIME,years 

012345 

EXPOSURE TIME, years 

0.) Cameron. LA. b.) Gulf of Mexico 

ml- / 

RESIDUAL 

STRENGTH, 6o 

percent 

RESIDUAL L aseline Scatter 

STRENGTH, 601 Band 

percent 

Mean and. Range 

20 &-of 6 Replicates 

baseline 

Mean and. Range 6-0, 6 Replicates 20 

baseline 

012345 

EXPOSURE TIME. years 

012345 

EXPOSURE TIME.years 

c.) Harnpton.VA d.) Toronto.Canada 

RESlDl 

STREN 

Der cer 

&-Mean and. Range 

20 of 6 Replicates 

baseline 

012345 

EXPOSURE TIME.years 

e.) Ft. Greely,Alaska 

Figure 25.-Residual Tensile Strength of T-300 Graphite/E-788 Epoxy 

Specimens Exposed at Locations Shown 

83 
RE SI DU AL 

STRENGTH, 6o 

percent 

B;msline Scatter 

0 Cameron, LA. 

0 Gulf of Mexico 

Hompton. VA. 

Toronto. Conoda 

hFt. Greely.Aloska 20 

baseline 

012345 

EXPOSURE TIME, years 

Figure 26 .-Effect of Exposure Locotion on 

the Residual Tension 

Strength of Kevlar-49/F-185 

sol- I 

RESIDUAL 1 Lg;;zIine Scatter 

STRENGTH, 6o 

percent 

0 Cameron. LA. 

0 Gulf of Mexico 

Hampton. VA. 

Toronto. Conodo 

hFt. Greely,Aloska 20 

baseline 

012345 

EXPOSURE TIME.year-s 

t igure 78, Effect of Exposure Location on 

the Residual Tension 

Strength of Kevalr-49/CE-306 

RE SlDU AL 

STRENGTH, 6o Band 

percent 

0 Comeron. LA. 0 Gulf of Mexico 

Hampton. VA. 

Toronto, Conoda 

hFt. Greely.Alaska 20 

baseline 

012345 

EXPOSURE TIME,years 

Figure 27 .-Effect of Exposure Location on 

the Residual Tension 

Strength of Kevlar - 49/LRF- 277 

801 I 1 LBaseline Scatter 

Band 

RESIDUAL 

STRENGTH, 6o 

percent 

0 Cameron, LA. 

0 Gulf of Mexico 

OHomaton. VA. 

baseline 

A Toronto, 'Conoda 

hFt. Greely.Aloska 

012345 

EXPOSURE TIME.yeors 

Figure 79 .-Effect of E xposure Location on 

the Residual Tension 

Strength of T-300/E-788 

84 
RESIDUAL 

STRENGTH, 

percent 

basel in e 

Figure 

120 

100 

80 

60 

40 

20 

0 

0 

-7- 

LBasejine n Scatter 

Band 

0 Kevlar Fabric(281)/CE-306 Epoxy 

A Kevlar Fabric(l20)/LRF-277 Epoxy 

hKevlar Fabric(281)/F-185 Epoxy 0 T-300 Graphite/E-788 Epoxy 

1 2 3 4 

EXPOSURE TIME,years 

30.-Residual Tensile Strength of 

Composite Materials after ExDosure 

5 

85 
Moisture 

Absorption, 

percent 

* 

I 0 

i 

1 .oo 

AAMA Ontario, Canada 

- 00000 Hampton, VA 

t&nM Gulf of Mexico 

00000 Cameron, LA 

00000 Ft. Greely, AK 1 Filled symbols are unpainted 

0.00 ' I I I I 1 

0 1 2 3 4 5 

Exposure Time,yea rs 

Figure 33. - Moisture absorption of Kevlar-49/LRF-277 

Composite Material 

Moisture o.80 t 

Oe60 i Absorption, 

percent 

0.20 

0.40 1 

* t3 

A 

0 

AAAAA Ontario. Canada 

00000 Hampton, VA 

t&nM Gulf of Mexico 

00000 Cameron, LA 

00000 Ft. Greely, AI< 

t illcd symbols or<' LIII~~II~~I~YI 

0.00 ' I I I I I 

0 1 2 3 4 5 

Exposure Time,years 

Figure 34. - Moisture absorption of T-300/E-788 

Graphite/epoxy Composite Material 

86 
Moisture 

percent 

Absorption, 2.00 

0 

AAAAA Ontario, Canada 

00000 Hampton, VA 

M&nbt Gulf of Mexico 

00000 Cameron, LA 

00300 Ft. Greely, AK 

Filled symbols are unpainted 

0.00 ' I I I I I 

0 1 2 3 4 5 

Expos u re Tim e ,yea rs 

Figure 31. - Moisture absorption of Kevlar--49/CE-306 

Composite Material 

2.00 

Moisture 

Absorption, 

percent 

0 

$r A 

0 

0 Q 

A 0 0 z 

AAAAA Ontario. Canada 

M 

00000 Hampton, VA 

Gulf of Mexico 

00000 Cameron. LA 

00000 Ft. Greely, AK 

Filled symbols are unpainted 

Ex p o s u re Ti m e ,ye a r s 

Figure 32. - Moisture absorption of Kevlar-49/F- 165 

Composite Material 

a7 
As fabricated 

1 yr exposure 

3 yr exposure 

5 yr exposure 

I I 

0 inches 1 /2 

Figure 35. - Effects of Outdoor Expsure on Unpainted 

Kevlar-49/CE-306 Composite Material Eqmsed at 

Hampton, Va 

aa 
As fabricated 

1 yr exposure 

3 yr exposure 

Figure 36. - Effects of outdoor Exposwe on Unpainted 

Kevlar-49/F-185 Caposite Material Expeed at 

-, va 

89 
0 inches 1 /2 

As fabricated 

1 yr exposure 

3 yr exposure 

5 yr exposure 

Figure 37. - Effects of Outdoor on Unpahbd Kmlar-49/LRF-277 Cmposite Materml Ekpoeed at 

HamPtOn, va 
As fabricated 

1 yr exposure 

I 

0 inches 1 /2 

Figure 38. - Effects of outdoor Exposum on Unpainted - T3OO/E-788 Graphite/epoxy Ccanposite Material 

at -1 va 

91 
1. Report No. 2. Government Acceasion No. 

NASA TM-101645 

3. Recipient's Catalog No. 

AVSCOM TM 89-B-007 I 

4. Title and Subtitle 

Hampton, Va 23665-5225 

5. Report Date 

12. Spomoring Agency Name and Address 

National Aeronautics and Space Administration 

Washington, DC 20546-0001 

and 

FIVE YEAR GROUND EXPOSURE OF COMPOSITE MATERIALS USED ON THE BELL MODEL 206L FLIGHT SERVICE 

EVALUATION 

7. Author(s) 

DONALD J. BAKER 

3. Performing Organization Name and Address 

Aerostructures Directorate 

U.S.Army Aviation Research and Technology Activity(AVSC0M) 

NASA-Langley Research Center 

13. Type of Report and Period Covered 

Technical Memorandum 

July 1989 

6. Performing Organization Code ~ 

- 

8. Performing Organization Report No. 

10. Work Unit No. 

50563-01-06 

11. Contract or Grant No. 

U.S. Army Aviation Systems Command 

St. Louis, MO 63166 

15. Supplementary Notes 

Donald J. Baker: Aerostructures Directorate 

USAARTA-AVSCOM, Langley Research Center, Hampton, Virginia 

This report presents part of the results of a U.S. Army/NASA-Langley sponsored research program to 

establish the long term-term effects of realistic ground based exposure on advanced compwite materials. 

Residual strengths and moisture absorption as a function of exposure time and exposure location are 

reported for four different composite material systems that have been exposed for five years on the North 

American Continent. 

L6. Ahtract 

17. Key Words (Suggested by Authors(s)) 

Composite Materials 

Environmental Effects 

19. Security Classif.(of this report) 120. security Classif.(of 

18. Distribution Statement 

Unclassified-Unlimited 

Subject Category 24 

his page) 121. NO. of Pager I 22. Price 

Unclassified ' I Unclassified I 92 I A05 I 

lASA FORM 1626 OCT 86 

For sale by the National Technical Informstion Service, Springfield, Virginia 22161-2171