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O OCTS'JBtf.' • \^^
t NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
TECHNICAL NOTE
No. 1054
IMPACT STHENO-TH AND FLEXUEAL PROPERTIES OP
LAMINATED PLASTICS AT HIGH"AND LOtf TEMPERATURES
By J. J, Lamb, Isa"belle Albrecht, and B. M. Axilrod j National Bureau of Standards
^HÖE^' ' Washington August 19k6
K A C A LIDRAKy J LANGLEY MEi IOKIAL AEEOitAUTEKAt.
IJUQORATORY , Langley Field, VH
1176 01433 8637
NATIONAL ADYISORY COMMITTEE FOR AERONAUTICS
TECHNICAL NOTE NO. 1054
IMPACT STRENGTH AND FLEXURAL PROPERTIES OF
LAMINATED PLASTICS AT HIGH AND LOW TEMPERATURES
By J. J. Lamb, Isabella Albrecht, and B. M. Axilrod
SUMMARY
The Izod-impact strengths and flexural properties of sev- eral types of plastic laminates, which are either in use or have potential application in aircraft structures and parts", were determined at different temperatures in the range of -700 to-200° .F.
The materials investigated were unsaturated-polyester laminates reinforced with glass fabric and phenolic laminates reinforced with asbestos fabric, high-strength paper, rayon fabric, and cotton fabric. Both high-pressure and low-pressure types of cotton-fabric phenolic laminates were included.
The impact strength of specimens tested flatwise was 4 to 7 foot-pounds per inch of notch for all the except the glass fabric and rayon fabric laminates, materials had impact strengths of 31 and 17 foot-poun respectively, at 77° F. The high-strength-paper, ray and asbestos-fabric phenolic laminates showed small c impact strength between -70° and 2000 F. Cotton~fabr lie laminates showed pronounced decreases in impact s at the low temperature and small changes between 775
F. The glass-fabric unsaturated-polyester laminates creased impact strengths at the low temperature.
at 77° F laminates These two ds , on-fabric, hanges in ic pheno- trength and 2000 had in-
The flexural strengths and moduli of elasticity of all the materials increased with change in the test temperature from 77° to -70o F. Under exposure to a 200° F temperature, all materials except the asbestos-fabric laminate lost 30 to 40 percent of their flexural strength at 770 F and the moduli of elasticity of all the materials, except the asbestos-fabric and one cotton-cloth phenolic laminate, decreased about 20 percent.
NACA TN So. 1054 2
Tests made at room temperature after heating the materi- als at 200° F for 24 hours indicate that prolonged heating with consequent loss of moisture content and further cure of the resin may offset the effect of high temperature alone. In flexural tests made at 1500 y ana 90 percent relative humidity- two laminates showed considerable loss in strength.
INTRODUCTION
A knowledge of the effect of temperature on the strength properties of plastics is of considerable importance in ap- plication of the materials for aircraft structural purposes. Results obtained by various investigators (references 1, 2, and 3) on plastic materials indicate that considerable varia- tion may be expected.
Oberg, Schwartz, and Shinn (reference 2) reported varia- tions of 10 to 30 percent in the tensile and flexural proper- ties of grades C, L, and XX phenolic laminates for the range -38° to 78o I1. Data on resin-bonded plywood and compreg also are included.
Norelli and G-ard (reference 3) reported data for tensile, compressive, and shear strengths and tensile moduli of elas- ticity for various phenolic laminates for temperatures rang- ing from -670 F to as high as 392° T in some instances. They concluded that the percentage change in strength for cellulose-filled plastics is greater than for the mineral- filled plastics.
Meyer and Brickson (reference 4) determined the mechani- cal properties of high-strength paper-base phenolic laminates for temperatures from -69° to 2000 F. For this temperature range they found large variations in tensile, compressive, and flexural strengths and somewhat smaller variations in modulus of elasticity. The strength and modulus-of-elasticity values diminished with increasing temperature.
In recent investigations by the Naval Air Experimental Station (reference 5) considerable data has been obtained at 770 and 1600 j on the mechanical properties of a variety of plastic laminates. The ultimate strength and modulus-of- elasticity values were generally lower at the higher tempera- ture but the percentage changes varied greatly for the different materials.
II AC A TN No. 1054 3
Izod-impact test data reported by Fuller (reference 6) for grades L and XX phenolic laminates and for a glass-cotton- fabric phenolic laminate indicate an increase in Izod-impact strength with temperature for the cellulose-filled resin and an opposite trend for the glass-cotton-fabric laminate for the^ range -67° to 158° F. Shinn (reference 7) found that the Izod-impact strength of paper and cotton-fabric phenolic lami- nates increased with temperature over the temperature range -67° to 158° F and a similar trend was observed for paper and cotton-fabric allyl laminates between -67° and 77° F,
The present investigation was undertaken to obtain the impact, flexural, tensile, and compressive strength properties of representative laminates in the temperature range -70° to 300° F. Since testing at these temperature conditions_pre- sents many problems not net in testing at room temperature, a major part of the project was concerned with the development of apparatus and techniques. This report summarizes the re- sults of Izod-impact and flexural tests on the selected mate- rials. Both flexural strength and flesuralfinodulug-of- elasticity data were obtained in the flexural tests.
This Standards assistance
The courtesy of the Army Air Forces, Bakelite Corporation, Consolidated Water Power and Paper Company, Formica Insulation Company, Plaskon Division of the Libbey-Owens-Ford Glass Company, and the Synthane Corporation in furnishing materials for use in this investigation is gratefully acknowledged. The cooperation of H. J> Kaiser, Es
w„ Thiebeau, G-, E. Brenner, and P. Pfaff of the National Bureau of Standards Instrument Shop in the design and construction of the flexural apparatus and the preparation of the test specimens also is appreciated.
MATERIALS
The materials selected for testing included commercial grades of high- and low-pressure cotton-fabric phenolic lami- nates, an asbestos-rfabric grade AA phenolic laminate, a high- strength-paper phenolic laminate, a rayon-fabric phenolic laminate, two experimental phenolic laminates made with high pressure and low pressure, respectively, using the same grade C cotton fabric as filler, and two glass-fabrio laminates looiideä. with the same unsaturated polyester reein. The
NACl TN No. 1054 4
materials were supplied in. nominal l/8- and l/3-inch thick- nesses. A detailed description of the materials is contained in table I.
DEFINITIONS
Izod-impact strength:
Snergy to break the specimens divided "by the dimension along the notch of the specimen
Flexural properties for "beam of rectangular cross section sub- jected to a concentrated load P at midspan:
Extreme fiber stress (at midspan):
s = 2- £* 2 bd3
where
P load
L span or distance between supports
b breadth of beam
d depth of beam
Flexural strength:
_ 3 Pml Sr = _ 2 bds
where Pm is maximum load and other quantities are as defined previously"
Flexural modulus of elasticity:
£ L3 P
4bd3 x
where x is the deflection at midspan and the other quantities are as defined previously
NACA TN No. 1054 5
Initial modulus of elasticity % is obtained when the initial slope of the load-deflection curve is used for P/x.
Secant modulus of elasticity for the stress range 0 to Sa is obtained from the above formula for E, using the value of Pj. corresponding to Sj and obtaining the corre- sponding deflection ij, from the load-deflection curve.
Specific flexural strength:
Sr
(Specific gravity)2
Specific modulus of elasticity:
B
/ \3
(Specific gravity)
where the specific gravity is taken as eq.ual numerically to the density in grams per cubic centimeter.
Statistical terms:
Mean value:
The arithmetic mean of a set of measurements
Standard error of the mean (usually called the "standard error" if no other statistic is referred to at the same time);
r\s + r2a + r3s + . . „ + r a + , . . + r a S.B
n(n-l)
where
r^ the difference between the iÜL. measurement and the mean value
n the number of measurements
NACA TN No. 1054
Standard error for the difference of two means ;
S.E.-n * ycs.i.j3 + (S.E,3)3
wh ere
S.E.j standard error for first mean
S.E.2 standard error for second mean
Criterion for significant difference between two means (as for example when comparing the mean of a group of treated specimens with the mean of a similar group of untreated specimens):
If the difference of the two means exceeds three times S.E.-j, the difference is considered signifi- cant .
APPARATUS AND TEST PROCEDURE
The testing procedures outlined in federal Specification L-P-406a (reference S) were followed as closely es possible. The specimens, however, were not polished with fine emery pa- per after machining. The flexure specimens of one glass-' filled laminate U2 were cut with a diamond abrasive saw. The impact and flexure specimens of the other glass-filled laminate ABS were machined with Carbide-tipped tools. Spec- imens of all other materials were machined with high-speed steel tools which gave a finish considered satisfactory.
Specimens tested at 77° P and 50 percent relative humid- ity were conditioned at least 95 hours prior to test. Speci- mens tested at other temperatures were first conditioned the same as the 77° 3P specimens and then were kept at the testing temperature for 24 ± 3 hours prior to test.
Impact Strength
The impact tests were made according to Method 1071 in Federal Specification L-P-406a, using a Baldwin-Southwark T>endulum-type Izod-impact machine which had ranges of 2, 8,
NACA TN No. 1054
and 16 foot-pounds. The specimens were centered and the notch located properly with alinement Jigs.
The tests were made at temperatures of -70°, 0°, 77°, and 200°P. The relative humidity was controlled at 50 percent in testing at 77° F and was not controlled at the other tempera- tures. The tests at 0° and 77° F were made in rooms controlled at these temperatures. For the -70° and 200° P tests, the impact machine was housed in an insulated cabinet shown in figure 1. The i cept during the air; heating was were kept in a < for about 20 hoi 2 to 4 hours prior to testing.
machine was housed in an insulated cabinet shown in 1. The air in the cabinet was circulated by a fan ex- iring the impact tests. Dry ice was used to cool the jating was done with electric heaters. The specimens "-,+ 4- ~ conditioning cabinet at the test temperature
3urs and were then placed in the testing cabinet
In testing conducted in the insulated cabinet the opera- tor kept his hands, which were protected with woolen gloves, inside the cabinet for periods of about 15 minutes at a time. This is sufficient for testing about 5 to 10 specimens.
The materials in the l/2-^inch thickness were tested flat- wise and edgewise for both the lengthwise and crosswise orien- tations. Since the Izod-impact machine had a limited capacity (16 ft-lb), the specimens of the glass-filled laminate tested flatwise were made only 0.25 to 0.30 inch wide. Edgewise tests were made on specimens of the l/8-inch-thick sheets of the materials for both lengthwise and crosswise orientations.
Plezural Properties
The flexural tests were made according to Method 1031 of Federal Specification L-P-406a, using a 2400-pound-capacity Baldwin-Southwark hydraulic universal testing machine which had ranges of 240, 1200, and 2400 pounds. This machine was located in a room in which the atmosphere was controlled at 77° P and 50 percent relative humidity. Tests to obtain flexural strength and load-deflection graphs were made at -70°, 77°, an(i 2000 P. p0r the low- and high-temperature tests the specimen, the flexural jig, and the deflection indicator were enclosed in a temperature-controlled cabinet equipped with a blower. The arrangement of the flexural apparatus for the low- and high-temperature tests is shown in figures 2 and 3. In figure 2 the insulated cabinet has been removed to show the pressure piece, flexural jig, and attachments.
The flexural jig is initially centered and alined relative
NACA TIT No. 1054 8
to the pressure piece in the following way. The alinement plate (L) having parallel V-grooves is used to locate the flexural jig relative to the pressure piece (S1) after the span has "been set appropriately. This is done with the con- tact edge of the pressure piece in the central V-groove in (.L) under a light load. The stand is clamped to the magnetic chuck and the latter is energized. As the right- and left- hand sections of the calibrated screw (J) have right- and left-hand threads, respectively, the flexural jig is now self- centering. Subsequent changes in the span merely require loosening the cap screws, setting the screw (j), and tighten- ing the cap screws again.
The deflection of the specimen at the center of the span relative to the supports is indicated "by an equal-arm lever (N) actuating a gage shown in figure 3. The gage, a Southwark-Peters plastics extensometer, Type PSr-6 or PS~7, is attached to the aluminum alloy brackets (P) which have grooves to locate the knife-edges of the gage. Load*-deflection graphs are obtained with this gage coupled to the recorder on the testing machine. The high-magnification gage, Model PS-6, has a range of 0.23 inoh and the low-magnification gage, Model PS-7, a range of 1 inch.
In figure 3 the flexural apparatus is shown with a specie men in place and the front of the cabinet removed. Triple- paned windows in the front and side, armholes, and lights in- side the cabinet facilitate the manipulation of the specimen and equipment.
Little difficulty was encountered in the high-temperature testing with this equipment. At low temperatures, frost on the electrical contacts of the gage was washed off with ethyl alcohol. Rusting of the flexural jig and gage upon removal from the cabinet was avoided by immersing them in alcohol un- til they attained room temperature. They were then disassem- bled and dried thoroughly and the flexural jig re-oiled.
The span of the flexural jig is adjustable from 1.6 to 9 inches and the screw is graduated to 0.002 inch. The combina- tion of recording gage and lever is acourate to about 5 percent in the measurement of deflections over 0.01 inch with the PS-6 gage and to about 3 percent for deflections over 0.1 inch with the PS-7 gage. The percentage error diminishes as the deflec- tion increases. Calibrations were made only at 77° P.
The flexural properties were determined only for the 0.5-inch-thick laminates. Bach material was tested four ways,
NACA TN No. 1054 <
flatwise and edgewise for specimens out both lengthwise and crosswise. At least five specimens were tested for each material for all orientations. The only deviation from Method 1031 of Federal Specification L-P-406a was the use of a span-depth ratio of 8:1 instead of 16:1 in order to con- serve materials. However, for comparative purposes flexure tests were made also at 77° 3? with a span-depth ratio of 16:1.
RESULTS AND DISCUSSION
Impact Strength
The data for Izod-impact strength of the various lami- nates at temperatures of -70°, 0°, 77°, and 200° F are pre- sented in table II. The variation in impact strength with temperature is shown graphically in figures 4a and 4b for lengthwise specimens of the 0.5-inch-thick materials tested flatwise. Figures 5 to 8 show the variation of impact strength of paper, cotton-fabric and rayon-cotton-fabric phe- nolic laminates with temperature for the various orientations of specimen and direction of load.
The Izod-impact strengths at 77° IP for the phenolic glass-fabric laminates tested flatwise are approximately as follows:
m„ ^ T * *. Izod-Imnact Strength Type of laminate /,, ,VJ; - . &- \ I_L . (ft-lb/in. of notch)
Grade 0 phenolic, high-pressure and low-pressure 4-7
High-strength-paper phenolic 4
Asbestos-fabric phenolic 2 - 4^
Rayon-cotton-fabric phenolic 17
G-lass-fabric unsaturated- polyester 30
The paper and asbestos laminates showed less than 25 percent variation in impact strength over the range of temper- ature and orientations of specimen and loading investigated.
NACA TN No, 1054 10
The variation in. impact strength was less than 10 percent for the 0.5-inch-thick paper laminate tested flatwise.
The temperature-impact strength trend for high-strength paper laminate agrees quite well with Shinn's data (reference 7) for flatwise tests where a very slight increase in strength with temperature was found for the range -67° to 158° F. Meyer and Erickson (reference 4) reported that the impact strengths for "Papreg" at the extremes of temperature were slightly less than the normal temperature values, a trend found in this lab- oratory only for the 0.5-inch sheets tested edgewise. In their impact tests at 158° and 200° Ff Meyer and Erickson stated (reference 4) that the specimen was "tested at room tempera- ture within 15 to 30 seconds after removal from the condition- ing medium"; this test condition is "believed to introduce some uncertainty into the results.
All the cotton-fabric laminates exhibited a steady de- crease in impact strength as the temperature was reduced from 77° to -70° F. For materials 12, L2, and V2, the impact strength at -70° F was between 55 and 65 percent of the 77° F value for all orientations of specimen and directions of load employed. The corresponding range for T.*r2, high-pressure grade C laminate, was 73 to 77 percent. Little change in im- pact strength at 200° F compared to 77° F was observed for the cotton-fabric laminates with the exception of the 12 mate- rial. The latter laminate showed a steady increase in impact strength with temperature up to 200° F. These results are in good agreement with values reported for grade-C material by Shinn (reference 7),who found that in flatwise tests impact strengths at -67° and 158° F were 66 and 113 percent, respec- tively, of the value at 77° F.
Directional properties were observed for the parallel-ply laminates, 12 and E2. The asbestos-fabric material, K2, for which the effect was greatest, exhibited an impact strength in the crosswise direction less than half of the cor- responding value in the lengthwise direction.
The rayon and glass-fabric laminates had much higher impact strengths than the other materials and also show dif- ferent impact-strength versus temperature trends (figs. 4a and 4b). When tested edgewise, the rayon laminate in both the " 1/8- and l/2-inch thicknesses showed a slight but steady de- crease in impact strength.as the temperature was varied from -70° to 200° F. The glass-fabric laminate, AB2, shows a constant trend toward higher impact strength at low
NACA TN No. 1054 11
temperatures. This agrees with data on glass-fabric laminates given by both Field (reference l) and Fuller (reference 6).
The approximate values for the changes in Izod-impact strength at -70° and 200° F are as follows :
Type of laminate
Change in Izod-impact strength -70ö F 200° F
(percent) (percent)
Grade C phenolic, low-pressure -40 0 to 5
Grade C phenolic, high-pressure -25 to -40 +10 to + 35
Asbestos-fabric-phenolic -15 -10
High-strength paper phenolic 0 to -20 +5 to -20
Rayon-fabric phenolic 0 to +35 0 to -10
Glass-fabric unsaturated- polyester +45 -5 to -15
The impact strength for specimens struck edgewise was lower than that of specimens of the same material tested flat- wise. For a given orientation of specimens in the sheet, the ratio of edgewise to the flatwise impact strength was very nearly constant for a given material over the range of temper- ature employed. These ratios are given in table III for the data in table II. The mean value of this ratio was 0.5 to 0.6 for the cotton-fabric laninates, 0,2 for the paper laminate, 0.8 for the asbestos-fabric laminate, and about 0.4 for the rayon-fabric laminate. The data of Meyer and Erickson (refer- ence 4) for cross-ply high-strength paper laminate give a value of 0.19 for this ratio at the various test temperatures.
In the tests at 200° F the materials may have lost some moisture as compared to those tested at the lower temperatures and may have undergone further cure as a result of the heating. To obtain information relative to these effects, Izod-imtjact specimens were tested at 77° l> after being heated at 200
b F for 24 hours and cooled to room temperature for 1 to 2 hours over calcium chloride in a desiccator. The results of these tests are shown in table IY. The low-pressure cotton-fabric materials, L2 and V2, were about 10 percent weaker and the glass-fabric laminate about 10 percent stronger after the 200° F
1TACA TN No. 1054 12
heating. A decrease of 10 percent was noted for the rayon laminate, hut this was not significant according to the_sta- tistical criterion. (See section on definitions.) No defi- nite effect of the heating on the strength of the other materials was noted.
Flexural Properties
The results of the flexural tests of the laminates at temperatures of -70° to 200° F are shown in table V for an 8:1 span-depth ratio. Values reported include flexural strength, specific flexural strength, initial and secant moduli of elasticity, and specific modulus of elasticity. The percentage, changes in strength of the materials from the 77öF values under exposure to the high and low temperatures are also shown in table V. The variations with temperature of flexural strength, specific flexural strength, initial flex- ural modulus of elasticity, and specific initial flexural modulus of elasticity of the materials are shown in figures 9, 10, 11, and 12, respectively, for the lengthwise-flatwise tests.
A typical load-deflection curve obtained at -70° F with the recorder is shown in figure 13. Average curves of extreme fiber stress versus deflection at midspan are shown in figure 14 for the different materials at 77° F. Similar stress- deflection curves are shown in figures 15 through 23 for the nine laminates at -70°, 77°, and 200° F. Figures 24 and 25 represent the average stress-deflection curves for the four directions of testing at 77° F of the asbestos-fabric laminate and the glass-fabric laminate, U2, respectively. Average stress-deflection curves for specimens taken lengthwise, crosswise, and on the diagonal from the rayon laminate, Z2, and the glass laminate, AB2, are shown in figures 26 and 27, respectively. The experimental stresB-deflection data were adjusted for the thickness of the material by multiplying the measured deflection at midspan by the ratio of standard thick- ness to the actual thickness; the curves shown in figures 14 through 27 were calculated for a standard thickness of 0.50 inch.
NACA TN No. 1054 13
at The
77° F flatwise flexural properties of were approximately as follows:
some of the laminates
Type of laminate Fleiural "strength
(105 psi)
Initial flexural
modulus of elasticity
(10s psi)
Grade C phenolic, low-pressure
Grade C phenolic, high-pressure
16 0.80
18 to 22 1.0 to 1.1
Asb-estos-fabric phenolic 9(C) and 16 (L) l .0 (C) and 1.2(L)
High-strength-paper phenolic S3 2.4
Rayon-cotton-fabric phenolic 34 1.6
Glass-fabric unsaturated- polyester
(C) - Crosswise
45(C) and 55(L)
(L) - Lengthwise
2.5 to 2.9
The four cotton-fabric phenolic laminates, 12, L2, V2, and ¥2, exhibit quite similar properties. For a given ma- terial the properties were generally equal to within 15 per- cent for the various orientations of specimen and load. The flexural strength of these cotton-fabric laminates increased about 10 to 30 percent at -r70° F and decreased very nearly SO nAfootit. a-fc P.nn® T? An•-»«»«;? 4-^ 4-1*-. nnO m i n —_-
These results are in fair agreement with data for grade C phenolic laminate given by Oberg, Schwartz, and Shinn (ref- erence 2). They observed increases in flexural strength and flexural modulus of elasticity of about 17 percent at -38° F compared to values at 78° F and 40 percent relative humidity.
The asbestos-fabric laminate, £2, of parallel-ply con- struction showed directional effects, especially in regard to
NACA TN No. 1054 14
the flexural strength. (See ta"ble V.) The variation of the strength properties of this material with temperature was less than that of the cotton-fabric laminates and the trend is dif- ferent. Most of the change in flexural properties of the asbestos-fabric laminate occurred between 77° and -70° F; the flexural strength and initial modulus of elasticity increased roughly 20 and 35 percent, respectively, at -70° F. The aver- age change in flexural properties at 200° F was not over 5 percent. The .stress'def lection curves for this material (fig. 16') indicate the similarity between the properties at 77° and 200° F.
The flexural strength and initial flexural modulus of elasticity of the paper phenolic laminate, S2, varied with temperature in a manner similar to the values for the cotton- fabric laminates except that the initial modulus of elasticity increased only 20 percent between 77° and -70° F.
The two glass-fabric laminates, Ü2 and AB2, showed the same trend in change of flexural strength and modulus of elasticity with temperature (figs. 9 and 11). The flexural strength increased about one-third at -70° F and decreased about one-third at 300° F. The flexural strengths of the two materials did not -differ significantly. The AB2 laminate was superior to the U2 material in flexural modulus of elas- ticity, having greater values at all temperatures and for all directions of testing. The percentage decrease in modulus of elasticity at 200° F was less for the AB2 than for the U2'" laminate.
NACA TU No» 1054 15
For "both, glass-fabric laminates the stress-deflection di- agrams were less curved than for any other materials tested. In the lengthwise and crosswise directions the secant modulus of elasticity for the range 0 to 35,000 psi showed a decrease of less than 10 percent from the initial modulus of elasticity at all the temperatures.
The approximate values for the changes in flexural strength and flexural modulus of elasticity at -70° and 200° F for the lengthwise and crosswise directions of the laminates investigated may he summarized as follows:
n. . Change in Change in initial flexural
r i 4 « fleXUral gtr»ngth modulus of elasticity Type of laminate n ^ „ — *- -70° F 200° F -70° F 200° F
(percent) (percent) (percent) (percent)
Grade C phenolic 10 to 30 -SO 40 to 80 -8 to -25
Asbestos-fabric phenolic 20 -5 35 0
High-strength-paper phenolic 25 -40 20 -18
Rayon-co tton-fabric phenolic 30 -25 40 -30
Glass-fabric unsat- urated-polyester 30 -30 to -35 10 to 15 15 to -25
Four of the nine materials tested, the two glass-fabric laminates, the asbestos-fabric laminate, and the grade 0 lam- inate, 12, were of parallel-ply construction. The most pronounced difference in strength properties between specimens taken from the principal directions of the sheet was observed in the asbestos-fabric laminate, K2. Its crosswise impact and flexural strengths were only half of those for the length- wise direction. The lengthwise flexural properties of the two glass-fabric laminates differ less than 15 percent from the corresponding crosswise flexural properties. The differences between the flexural properties for the lengthwise and cross- wise directions for the grade C parallel-ply laminate, 12, were small and were of the same order of magnitude as the cor- responding difference for the three cross-ply cotton-fabric laminates. The flexural properties of the AB2 glass-fabric-
ÜTACA Tff 5To. 1054 16
When the density is considered in evaluating the flexural properties of the materials, the cellulose-filled laminates, with lower densities than the mineral-filled laminates, com- pare more favorably with the latter materials and are superior in some instances. This may "be seen "fay comparing figures 9 and 10 or 11 and 12. The specific flexural strength values are in the ratios of 18:17:16 for the rayon-f abric, paper, and glass-fabric laminates, respectively. The specific initial flexural modulus of elasticity values are in the ratios of 9:6:5 for the paper, rayon-fabric, and. glass-fabric laminates. These graphs also show that there is no difference in specific strength properties between the low-pressure and high-pressure laminates, V2 and W2, made with the same grade C fabric.
Flexural tests were also made at 77° F on specimens heated at 200° 3? for 24 hours to determine whether changes in the strength properties occurred in the 200° F tests. Such changes may be brought about by (a) additional cure of the resin, (b) loss of moisture, (c) deterioration of the filler if organic, or (d) a combination of these factors. The re- sults of these tests and of tests on unheated specimens are shown in table VI. The flexural strength values showed an average decrease of about 8 to 13 percent for the cotton-fabric and paper laminates. The changes in the flexural moduli of elasticity were small and not consistent except for the low- pressure material, L2, which exhibited increases of 10 per- cent after heating. The glass-fabric laminate, U2, exhibited average increases of 11 and 4 percent, respectively, in flex- ural strength and moduli of elasticity on heating. The asbestos-fabric laminate, K2, also exhibited higher flexural properties after heating, the increases in flexural strength and moduli of elasticity being about 7 and 12 percent, respec- tively.
It seems reasonable that the strength and modulus of elasticity values of these organic plastics should diminish with increase in temperature if no change in composition or structure takes place. If heating a laminate at 200° F for 24 hours causes an increase in the strength properties due to a change in composition or structure, then in the flexural tests at 200° F (table V) the effects of prolonged heating and
NACA TN No. 1054 . IV
of an elevated test temperature may oppose one another. This may explain the very small differences "between the flexure . properties at 77° and 200° I" (table V) for the asbestos-fabric laminate which had increased flexural properties at 77° F aft- er heating (table VI). The effect of prolonged heating on the flexural strength of laminates was investi-gated "by Hausmann, Parkinson, and Mains (reference 9). They found that the flexural strength of grades 0, X, and XXX phenolic lami- nates at 90° 0 increased with the length of time the specimens were at the test temperature. (See table I, reference 9.) For the grade XXX laminate the flexural strength values at 90° 0 after a month of heating were nearly equal to the 25° 0 values on unheated specimens.
Flexural strength tests were made on six laminates at 150° F and 90 percent relative humidity after 24 hours condi- tioning at the test temperature, combining the effects of elevated temperature and high relative humidity. The results of these tests are given in table VIII together with corre- sponding data from table V for the 77° and 200° F tests.
The deleterious effect of these extreme conditions was most pronounced for the paper laminate, S2, and the low- pressure grade 0 laminate, V2.- The other four materials were not so greatly affected by these conditions as they were by 24 hours at 200° F and a low relative humidity. The effect of moisture content on the strength properties of high-strength- paper laminate was studied by Erickson and Mackin (reference 10). They tested specimens from a series of panels condi- tioned 100 days at 80° F at various relative humidities. They found decreases in ultimate strength in tension, compression, and flexure of 25 percent or more and decreases of about 35 percent in modulus of elasticity as the relative humidity was varied from 30 percent to 97 percent, corresponding to mois- ture contents ranging from 0.2 to 9.5 percent.
The above results and the results obtained in this labora- tory indicate the necessity for studying the effect of relative humidity as well as temperature on the strength properties of laminates, especially those with cellulosic fillers.
The results of tests made at 77° F using span-depth ra- tios of 16:1 and -8:1 are given in table VII, The flexural strength obtained with a 16:1 span-depth ratio was slightly less for all materials, the decreases ranging from about 2 percent for the glass-fabric laminate, U2, to about 7 percent for the cotton-fabric phenolic laminates. The initial 'flexural modulus of elasticity values were usually a little greater for
NACA TN Ho. 1054 18
the tests with the larger span-depth ratio. The 12 material, a high-pressure phenolic grade C laminate, showed significant changes in "both flexural strength and initial modulus of elas- ticity with the change in span^-depth ratio. Significant changes in only one of the two properties occurred.for the rest of the materials listed in table VII.
CONCLUSIONS
1. The Izod-impact strength-temperature trend of the laminated plastics is different for the various types of mate- rial. The glass-fabric laminates decreased steadily in impact strength with increasing temperature, the value at 200° F be- ing about 70 percent of the -70° value. The asbestos-fabric, rayon-fabric, and highr-strength-paper phenolics showed little variation in impact strength between -70° and 200° F. The cotton-fabric phenolics exhibited increasing impact strength with temperature, roughly doubling their impact strength be- tween -700 an<i 3oo° y.
2. The Izod-impact strength values for the rayon-fabric and the glass-fabric laminates are much greater than for the other materials.
3. The ratio of edgewise to flatwise impact strength for the l/2-inch-thick phenolic laminates tested is nearly con- stant over the range of temperatures, -70° to 200° IP.
4. An increase in flexural properties occurred for all materials at low temperature, and at high temperature a de- crease occurred for all materials except the asbestos-fabric laminate, which showed no change.
5. The high-strength-paper and two glass-fabric laminates are outstanding in flexural properties. When the materials are compared on the basis of specific strength values, th~e paper and rayon-fabric laminates are superior to the others.
6. The low-pressure grade-C phenolic laminate, V2, con" pared favorably in flexural strength properties with the high- pressure laminate made with the same filler, especially when the comparison was made in terms of specific strength proper- ties .
7. The flexural properties of plastic laminates at high temperature are not a function of temperature alone, but may
NACA TIT No. 1054 19
"be affected by further cure of the resin and loss of moisture content.
8. The effect of high humidity in addition to an elevated temperature may be much different from the effect of the ele- vated temperature alone. A severe loss in strength was noted for the high-strength-paper and one low-pressure cotton-fabric phenolic laminate at 150° 3P and 90 percent relative humidity.
National Bureau of Standards, Washington, D. 0», December 29, 1945.
NACA TN NO. 1054 20
REFERENCES
1. Field, Modern 128, 130
Philip K.: Basic Physical Properties of Laminates irn Plastics, vol. 20, Aug. 1943, pp. 91-102, 126,
2. Oberg, T. T., Schwartz, R. T. , and Shinn, Donald A.: Me- chanical Properties of Plastic Materials at Normal and Subnormal Temperatures. Air Corps Tech. Rep. No. 4648, June 6, 1941; Modern Plastics, vol. 30, April 1943, pp. 87-100, 122, 124, 126, 128.
3. Norelli, P., and Gard, W. H.: Temperature Effect on Strength of Laminates. Ind. Eng, Ohem., vol. 37, June 1945, pp. 580-585.
4. Meyer, H. R., and Erickson, B. C. 0.: Factors Affecting the Strength of Papreg. Some Strength Properties at Elevated and Subnormal Temperatures. Rep. No. 1521, Forest Products Laboratory, U. S. Dept. of Agriculture, Madison, Vis., Jan. 1945.
5. Renwick, Wm. C: Properties of Plastic Laminates, Part VI. Naval Air Exp. Sta. Rep. TED NAM 25217.0, June 3, 1944.
6. Fuller, Fortest B.: Engineering Properties of Plastics. Modern Plastics, vol. 20, June 1943, pp. 95-97, 130.
7. Shinn, D. A.: Impact Data for Plastic Materials at Various Temperatures. Air Corps Tech;Rep. No. 5Cl2, Aug. 9, 1943; Modern Plastics, vol. 22, July 1945, pp. 145-152, 184-186.
8. Federal Specification L-P-406a: Plastics, Organic; General Specifications, Test Methods; Jan. 24, 1944. Government Printing Office, Washington 25, D. C.
9. Hausmann, E. 0., Parkinson, A. E., and Mains, G. H.: Heat Resistance of Laminated Plastics. Modern Plastics, vol. 22, Nov. 1944, pp. 151-154, 190, 192, 194, 196, 198.
10. Erickson, E. C. 0., and Mackin, G. Ef: Properties and Development of Papreg - A High-Strength Laminated Paper Plastic. Trans. A.S.M.E., vol. 67, May 1945, pp. 267- 277.
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Table III.- Ratio of EdgewiBe Impact Strength to Flatwise Impact Strength fir Lsminated PlaBtics at
Various Temperatures.
> o
S3 o
H O Material Designation
Orientation of Specimen
Ratio at TestLTemperature of •70° F 6°" F JILL go6°"F
Mean Ratio, All Temp.
12, Grade C Phenolic
K2, Ashestos-Fabrlo Phenolic
L2, Low-Pressure Cotton-Fabric Phenolic
S2, High-Strength-Paper raonoxxa
V2, Low-PresBure Grade 0 Phenolic
W2, High-Pressure Grade 0 Phenolic
Z2, Rayon-Cotton-Fabric Phenolic
AB2, Glass-Fabric Unsaturated-Polyes tor
Lengthwise Cropswipe
Lengthwise Crosswise
Lengthwise OrOBswiBe
Lengthwise Crosswise
Lengthwise Crosswise
Lengthwise Crosswise
Lengthwise CrosBwise
Lengthwise CroBSwi.se
0.62 0.60
0.77 0.32
0.57 0,56
0.17 0.17
0.£L O.63
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TABU IV.- ffiFPECM OF HEATIHO IT 200oFBF0R 24 HOURS 05 IZOD-IMPAOT 8TRBHGTH5
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Impaot St rength
tu Q
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Orientation of Speolmen
Direction of Load
So Heating (ft-lb/ln.of notch)
Range of Machine
(ft-ibL Heated at 200°F
(ft-lb/ln.of notch)
Range oT Machine
I (ft-ib)
12, Grade C Phenolic
ES, Asbestos-Fabric Phenolic
12, Low-Pressure Cotton-Fabric Fhenolio
S2, High-Strength-Paper; Fhenolio
VB, Low-Pressure Grade C Phenolic
1N2, High-PreBSUr© Grade C Phenolic
22, Rayon-Cotton«Pabrio Phenolic
AB2, Glass-Fabric Unsaturated-Polyeater
Lengthwise Orosetise
Lengths lee Crosswise
Lengthwise CroBSwise
Lengthwise Crosswise
Lengthwise Crosswise
Oroeswiee
Lengthwise OzosBwise
Lengthwise
Flatwise Flat«1Be
Idgewlee Edgewise
Edgewise Edgewise
Flatwise Flatwise
Flatwise Flatwise
Flatwise
Flatwise Flatwise
Flatwise
5.06 t 0.14 4.03 I 0.05
3.84 1 0-03 1.60 + 0.05
a.2a j 0.0s 3.09 i 0.01
4.ia + 0.10 4.17 + 0.14
6.57 i o.i4 6.26 ; 0.13
5.27 S 0.37
17.6 i 0.6 17.4 i 0.7
31.5 i 0.6
g
8 8
8 8
16 16
16
5.13 i 0.13 4.21 1 0.07
3.86 i O.06 1.48 i 0.03
2.«8 + Q.04 2.«5 i 0.02
4.02 * 0.18 ' 4.29 i 0.20
5-95 i 0.21 5.55 + 0.1Ö
4.93 i 0.12
16.0 * 0.4 15.8 1 1.0
35-5 i 0.8
8 8
8 8
8 8
16 16
16
a. The teets were made in acoordance with Method 10711 Federal ßpeoifiostion L-P-406a.
b. Mean value fox nine to twelve specimens for all materials except glase-fabxio laminate ABE, for which 20 to 25 specimens were tested. The accompanying plus or minus value is the etand&rd error.
o. Specimens conditioned and tested at 77°F and gQjb relative humidity. d. Speoimens teBted at 77°F after being allowed to cool to room temperature
fox 1 to 2 hours in a desiccator containing calcium ohloride.
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BytTlil Potmnrtlon Ori»nt»tlon of BP«<I1M»B
DlnotioB Tnp TMt J2Ü
Fl«nr«l Stattxth, *.'• • Initial Tjg3e3tr
(lflftWfa8!,
Flmml Modulo» of llMtlott
Ufl^£Zis!L Onugo ill
I üRangoi of Btxeu " „ (lowy) (io°ln/iiig> Inn6lb/ln2)
Jhift B.digt liodülta» to* Tirlofi»-
(lofrb/l^) Br/18p.w*A/- (MPlb/ln2)
anrtn VftlnaT"
SS 38, IUgh-3tMngth-
ftipor Phanollo
02, Qlas»-Fabrlo ^Dkuaturat*d-
PoXyo«t«p
V2,Low-Proi«ur« Oride 0 Fhtnollo
«S, Hl(jb.-Pr«Mur» dnlt a Fbanolia
LmgthvlM
OroMwHt
LmgtlwlM
OroMwiM
UngthwlM
Oxoinlaf
I*ngthwlio
OroMwiM
I*ngtkwlM
Oro***la*
Longthw!«
OronwlM
Ltocthwla*
OioMwlM
rutwii*
rutwu«
IdgtwlN
Idgewlis
flatwlM
nstwiM
XdgtwlM
Mgraioa
riatwlM
tdgowlt«
IdftWiM
rutwiM
-7o
eoo
EOO
-70
Ungthwlao Cdftwlu
CIOMWIM Xitnif -70
»0.7 2 0.3
if.i I o'.e 42.4 2 1.4 34.2 2 0.6 I9.8 2 0.»
*J.7 1 0.7 3J.| 2 0.£ 20.6 2 0.3
42.0 2 0.7 33-6 2 0.4 20.8 2 0.*
78.1 I 0.5 56.9 t 0.1 37-Ot 0.3
59.0 10.8 tg.l 20.7 £7.6 20.5
.2 2 0.4
.8 2 0.9 30 i 0.9
66.0 i 0.5 48.6 2 0.5 34.5 i 0.»
SO.« 2 0.4 16.7 2 0.3 11.4 2 0.2
20.4 2 0.4 I6.3 i 0.2 ll.g 2 0.2
.8 * 0.4
.3 2 0.1
.4 * o.e 20.2 2 0.2 I6.5 2 0.2 XI.5 2 0.1
E2.6 2 O.3 18.3 2 0.4 13.3 2 0.2
23.9 i 0.3 .18.4 I 0.2 13.2 2 0.1
23.E 2 0.4 17.9 J 0.1 12.7 i 0.3
£3.3 2 0.2 18.0 2 0.1 IZ.7 2 0.2
+23
-42
+24
-42
+30
-39
+25
-38
+27
-35
+31
-39
+3*
-21
+36
-29
+24
-32
+25
-29
+22
-30
+22
-30
+23
-28
+30
-28
+30
-29
+29
-29
2.89 2 0.02 2.42 2 0.02 1.95 i 0.01
2.92 2 0.03 2.30 2 0.02 1.88 * 0.02
3.32 2 O.Oi 2.65 2 0.0; 2.21 2 0.0;
3.12 2.71 2 2.29 2 0.02
2 O.O5 2 0.06
2.87 - 0-01 2.59 - 0.02 1.89 2 0.02
2.72 2-0.02 2.45 2 0.01 1.82 2 0.02
2.94 2 0.03 2.70 2 0.03 2.66 2'0.03
2.76 2 0.01 2.43 2 0.03 1.82 2 0.01
1.22 2 0.02 0.82 2 0.01 0.71 2 0.01
1.27 i 0' 0.81 2 0.02 0.68 2 0.01
1.14 2 0.01 0.79 2 0.01 O.65 2 0.01
1.21 2 0.01 O.79 2 0.01 0.64 2 0.01
1.31 2 0.02 O.96 2 0.02 0.80 2 0.02
1.45 2 0, O.99 2 0.02 0.82 2 0.02
1.46 2 0, 1.00 2 0, O.75 2 0.02
I.56 2 0.01 I.03 2 0.02 0.80 0.03
+19
-19
+27
-18
+25
-17
+15
-16
+11
-27
+11
-26
+ 9
-24
+14
-25
+49
-13
+57
-16
+44
-18
+53
-19
+36
-17
+46
-17
+46
-25
+51
-22
0-10,0001b/ln2 O-l5,O0Olb/ln2 0-20,0001b/tn2 O-25,O001b/ln2
2.71 2 0.03
1.80 2 0.01
1.78 2 0.01
2.16 2 0.02
2.28 I.55
0.01 0.01
2.24 2 0.02 1.51 2 0.01
S:i ; 2 0.02 2 0.02
2.60 2 0.06 1.89 2 0.02 2.21 2 0.02
0-20,0001b/ln2 O-25,O001b/ln2
2.78 2 0.02 2.10 2 0.01
2.84 2 0.02 2.O5 2 0.01
3.14 2 0.04 2.31 2 0.01
3.03 2.35
0.02 O.O5
2.86 2 0.01 2.57 2 0.02 1.84 2 0.02
2.66 2 0.02 2.35 2 0.02 1.71 2 0.02
2.94 2 0.03 2.67 t 0.03 2.00 2 O.O3
2.72 2 0.02 2.37 2 0.03 1.73 t 0.01
O-5,O001b/ln2
O.63 2 0.01
0.61 2 0.02
0.59 2 0.01
0.60 2 0.01
0-5, OOOlb/11)8
0.74 2 0.01
O.76 2 0.03
O.74 2 0.02
I b.77 2 0.01
2.78 2 0.01 2.52 2 0.02 1.80 2 0.O2
Vi : 0.01 : 0.02 : 0.02
2.92 2 0.03 2.63 - 0.04 I.97 2 0.03
2.63 2-33 1.68
0.01 0.03 0.01
2.77 2 0.02
3.06 2 0.03
2.96 2 0.04
O-lO.OOOlb/l«? 0-15,0001b/laS
0.79 0.3S
1.09 2 0.02 O.58 2 0.01 0.41 2 0.02
1.11 2 0.01 . 0.02 : 0.01
O.58 2 ..__ 0.39 2 0.01
1.09 2 0.01 0.60 2 0.01 OAl 2 0.01
0.59 2 0.41 2
1.05 2 0.01 0.58 2 0.01
0.79 2 0.03 0.01
0.83 2 0.02 0.39 2 0.01
0.78 2 0.01 0.37 2 0.01
0.83 2 0.01 O.38 2 0.01
0-10,0001b/in2 0-15,0001b/ln2
1.23 2 0.02 O.76 2 0.02 O.55 2 0.02
I.36 2 0.05 0.79 2 0.02 O.58 2 0.03
1.38 2 0.02 0.78 2 0.02 0.52 2 0.03
1.47 2 0.01 0.81 2 0.02 0.55 2 O.Ot
1.05 2 0.04 O.58 2 0.02
l.r 0,
.17 2 0.06 59 2 0.03
1.17 2 0.04 O.59 2 0.03
1.32 2 0.01 0.61 2 0.02
20.1
I* 21.0
10.2
20.8 16.7 10.3
22.8 18.0 11.7
18.6 14.2 8.7
23.1
3:? 20.8 15.3 10.9
12.5 10.0 6.8
12.3
8 6.8
12.1 •9 • 9 8
12.2
?:? 12.9 9.9 7-1
12.5
12.6 V 6.9
1.01 o.r 0.1 0.845
.681
1.02
o!656
1.16, O.926 0.772
\% 0.800
O.509 0.459 O.335
0.482 0.434 0.323
O.52I 0.479 O.365
0.489 0.431 0.323
O.568 0.382 0.331
0.592 0.577 O.3I7
0.531
o'.303
o'.ya
0.326
0.580 0.398 0.298
0.620 0.409 O.3W
TABIZVI .- tmCT Of MATI»0 AT 200° T TOR 24 HODBB OH MKDRAl PHOPIRTTW Of HAKIMIED «ITIRIAIS.*
lo Beating» (lQJlb/li?)
flexnral stren/raT" iHoated at 200°r° MSE
nnmral llodulue of ElaatlcltT
lo Hsatlng^ Heati lateriil Pealgnatlon
Orientation Dlreotlon of Bpaolaan I of toad
lo UaatlnL Heated at 2Q00r° Uo°lP/ln2) qpSlh/lng) •ÜgPlVA'
at 2go°r< Ho Beating0
(lpSlb/ln2) Heated at 2Q0°F°
12, Orade C Phendllo
EB, Aaboat'oa-Fabrlo Phanollo
LB, Low-Presaure Cotton-Fabrlo Phanollo
32, Hlsh-3tron3th-Papar Phanollo
TIB, Qlaei-Fabrda Onaaturated-PolyaBter
VB, iow-Preaaur» . Orada C Phanollo
ij2, Hish-rroaaure Orada C Phanollo '
Z8, nayon-Cotton-Fabr-lo. Phenolic
ABB, Olaas-Fabrie !
Bhaaturatod-Polyeetor
Oroaewlae Lengthwlee
Croaeiri.ee Croeewlee
Croaawiae Croaawlsa
tengthwlee Oroeewlae
Oroeawlee Croeewlee
tengthwlee Croeewlee Lengthwlao Oroaewlae
Lengtbwlaa Oroaewlae Lengthwieo Croaawiae
Lengthwlee Croaawiae
Lengtbwlaa
riatwlaa Idgewlee
natwlaa Idgewlae
20.7 i 0.3 21.2 i 0.2
8.9 S 0.8 9.* i 0.1
flutpiae Idwwiaa
rlatwlee Idgewlee
riatwlaa Idgewlae
riatwtee riatwlaa Idgewlee Idgewlee
rlatwlee riatwlaa Idgewlae Idgewlee
rlatwlee rlatwlee
i mtwioe
lb.l 17.5
O.S 0.4
33.8 t 0.4 33.6 1 0.4
45.1 1 0.7 43.6 * 0.5
16.7 t 0.1 16.3 s 0.5 16.3 i 0.1 16.5 : 0.2
111.3 1 0.4 18.4 • 0.2 17-9 18.0 ;
0.1 0.1
34.4 1 0.5 .32-7 * 0-5
53.2 : 0.1
18.8 1 0.2 19.7 i 0.3
9.6 i 0.1 9.9 - 0.2
15.4 )5.7
0.1 0.1
27.2 t 0.6 .30.4 t 0.1
53-0 i O.J 51.3 i 0.5
14.7 i 0.2 14.6 i 0.2 14.7 i 0.1 14.5 1 0.5
16.9 i 0.4 17.2 t 0.2 16.5 1 0.2 16.3 J 0.2
31.0 30.8
0-.4 ; 0.7
57-« : 0.7
1.07 i 0.07 1.14 j — 0.03
0.99 • o.oi 0.97 i 0.08
1.07 l.ll
l.ll 1.07
0.B0 0.76
2.42 2.71
L.ll 0.02
0.02 0.06
2.45 • 0.01 2.43 • 0.02
0.82 t 0.01 0.81 i 0.02 0.79 i 0.01 0.79 1 0.01
0.96 • 0.02 0.99 i 0.02 1.00 i O.OJ I.03 I 0.02
I.58 1 0.02 1.40 I 0.01
'2.88 1 0.01
0.02 0.03
0.01 0.01
0.86 1 O.Cl o.ae 1 0.02
2.43, 2.88
2.55 2.52
0.02 0.05
; 0.01 : 0.03
0.79 * 0.01 O.77 2 0,01 0.74 1 0.01 0.74 • 0.08
0.89 i 0.02 0.91 I 0.03 0.91 t 0.01 0.94 I 0.02
1.71 i 0.01 1.39 i 0.02
2.91 • 0.04
0-10,000 lb/ln2
1.02 * 0.04 1.09 * 0.02
0.99 J 0.02 1.04 1 0. 01
0-7,500 lb/In2
0.92 £ 0.01 0.90 I 0.02
1.04 • 0.02 0.99 : 0.02
0-1(J,UOC lb/ir-
0.67 1 Crll 0.6* 1 O.OI
C.72 . (.-.Cl 0.7E 1 L.Ö1
0-15,000 lb/In«*
2.28 i 0.01 2.60 J O.O6
2.23 i 0. 2.64 i 0.
0-20,000 lb/in8
8.35 J 0.02 2.37 i 0-03
0-10,000 lb/ln2
2.48 « 0.01 2.46 • 0.03
O.58 i 0.01 0.59 i 0.02 O.58 J 0.01 0.60 2 0.01
0.56 : 0.01 0.55 1 0.01 0.56 1 0.01 0.59 • 0.01
0-10,000.lb/ln2
0.76 t 0.02 0.79 1 0.02 0,78 i 0.02 0.81 t 0.02
0.76 • 0.03 0.79 : 0.03 0.78 1 0.02 0.81 t 0.02
0-15,000 lb/ln2
1.42 1.25
0.03 0.02
I.56 I 0.004 1.24 1 0.02
0-20,000 lb/ln2
2,80 • 0.32 2.S0 I 0,02
0-25,000 lb/ln'
2.29 • 0.02 2.33 i O.03
2.44 t 0.01 2.42 I 0.03
0-15,000 lb/ln2
,58 i 0.02 .59 I 0.03 •59 i O.OJ ,61 : 0.08
O.57
o-20,f)00 lb/ln2
I 0.03 1 O.OJ : 0.03 1 0.02
1.23 i 0.04 1.09 I 0.02
1.42 i 0.004 1.09 • 0.D2
0-25,000 lb/ln
2.77 - o.pe 2.77 0.02
b. Data fro» table T j •PMUMO« oondltloned and to.ted at 77°' «"- 50* «Artiw M»ldlty.
0. Spool«.», teated at 77°r after being allo«d to oool to room te«n.ratur. for 1 to 2 honr. In c deelooator oontalnlng oalolvuo onlorlda.
TABU vn- tmoT or era-am RATIO CM rmtsui pftanmn or utaatn FUSTICM
Oriürtatlsn tf Bpoolaaii
OlTAotlOC of LOBJ
ntotanl ltni|tt it Ipa-Mh IttUt ; P^HlHPtyBA
1:1 . I IETT „
Initial He-Msa aJ ttatrticltj It Bpan-Dapth ftttBi
nantria nodoina of EUitiol-tT
{MM»
gp=s Oaoant VooÄiaa or laaraoity 1 \Z-T „.
»4 M M
lattorl«! Designation LVlnB) (105jb7ijg)
IB, arid! C PbattwUo
KB, JLabaitoa-Palirla
13, Lo«-?nMim Cottwi-Fabrlo Phtnolio
13, Kgfc-StMWtli-filiw Phmolia
IB, (Ji*»a-T»brts. (hu&tsr«ted- PoUe»t«>
Vs. LW-PMMBM (b«di 0 Fbanello
K, Hlgv-Fnean» Braa* 0 Plwulln
re, E«ioii-ootton-r»brio Pfcooollo
*B3, oim-pitoiii
iiangtlniaa oxoaan«* Length«-!*« OtoMwm
LSBSUUIU« Otouirlse LrasUnlse Oxomlae
Ltt gthMw oniiwl» LaagtlnlBa
Leighaiaa nmniii Lafigthi&aa aiouwu«
Langt kirlae Onwswlw Limethwlaa cwawiaa
Lcnjtimlae Oroawlaa Lengtlwtae Oroaailaa
langt lnrlaa •Jroaaal» Langtlnlae Otoaairl»
Langthalaa OroMwla« LanjthaUe OIHMH
Laugtbilaa Croaaalaa L«ogth»laa OiMaalce
rutwii« riaftaaa td|»idaa umui
riatalu »laMta Kdgnl*« Idgavla*
lOatwlw riataln
Idöawlao
rutdit riit*iii IlfMlaa RlgawiM
mtHae Hatalae Idgavlaa HgBWlM
riitalae rla.t*lM Idgavlaa IdgewlM
rlatiiaa Flatrdao ligeilaa Kdgsaiaa
n-jtvlaa IdBOwlao Ideaalae
riatwlaa ri*twlaa Idgavlaa Edgswlaa
22.2 2 0.: B0.7 i 0. 21.fi 2 0. a.S 2 0.1
IS.J 2 0.6 8.3 i 0.2
16.& : o.e 9.4 i o.i
ie.4 * o.e ie.1 ; o.e il«5 r °«e
17.11 o.4
5.2 * 0,4 *.e 2 0,6
is.; 2 o.H 18.1 2 o.e 17.9 2 0.1 18.0 1 0.1
jlt.1V 1 O.J «.7 i O.f J3.4 ± o.f SI.7 io.i
fiO.S 2 0 53-5
s jq.l o 2 0.7
2 0.5 :0.7
SO.9 i 0.1 19.7 * O.J 19.8 1 o.e 19.5 2 0.1
9.0 2 0.1
ifi.5 t o.e
:.* 2 o.e !.4 1 0.5 .6 * 0.4 ,.S 2 0.5
55-7 2 0.7
65!! * o!ft
3 j 0.1 0 : o.e
15, i 1 O.'l
5S.1 1 0.5
J7.9 t 0.8
l.OB 2 0.02 1.07 i 0.07 l.lt 2 0.03 l.U i 0.08
i.eo t o.oe 0.99 t 0.01 1.15 i 0.97 : o.oe
i O.OE
O.SO £ 0.01 0.80 i 0.01 0.7s • 0.01 0.76 : o.oa
o.oe o.oe
1 0.03 t 0.0E
59 2 o.oe ,*5 £ 0.01 fa s 0.03
J i O.03
o.se : 0.01 0.81 * 0.05
01 01
0.7? i 0.0 0.79 I 0.0
0,96 • o.oe 0.9? 2 o.oe 1.0a 2 0.03 1.03 i o.oe
1.58 : o.oe i.fo : 0.01 1.57 2 o.aj 1.96 2 0.01
e.tH 1.o.ai E,* I 0,01 e.*9 2 o.aS E.Sa 2 0,02
i.e4 t o.oe l.EE 2 0.03 1.30 2 0.08 1.31 2 o.o<+
i.o£ 2 o.oe
0.87 2 0.01
K.54 2 0.02 a.5« 2 0.03 2.57 2 0.04 e.54 2 0.03
2.<K 2 O.O5 e.$£ 2 o.oe E.ao 2 o.oe E.57 2 o.oe
o.*- 2 0.01 o.as 2 o.oi 0.84 2 o.oe O.M 2 0.01
1.03 2 0.03 l.OB +O.O5 1.01 2 o.oe 1.00 : o.04
1.76 2 0.03 1.42 t o.oe 1.66 2 o.oe 1.43 2 0.04
J.14 i o.oe
3.U 1 o.o4
0-10,000 lb/In2
1.07 2 o.oe 1.02 2 0.04 1.09 2 o.oe 1.04 2
1.10 2 0.02 l.oe 2 0.01 I.09 2 O.OE 1.07 2 0.03 0.07
0.5,000 UJ/D>5
i.eo
l'.l5 2 0.02 7 i o.oe
0.02 0.01
0.97 1.02 2 0.02
0-10,000 llj/ln6
0,67 io.m. 0.67 2 0.01 0.6S 2 0.01 0.64 2 0.01
0-20,000 lb/la2
E.10 t 0.01 s.05 2 0.01 e.31 : 0.01 E.J5 i 0.06
0.7fi 2 0.79 2 0.7« £ O.fll 2
O-I5.OOO Ib/U'
i.4e 1. 1 1.3
2 0.03 2 o.oe 2 0.03 2 o.oi
o-i;,ooo ib/ia'
e.BO 2.61
0.02 0.01
2.B7 2 0.01 .66 2 0.01
2.97 * 0.03
2.95 * 0.03
0-7,500 a/In*
0.90 2 0.02 0.92 2 0.02
0.S4 2 a.01
2.15 i 0.03 E.1J 2 0.0E 2 2
17 2 0.06 I IE 2 0.04 '
0-30,OM lb/In8
I.58 2 O.03 I.EO 2 0.04 1.47 S 0.01 1.21 i 0.04
0-25,000 lDi/inE
e.52 2 o.oe E.B9 2 o.oe 2.63 2 0.04 2.33 2 0.03
2.63 I 0.04 2.33 2 0.01 2,62 2 0.01 e.32 2 o.oe
O-lS.OOO'lVin"
0.5« 1 O.55 2
0.04 0.06
•ptalHU «J«I «udltloutd md Mated at 77°r »nd 40f mum lualdlty In aaoordaaoa frtth Kttbod IO31. railaral BpaolflntGa UrAoSa. Ituh Taloa In Ww tablt npnmti Uta HU for fir* to tan apaolMs*. - aocoarpurtas pi« or aim»» nlna la tha atudanl arn».
TBJI
NACA TN No. 1054 30
TABLE VIII.- FLEXtJRAL STRENGTH OF LAMIHATES AT VARIOUS TEMPERATURES AND RELATIVE HUMIDITIES^
Material Designation
77°F 50# R.H.b
(105lb/in2)
Flexural Strength. 150°P 90% R.H.C
(105lb/in2)
200°P - < 6% H.H.
(105lb/ing)
12, Grade C Phenolic
S2, High-Strength-Paper Phenolic
V2, Low-Pressure Grade C Phenolic
W2, High-Pressure Grade C Phenolic
Z2, Rayon-Cotton-Pabric Phenolic
AB2, Glass-Fabric Uns aturated-Polye ster
22.2 1 0.3
33.2 * 0.4.
16.7 i 0.3
18.3 i 0.4
34.4 i 0.5
53.2 i 0.1
19.8 + 0.2
13.2 i 0.6
7.0 * 0.1
15.4 i 0.3
26.0 i 0.3
34.7 i 0.4
14.5 ± 0.1
19.4 i 0.2
11.4 i 0.2
13.3 * 0.2
25.8 i 0.5
33.8 i 0.8
a. Lengthwise specimens tested flatwise. Tests were made in accordance with Method 1031, Federal Specification L-P-406a, using an 8:1 span-depth ratio. Each value in the table represents the mean for five specimens.
b. Data from table V; specimens conditioned and tested at 77°F and 50$ relative humidity.
c. Specimens tested at 150°F and 90$ relative humidity after 24 hours at the test conditions•
d. Data from table V; specimens tested at 200°P and less than &% relative humidity after 24 hours at the test conditions.
NACA TN No. 1054 Fig. 1
Figure 1.- Izod impact machine in insulated cabinet with front panel removed.
NACA TN No. 1054 Fipr. 2
Figure 3.- Adjustable-span flexural jig used for high- arid low-temperature testing.
t '1 • *•!
1 I. <
ill
.UJ
o
A! o
O if*
*tj.
#
Figure 3,- Flexural apparatus in insulated cabinet with front panel removed; a BT>ficimen is in t)lace.
NAOA TN No. 1054 Fig. 4a
40
X
Li_ O 30
20
I K L S V w z
AB
TYPE OF LAMINATE GRADE C PHENOLIC ASBESTOS-FABRIC PHENOLIC LOW-PRESSURE COTTON-FABRIC PHENOLIC HIGH-STRENGTH-PAPER PHENOLIC LOW-PRESSURE GRADE C PHENOLIC HIGH-PRESSURE GRADE C PHENOLIC RAYON-COTTON-FABRIC PHENOLIC GLASS-FABRIC UNSATURATED-POLYESTER
8 10
200
TEMPERATURE, °F Figure 4a.- Variation of Izod impact strength with
temperature for 1/2-inch-thick laminates, Lengthwise specimens tested flatwise.
NAOA TN No. 1054 Fig. 4b
zo
2J0
M
I JO
TYPE OF LAMINATE I GRADE C PHENOLIC K ASBESTOS-FABRIC PHENOLIC L LOW-PRESSURE COTTON-FABRIC PHENOLIC S HIGH-STRENGTH-PAPER PHENOLIC V LOW-PRESSURE GRADE C PHENOLIC W HIGH-PRESSURE GRADE C PHENOLIC
1 -70 77 200
TEMPERATURE, °F
Figure 4b.- Variation of Izod impact strength wi~th temperature for l/2-inch-thick laminates.
Lengthwise speoimens tested flatwise.
440
400
Z
Ü aoo
i i- o z
tO
I-
i 2
2JÖ0
IjOO
S2CF'
S2LF
S1LE
SI S3 LF LE OF CE
SHEET 1/8-IffCH THIOK SHEET 1/2-IN0E THICK LENGTHWISE SPECIMENS TESTED FLATWISE LENGTHWISE SPECIMENS TESTED EDGEWISE CROSSWISE SPECIMENS TEST-ED FLATWISE CROSSWISE SPECIMENS TESTED EDGEWISE
si fc-
O
o
-70 0 77
TEMPERATURE, °F
200
Figure 5.- Variation of Izod impact strength with temperature for nigh-strength-paper phenolic laminate.
•=4
TO •
en
NACA TN No. 1054 Fig. 6
7.0
i t ID z
2
1.0
V2CE .x —— "•"• \/of r I V2LE
VI V2 LF LE OF CE
SHEET 1/8-INOH THIOK 8HEET l/2-INOH THIOK LENGTHWISE SPECIMENS TESTED FLATWISE LENGTHWISE SPECIMENS TESTED EDGEWISE CROSSWISE SPEOIMENS TESTED FLATWISE CROSSWISE SPECIMENS TESTED EDGEWISE
-70 77 200
TEMPERATURE, °F
Figure 6.- Variation of Izod impact strength with temperature for low-pressure grade C cotton-
fabric phenolio laminate. Mean value ± standard error is indicated by <J> or x.
NACA TN No. 1054 Fig. 7
7.0
i t x i-
tn
i.o
X-'-WlCE
Wl • SHEET 1/8-INOH THICK W2 « SHEET 1/3-INOH THICK LF = LENGTHWISE SPEOIMENS TESTED FLATWISE LE »= LENGTHWISE SPECIMENS TESTED EDGEWISE OF = CROSSWISE SPECIMENS TESTED FLATWISE CE = CROSSWISE SPECIMENS TESTED EDGEWISE
-70 77 200
TEMPERATURE, °F
Figure 7.- Variation of Izod impact strength with temperature for high-pressure grade C cotton-
fabric phenolic laminate. Mean value x standard error is indicated by § or x.
NACA TN No. 1054 Fig. 8
X
GO _1 ,i
X \- o z LÜ cr
15.0
10.0
5.0
—*"^Z2CF
.Z1LE
Zl SHEET 1/8-INCH THICK Z2 SHEET 1/2-INCH THICK LF LENGTHWISE SPECIMENS TESTED FLATWISE LE LENGTHWISE SPECIMENS TESTED EDGEWISE CF CROSSWISE SPECIMENS TESTED FLATWISE CE CROSSWISE SPECIMENS TESTED EDGEWISE
'-=-*-
-70 77 -200
TEMPERATURE, °F
Figure 8.- Variation of Izod impact strength with temperature for rayon-cotton-fabric
pnenolic laminate.
NACA TN No. 1054 Fig. 9
TYPE OF LAMINATE. ©RADE C PHENOLIC ASBESTOS-FABRIC PHENOLIC LOW-PRESSURE COTTON-FABRIC PHENOLIC HIGH-STRENGTH-PAPER PHENOLIC GLASS-FABRIC UNSATU RATED-POLYESTER LOW-PRESSURE GRADE C PHENOLIC HIGH-PRESSURE GRADE C PHENOLIC RAYON-COTTON-FABRIC PHENOLIC GLASS-FABRIC UNSATU RATED-POLYESTER
TEMPERATURE, °F
Figure 9.- Variation of flexural strength with temperature for 1/2-inch thick laminates. Lengthwise
specimens tested flatwise. Span-depth ratio 8:1.
* I
20
15
10
m TYPE OF LAMINATE
I GRADE C PHENOLIC K ASBESTOS-FABRIC PHENOLIC L LOW-PRESSURE CÖTTÜM-5ÄBRJC PHENQUG S HIGH-STRENGTH -PAPER PHENOLIC
. U GLASS-FABRIC UNSATURATED-POLYESTER V LOW-PRESSURE GRADE C PHENOLIC W HIGH-PRESSURE GRADE C PHENOLIC Z RAYON-COTTON-FABRIC PHENOLIC
AB GLASS-FABWC UNSATURATED-POLYESTER
Q > 1-9 fei
O
M O
•P*
*1
ZUSABILVWK ZUSABILVWK' ZUSABILVWK
-70°F 77°F 300°F figure 10.- Comparison of specific flexural strength of 1/S-inch-thick
laminates at three temperatures. Lengthwise specimens tested flatwise. Span-depth ratio 851.
NAOA TN No. 1054 Fig. 11
r\j.
^ 3.00
(O O
y
<
UJ
O if)
I o
_) <
•z.
2.50
2.00
150
1.00
.50
TYPE OF LAMINATE I GRADE C PHENOLIC
K ASBESTOS-FABRIC PHENOLIC L LOW-PRESSURE COTTON-FABRIC PHENOLIC S HIGH-STRENGTH-PAPER PHENOLIC U GLASS-FABRIC UNSATURATED-POLYESTER V LOW-PRESSURE GRADE C PHENOLIC W HIGH-PRESSURE GRADE C PHENOLIC Z RAYON-COTTON-FABRIC PHENOLIC
AB GLASS-FABRIC UNSATURATED-POLYESTER
-70 77 200
TEMPERATURE, ° F
Figure 11.- Variation of initial flexural modulus of elasticity with temperature for l/2-inch-
tnick laminates. Lengthwise specimens tested flatwise. Span-depth ratio 8:1.
aeo
a so
O40
020
TYPE OF LAMINATE
I GRADE C PHENOLIC K ASBESTOS-FABRIC PHENOLIC L LOW-PRESSURE COTTON-RöiBRiC PHENOLC
S HIGH-STRENGTH-PAPER PHENOLIC U GLASS-FABRIC UNSATURATED- POLYESTER V LOW-PRESSURE GRADE C PHENOLIC W HIGH-PRESSURE GRADE C PHENOLIC Z RAYON-COTTON-FABRIC PHENOLIC
AB GLASS-FäBRK; UNSATURATED-POLYESTER
as Je- O Se-
al o
M o Ol
s z u IABVWKL SZUIABVWKL SZUIABVWKL
-700F 77°F 200°F Figure 12.- Comparison of specific flexural modulus of elasticity of
l/2-incn-tnick laminates at three temperatures. Leng-fchwiee specimens tested flatwise. Span-depta ratio 8:1.1
H
Deflection
Figure 13.- Typical flexural load-dafleoUoa curves at -70°F obtained jiltTa. automatic stresB-straln recorder. OroBewiae specimens of glaee-fabrio laminate, U3,
tasted flatwise. Span-depth ratio 8:1.
at
•
01 if»
in
NACA TU No. 1054 Fig. 14
(M
40
CO en
Q CQ
30
20
TYPE OF LAMINATE I GRADE C PHENOLIC
K ASBESTOS-FABRIC PHENOLIC L LOW-PRESSURE COTTON-FABRIC PHENOLIC S HIGH-STRENGTH-PAPER PHENOLIC U GLASS-FABRIC UNSATURATED-POLYESTER V LOW-PRESSURE GRADE C PHENOLIC
W HIGH-PRESSURE GRADE C PHENOL.IC Z RAYON-COTTON-FABRIC PHENOLIC
AB GLASS-FABRIC UNSATURATED-POiyESTER
& •
u
AB /
z /. / /*
. 1
-w -—L
Im / r^^Z *S**?K\^ V
//•^ I/0& l/Z&^
.OS .10 .15 .20 .25
DEFLECTION AT MID-SPAN, IN.
Figure 14.- Flexural stress-deflection curves for 1/2- inch-thick laminates at 77°F. Lengthwise
specimens tested flatwise. Span-depth ratio 8:1.
NACA TN No. 1054 Fig. 15
«vi. Z
Id 2 Id CC i- X Id
.050 .100 .150 .200
DEFLECTION AT MID-SPAN, IN.
Figure 15.- Flexural stress-deflection curves for grade C cotton-fabric phenolic laminate, 12.
Lengthwise specimens tested flatwise. Span-depth ratio 8:1,
NACA TN No. 1054 Fig. 16
20 v'
/ >i
^S-IQ^Y.
/ ^ 11°Y.
M. z & 15 _J
O
to
a. \n
£ 10 OQ u_
. j /// ^^^200° F.
•// i / //
// s
/=^ y^
— // ?/
//
EX
TRE
ME
in
INI TIAL MODULI JS OF ELAST ICITY
-70°F: 1,640,000 PSI 77°F: 1,200,000 PSI
200°F: 1,220,000 PSI *
1 1 1 •025 .050 .075 JOO
DEFLECTION AT MID-SPAN, IN.
Figure 16.- Flexural stress-deflection curves for grade AA asbestos-fabric phenolic laminate, K2.
Lengthwise specimens tested flatwise. Span-depth ratio 8:1.
Mt
fr-
iz! O
O
.050 J00 J50 .200 ,
DEFLECTION AT MID-SPAN, IN.
.250
Figure 17.- Flexural stress-deflection ourves for low-pressure cotton- fabric phenolic laminate, L2. Lengthwise specimens tested
flatwise. Span-depth ratio 8:1.
NACA TN No. 1054 Fig. 18
* ä
cc ui CO
Ui 2 Ui cc
Q
025 .050 .075 .100
DEFLECTION AT MID-SPAN, IN.
Figure 13.- Flexural stress-deflection curves for high- strength-paper phenolic laminate, S2.
Lengthwise specimens tested flatwise. Span-depth ratio 8:1,
NAOA TN No. 1054 Fig. 19
70
60
«I. z
50
en </>
tr ÜJ m u. Lü
H
2
•40
30
20
10
j-70'F. t
/ ///irr-
•
/ yZOO'f.
INITIJ
—7
LL MODULUS
'OOF: 2,8' '?OF« 2,5$ )0°F: 1,8?
OF ELASTI
70,000 PSI 90,000 PSI 90,000 PSI
CITY
7 2C
.050 JOO .150 .200
DEFLECTION AT MID-SPAN, IN.
Figure 19.- Flexural stress-deflection curves for glass- fabric laminate "bonded with unsaturated
polyester resin, U2. Lengthwise specimens tested flatwise Span-depth ratio 8:1.
I fr» r
H S3
O
O
JO 50 400 JSO 200 2»)
DEFLECTION AT MID-SRAN, IN.
Figure 20.= Flexural stress-deflection curves for low-pressure gra&e 0 cotton-fabric phenolic laminate, 72. Lengthwise specimens
tested flatwise. Span-depth ratio 8:1.
CO o
NAOA TN No. 1054 Fig. 21
.050. JOO .150 .200
DEFLECTION AT MID-SPAN, IN.
Figure 21.- Flexural stress-deflection curves for high- pressure grade 0 cotton-fabric phenolic
laminate, 172. Lengthwise specimen tested flatwise, Span- depth ratio 8:1.
NACA TN No. 1054 Pig. 32
(VI. Z
_J
5
LÜ m
LÜ
LÜ CC h- Ö
40
35
30
25
20
IS
10
•
• *•/• •
V ^?
^>^
J^
INITIAL FLEXURAL FLEXURAL TOTAL _ rLECTION
IN.
0.16
0.25 ~
0.23
/^ MODULUS OF ELASTICITY STRENGTH DEI
LB/IN? LB/IN.*
-70* F 2,340,000 43,700
77* F
200* F
1,580,0«
l,160,0C
XI 34,
>0 2*,
400
a oo
.02 .04 .06 .08 40 .12
DEFLECTION AT MID-SFAN, IN.
14
Figure'S3.- Flexural stress-deflection curves for rayon- cotton-fäbric phenolic laminate, Z3.
Lengthwise specimens tested flatwise at three tempertures Span-depth ratio 8:1.
NAOA TK No. 1054 Fig. 33
CM.
ÜJ
I-
70
60
J£ SO
LÜ
40
30
20
10
/
/
j^
^ INITIAL
MODUUUS
L
-70* F
77* F
200*F
FLEXURAL
OF ELASTIC
.B/IN?
3,150,<
2,680,1
2*80,1
FLEXURAL Tl
ITY STRENGTH DCFI
LB/IN?
MO 70,500
900 53*200
300 33,000 •
OTAL
LECTION
IN.
ai2
0.11
008
.02 J04 .08 JOS .10
DEFLECTION AT MID-SFAN, IN. .12
Figure 23.- Flexural stress-deflection curves for glass- fabric laminate, ABS. Lengthwise specimens
tested flatwise. Span-depth ratio 8:1.
LF » LENGTHWISE SPEOIMENS TESTED FLATWISE
LE = LENGTHWISE SPEOIMENS TESTED EDGEWISE
OF = CROSSWISE SPECIMENS TESTED FLATWISE
CE m CROSSWISE SPECIMENS TESTED EDGEWISE
IV. Z
m c/)
u a. ui OD
u u I- 2
Q
o
It*
DEFLECTION AT MID-SPAN, IN. i
Figure 24.- Flexural atresa-deflection curveB for aabeatOB-fabric phenolic laminate, K2, at ?7°F. Span-depth ratio 8:1. to
1. z 50
30
LF * LENGTHWISE SPECIMENS O TESTED • ** FLATWISE $
LE - LENGTHWISE £ SPECIMENS i= TESTED * EDGEWISE cc
OF - CROSSWISE £ SPECIMENS 5 TESTED FLATWISE
CE « CROSSWISE SPECIMENS TESTED EDGEWISE
Id 20 2 id oc H
5=j
Q
o
en
DEFLECTION AT MID-SR\N, IN.
Figure 35.- Flexural stress-deflection curves for glaBs-fabrlc laminate bonded with uneaturat«d polyester resin, U2,
at 77°J. Span-depth, ratio 8:1.
TO
10 01
NAOA TN No. 1054 Fig. 26
35
2 25
in UJ CC 20
CO
15
LJ OC I- X Ld
10
^
»*T -
^oaees^
• s •
FLEXURAl STRENGT»
LB/IN?
34,400
32.700
18.900
y^ 1 X MOD*
LENG
NITIAL FLEXURAL JLUS OF ELASTICITY
LB/IN*
iTHWISE 1,580,000
TOl A DEFLE
1
0.
0.
0.
'AL CTKDN N.
25
r
CROS
45* C
SWISE
>IAGONAL
1,400,000
780U0OO
25
28
.05 JO .15 .20 .25
DEFLECTION AT MID-SPAN, IN.
.30
Figure 26.- Flexural stress-deflection curves for rayon- cotton-fabric phenolic laminate, Z2, tested
flatwise at 77°F. Span-depth ratio 8:1.
NACA TN Ho. 1054 Fig. 37
«,
O
ft
LÜ
UJ Q: I- Ö
60
50
40
30
20
10
INITIAL FLEXURAL
MODULUS OF ELASTICITY
LB/IN.*
LENGTHWISE 2,880.000
CROSSWISE 2,84.0,000
45* DIAGONAL L810,000
FLEXURAL TOTAL
STRENGTH DEFLECTION
LB/JN.* IN.
53,200 0.11
46,000 0.10
35,700 0.35 y
.04 .06 .08 \Q iZ
DEFLECTION AT MID-SPAN, IN.
Figure 37.- Flexural stress-deflection curves for glass- fabric laminate, ABS, tested flatwise at 77°F.
Span-depth ratio 8:1.
rapfsne» (BICHT) R-8-2-14 Lamb, J. J. DIVISION: Materials (8) Albrecht, I. SECTION: Plastics (2)
«OSS REFERENCES: Plastic materials (71942); Materials, Laminated (60600); Strength of materials (90750);
AUTHOR(S) II Plastics - Testing (71962);
UXSh 8007 ORIG. AGENCY NUMBER
TN-1054
REVISION
AMER. TITLE: impact strength and flexural properties of laminated plaetics at high and low temperatures
FORG'N. TITLE:
ORIGINATING AGENCY:
TRANSLATION:
National Advisory Committee for Aeronautics, Washington, D.C.
COUNTRY U.S. Eng.
LANGUAGE FO*G'N.CL*SS U SJCL'SS.
Pnclass. DATE
Aug'46 PAGES
58 IUUS.
38 FEATURES
photos, tables, graphs
Izod-impact atrength and flexural properties of uneaturated-polyester laminates rein- forced with glass fabric and of phenolic laminates reinforced with aebestos fabric, high- strength paper, rayon or cotton fabric were determined at temperatures from -70° to 200°F. Impact strength of specimens tested flatwise at 77°F was 4-7 ft/lb per in. of notch for all laminates, except those of glass fsbric and rayon fabric. Flexural strengths and moduli of elasticity of all materials increased with change in test temperature. At 200°F, all materials, except asbestos fabric laminate, lost 30 to 40^ of their flexural strength. * Plastics - Phyaical properties (71959.5)
NOTE: Requests for copies of this report must be addreseed to: N.A.C.A.,Washington,P.C.
AIR "CECHNICAL DNOEX WRIGHT FIELD, OHO. USAAF HfeO-31 «Aft 47 aa
T-J, HQ„ AIR MATERIEL COMMAND
