EXPERIMENTAL RESEARCH AND FINITE ELEMENT ANALYSIS OF ELASTIC AND STRENGTH PROPERTIES OF FIBERGLASS COMPOSITE MATERIAL

Nekliudova E.A.; Semenov A.S.; Melnikov B.E.; Semenov S.G.

Experimental research and finite element analysis of elastic and strength properties of fiberglass composite material

Undergraduate E.A. Nekliudova;

PhD, Associate Professor A.S. Semenov;

Dr.tech.sci., Head of Department B.E. Melnikov;

Engineer S.G. Semenov;

Saint-Petersburg State Polytechnical University

Abstract. This work is devoted to the research of the strength and elastic properties of the laminated fiberglass composite. Experiments were performed on tension and compression of specimens with different orientation of the reinforcement in relation to the loading direction. The predictions of three different failure criteria (Hill criterion, Tsai-Wu criterion, Zakharov criterion) were compared to experimental results.

The strength and elastic properties of the composite separate components have been also researched with the aim to perfom finite element simulation of composite failure process. The elastic moduli of the composite are determined by means of the method of the finite element homogenization.

Key words: laminated composite; fiberglass material; experiment; elastic properties; strength; orientation of the reinforcement; failure criteria; orthotropic material; finite-element method

Introduction

High strength, light weight, durability and affordability of modern composite materials make it possible to replace traditional, natural and man-made materials in all areas of life: in construction and reconstruction [1-3], mechanical engineering, shipbuilding, aerospace engineering. There are a lot of compositions of fibers [4] and matrixes [5]. However, correct analysis of strength and durability of construction elements made of composite materials requires development and application of new, complex criteria and their experimental verification. Various strength criteria and their comparison with experimental data for anisotropic composites are given in [6-9]. Modern literature is focused on the Tsai-Wu criterion. In this paper we consider three criteria - Hill, Tsai-Wu and Zacharov. Zacharov criterion has not been considered in modern literature and its predictions have not been compared with experimental data. Computation of elastic properties of composite materials is another problem of composite materials mechanics. Methods to determine effective elastic moduli of anisotropic materials by homogenization are considered in [10-12]. A finite-element homogenization method can be applied to anisotropic materials, One of the main problem of this method is how to determine the representative volume element correctly. In this work we consider a layered fiberglass composite, belonging to the orthotropic materials class. In reconstruction of a power plant pipeline that has lost its cross-section circular form because of long-term weight loads of overlying layers of soil [13], a problem rose related to obtaining properties of composite when strengthening the pipeline walls with this material.

The composite under study has a laminate structure, which represents an alternation of fiberglass fabric and epoxy resin. In this composite the fiberglass fabric T-23 made by TU 6-48-53-90 [14] is used. Properties of this fabric are presented in Table 1. Thickness of one layer of composite (fiberglass fabric + epoxy resin) is 1 mm. Fabric T-23 has a plain weave. The warp and weft are perpendicular to each other. Each layer of fiberglass fabric is placed evenly in manufacturing the composite.

Table 1. Basic properties of the fiberglass fabric [14]

Parameter Value

Density (number of yarns per 1 cm) along the warp 13±1

Density (number of yarns per 1 cm) along the weft 7±1

Fiber width, mm 1.05

Fiber thickness, mm 0.12

Surface density of the fabric, g/m2 285±25

The composite is considered an orthotropic material [15, 16]. Its elastic and strength properties depend on direction, but are symmetrical with respect to orthotropy axes 1, 2, 3 (Figure 1). Axes 1 and 2 coincide with directions of the warp and weft. In general, orthotropy axes do not coincide with global

Nekliudova E.A., Semenov A.S., Melnikov B.E., Semenov S.G. Experimental research and finite element analysis of elastic and strength properties of fiberglass composite material 25

coordinates of the composite x, y, z. The stresses in the plane of reinforcement in the orthotropy axes and global coordinate system are interconnected in the following way [14]:

о 1 = ax cos2 ф + оy sin2 ф + Txy sin 2ф

о2 =ax sin2 ф + ay cos2 ф-ту sin2ф,

T12 = (<y - <x )cos ^ sin ^ + Txy cos 24, where <p is an angle between the warp and axis x.

(1)

Figure 1. Orthotropy axes of the laminated fiberglass composite [17]

Failure Criteria for Orthotopic Materials

The problem discussed in this section concerns evaluation of laminate load-carrying capacity [18, 19]. The failure criterion allows determining ultimate stresses that cause the composite fracture. Generally, failure criteria for an orthotropic material can be written in a compact form [20-22]:

F 0 Tj ) = 1 ■

(2)

where <,Ty are components of the stress tensor written in the orthotropy axis. The composite works if

F < 1 and fails if F = 1. It does not exist as a load-carrying element if F > 1.

The criteria considered in this paper will be written for a composite in a plain stress state. It allows comparing the predictions of different criteria with the experimental results.

Hill Failure Criterion We write the generalized von Mises criterion (square criterion)[19]:

s ••4V-s = 1, (3)

where s is a deviator of the Cauchy stress tensor, 4 V is a tensor of 4th rank constants.

The generalized von Mises criterion recorded for an orthotropic material is the Hill failure criterion.

For an orthotropic material in plane stress state the Hill criterion, recorded in the orthotropy axis, is the following [22]:

_2 2 f

О+0 -— 2 —2

'1

2

1 1

-г + —;

1

Л

a

'3 J

T2 i

О\0 2 +=2 = 1,

T12

(4)

where oi,rtj are ultimate (limiting) stresses determined experimentally.

It is assumed that the strength of the composite in direction 3 and in the direction at the angle of 45° to the warp is determined by the strength of the composite isotropic matrix, i.e. destruction occurs in

these areas at the same critical value of stress, it is denoted as cT . Let cT be a certain critical stress intensity. Then we have this relation:

aT =V3r12,

then we find:

T2 =

45°

л/Т

(5)

(6)

Dependence of the limiting stress on the direction of the applied load can be obtained from the Hill failure criteria. Let us now consider the case of uniaxial tension. Let the load be applied along the x-axis. Angle ( is the angle between the applied load and warp. After we substitute into (4), the formula for the stresses (1) and take into account (5) and (6), we obtain the following dependence:

4 =

cos4 m sin4 m

-:т- +-:r~ +

f

1 1

Л

A

cos2 ^sin2 ф

(7)

The equation (7) shows dependence of the limiting stress on the angle between the applied load and warp. Since this dependence is based on the Hill failure criterion, the sign of the applied load is not

taken into account. This is also true for tension and compression. The values of a, are taken from a tensile experiment.

Tsai-Wu Failure Criterion

Let us consider the Tsai-Wu tensor-polynomial criterion [20]:

or, in the index form:

W1 -о + о •• W2-o = 1,

+ = 1 U J = 1,(6

(8)

(9)

Tsai-Wu criterion takes into account the sign of the applied load, because it contains linear summands on^. Let us rewrite the criterion (9) for the orthotropic material in plane stress conditions [23, 24]:

Fiai + F2a2 + F1iai2 + F22a22 + F12aia2 + F66TU = 1.

The constants for Tsai-Wu criterion are defined as follows:

(10)

Fl F, =4-

G1t 41c 42t

1

2c

Fu =■

1

F22 = — — , F12 4F11F22 , F12 — 2

42t42 c

(11)

where index t is tension, index c is compression.

To obtain the dependence of the limiting stress on the direction of the applied load, we substitute in (10) the expression (1). c =Txy = 0. As result we obtain the equation for Ccx :

Aöl + B4 = 1,

(12)

where

4 4 { \ 2 2

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A = F11 cos < + F22 sin < + ( 2FJ2 + F66) cos <sin

2 • 2 (13)

B = F1 cos < + F2 sin

When solving (12) with respect to cX , we get two expressions of limiting stress on angle $ between the applied load and warp:

_ -B -V B2 + 4 A

cxc =-for compression.

2 A

__(14)

_ -B W B2 + 4 A

crrf =-for tension.

2 A

Thus, on the basis of the Tsai-Wu criterion that takes into account the direction of the applied load, we obtain two different expressions of the limiting stress on the direction of the applied load.

Zakharov Failure Criterion The Zakharov criterion is a special case of the Gol'denblat-Kopnov criterion [25]:

(n ik Cik Y + (n pqnmcpqcnm f + (n rstlmnC rsC tlC nm )" + ... = 1 (15)

If in (15) we get only the first two invariants and put a = ft = 1, we obtain the Zakharov criterion. The Zakharov criterion for orthotropic material in the plane stress state has the following form [22]:

c12 + Ac22 + Bc1c2 + Cc1 + Dc2 + E = 0. (16)

Constants for the Zakharov criterion are defined as follows:

A = , B = -1 -A-4

fa ^

E + (C + D )

a2°

45°

, C = (aic -ait ) >

(17)

D = A (a2c -a2t ) > E = -aicaii

The Zakharov criterion, like the Tsai-Wu criterion, considers the sign of the applied load, but does not take into account the shear stress impact. Expressions for the limiting stress on the direction of the applied load are similar to the Tsai-Wu criterion:

_ -N -V N2 + 4ME

c =- for compression.

xc 2M

_ (18)

_ -N WN2 - 4ME

C , =-for tension.

2M

where M = cos4 $ + A sin4 $ + D cos2 $sin2 $, N = B cos2 $ + C sin2 $.

Experimental research of elasticity and strength properties of the

composite

Elasticity and strength properties of individual components of the composite

Determination of the elastic moduli and limiting stress of individual components of the composite is required to perform finite element analysis research of the elementary representative volume (RVE) of the composite. To determine the elastic moduli of the material components, tensile strength experiments on epoxy resin and glass fiber have been performed.

For the experiments, samples were made from the same epoxy resin as the one used in the composite. Sample sizes were 25*10x250 mm. The loading test was carried out on the Instron 8801 machine at the rate of 2 mm/min. Deformations were measured with an Instron 2620-603 strain gauge transducer, which was fixed to the broad side of the sample. As a result of the experiments, a stressstrain diagram was obtained for the epoxy resin (see Fig. 2), the Young's modulus was calculated and the limiting stress was defined (see Table 2). For each of the defined values the mean square deviation was calculated:

8 =

1 V i

- v \Xj - x) ni=1

-\2

(19)

where n is the number of experiments, xt is the measured value, x is the expectation (mean) value of the measured values.

Table 2. Outcome of epoxy resin tensile strength experiment

a, MPa E, MPa

Sample №1 49.2 3907

Sample №2 41.3 3669

Sample №3 52.2 3131

Expected value 47.6 3569

5 4.6 325

60 50

Ö 40 CLh

^ 30 b

20 10

"0 0.5 1 r. , 1.5 2 2.5

£, %

Figure 2. Stress-strain diagram of the epoxy resin

Additional experiments on tensile strength of samples were performed to determine the epoxy resin Poisson coefficient. The result for the epoxy resin is v = 0.2.

To determine properties of the glass fibric, extracted from fabric T-23, tensile strength experiments of glass yarns were performed. The ends of fiber were fanged with epoxy resin to place them into the grips of the testing machine. The length of the yarns outside the grips was 100 mm. A loading test was carried out on an Instron 5965 machine. The experiments resulted in obtaining a stress-strain diagram for glass yarn (see Fig. 3), calculating the Young's modulus and defining the limiting stress (see Table 3).

Table 3. The Results of Experiments on Glass Yarn Tensile Strength

G, MPa Е, MPa

Sample №1 1300 60

Sample №2 1610 80

Sample №3 756 70

Expected value 1222 70

5 353 8

£, %

Figure 3. Stress-strain diagram of glass yarn

In further calculations we will accept the value of the glass Poisson coefficient as the glass fabric Poisson coefficient v = 0.23 .

Experimental research of elasticity and strength properties of the composite material

Experiments were performed on tension and compression of fiberglass composite material samples at angles of 0°, 15°, 30°, 45°, 60°, 75°, 90° to the warp yarns, on an Instron 8801 testing machine, according to GOST 25.601-80 [26] and GOST 25.602-80 [27]. Deformations were measured with an Instron 2620-603strain gauge transducer. Samples for tension had size 25*10*140 mm, the size of samples for compression was 25*10*250 mm. Stress-strain diagrams were obtained for tension and compression (see Fig. 4, 5), Both Young's moduli were calculated and the maximum values of stress

cmax and limiting values of stress, c , at which the material is destroyed, were defined (see Table 4, 5).

90 SO 70

S 60

^ 50 40

30 20

10

°0 1 23456789 10

Figure 4. Stress-strain diagram of the composite in tension at different angles to the warp

100 90 80 70

CL, 60 §

^ 50 fc 40

30 20

10

°0 1 2 3 4 5 6 7 S

Figure 5. Stress-strain diagram of the composite in compression at different angles to the warp

Table 4. Result of experiments on composite tensile strength at different angles to the warp

Angle between warp and applied load 0° 15° 30° 45° 60° 75° 90°

<7 , MPa 96.88 85.67 64.37 48.24 57.39 64.47 65.32

—_ max _ _ _ <7 , MPa 96.88 85.67 66.30 55.54 59.41 64.47 65.32

E, MPa 8308 5861 4539 3585 3969 4723 5427

Table 5. Result of experiments on composite compression strength at different angles to the warp

Angle between warp and applied load 0° 15° 30° 45° 60° 75° 90°

7, MPa 93.72 84.33 83.46 50.84 57.09 67.48 68.02

—_ max _ _ _ 7 , MPa 93.72 84.33 83.46 71.33 77.56 67.48 68.02

E, MPa 7533 7667 5514 4627 5492 5526 12478

Photos of the broken samples are shown in Figures 6, 7.

Figure 6. Samples broken under tension at angles 75° (above) and 45° (below) to the warp

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Figure 7. Samples broken under compression at angles (from top to bottom) 45°, 60°, 75°

to the warp

is

Under tension the value of the limiting stress is o, the maximum stress

omax and Young's modulus reaches the highest value with loading along the warp. The minimum values

of the limiting stress o , the maximum stress omax and the Young's modulus are observed under loading at the angle 45° to the warp yarns. It should be noted that under this loading the sample breaks at the stress of 48.24 MPa, which is almost exactly the same as the tensile strength of the epoxy resin.

The character of deformation diagrams varies depending on the type of loading. At 0°, 15°, 75° and 90° angles of loading the values of limiting and maximum stresses coincide. When a load is applied at 30°-75° angles these values differ. The form of the deformation diagram also varies: after reaching its maximum value, the stress begins to decrease, yield is reached and the highest values of deformation are obtained.

The fracture pattern is the same in all the cases: first, the epoxy resin breaks, then the fiberglass fabric is torn.

Under compression the maximum value of the Young's modulus is observed in compression across the warp, and this value is higher than the one for tension. The values of the limiting stress and the maximum stress reach their maximum level under the loading along the warp. The minimum value of the ultimate stress o is reached under the loading at the angle of 45° to the warp. This value is close to

the ultimate strength of the epoxy resin. But the value of the maximum stress omax increases compared to the tensile strength experiment. This may be due to the fact that under compression the bearing capacity of the sample is lost as a result of delamination of the material rather than complete destruction

of the matrix, as it happens in tension. The minimum experimental value of omax is reached under the loading at the angle of 75° to the warp yarns. The Young's modulus, as in the tensile strength experiment, is minimal at the angle of 45 ° to the warp.

The pattern of stress-strain diagrams is the same as the one in tension. Absence of yield plateau in the diagrams for compression at the angle of 30° may be caused by premature stopping of the experiment.

The mode of destruction is same in all the cases of compression: there is a local matrix and glass fiber delamination with the subsequent buckling of the yarns.

Comparison of Failure Criteria Predictions with Experimental Data

To estimate how well the Hill, Tsai-Wu and Zakharov failure criteria predict the limited stress, we plotted relations (7), (13) and (18). Depending on what kind of experimental data will be substituted into

the formula, we obtain dependence of the limiting stress o or maximum stress crmax on the angle between the applied load and the warp [28]. Plotted dependences are presented in Figures 8, 9. Experimental data points are plotted on graphs too.

Experimental results and results obtained on the basis of various criteria are shown in Tables 6, 7. For each criterion, the mean square deviation was counted from the experiment.

Table 6. Comparison of the limiting stress obtained according to various criteria and experimental data

Value, MPa Experiment Hill criterion Tsai-Wu criterion Zakharov criterion

G1t 96.88 96.88 96.88 96.88

G1c 93.72 96.88 93.72 93.72

G t 85.67 74.55 78.09 74.77

G c 84.33 74.55 76.40 73.217

G 30° t 66.30 54.80 59.09 54.93

30 c 83.46 54.80 58.71 54.60

G 45° t 48.24 48.24 52.04 48.24

G45° c 50.84 48.24 52.39 48.54

G60° t 57.39 50.20 53.25 50.11

G60° c 57.09 50.20 54.32 51.05

G75° t 64.47 58.66 60.17 58.57

G 75o c 67.48 58.66 62.21 60.50

G2t 65.32 65.32 65.32 65.32

G2c 68.02 65.32 68.02 68.02

5 - 10.03 7.89 9.94

Table 7. Comparison of the maximum stress obtained according to various criteria and experimental data

Value, MPa Experiment Hill criterion Tsai-Wu criterion Zakharov criterion

max 96.88 96.88 96.88 96.88

^max a1c 93.72 96.88 93.72 93.72

max 85.67 80.70 83.21 80.87

max 15 c 84.33 90.67 88.70 88.45

—_max 66.30 62.77 66.33 62.89

max 30 c 83.46 79.54 79.45 78.91

max 1 55.54 55.54 58.73 55.54

max G A V 45 c 71.33 71.33 72.53 71.99

max CT60-1 59.91 56.10 58.45 56.02

max 60o c 77.56 67.11 69.14 68.79

—_max 64.47 61.52 62.49 61.45

max 75 o c 67.48 65.61 68.13 68.01

max a2t 65.32 65.32 65.32 65.32

max CT2c 68.02 65.32 68.02 68.02

8 - 4.19 3.05 3.53

According to the results of all the experiments the smallest mean square deviation is observed in the Tsai-Wu criterion, which takes into account the sign of the applied load and influence of shear stresses.

The premature stopping of the experiment on compression at the angle of 30° to the warp explains a sufficient error for „ .

30 c

Figure 8. Dependence of limiting stress on the direction of the applied load

for compression and tension

Figure 9. Dependence of maximum stress on direction of the applied load for compression and

tension

Results of Finite Element Modeling

The finite element model of the representative volume element of the composite is shown in Fig. 10, 11. For this, the composite representative volume element is a single cell of plain weave [10, 29]. Parameters of the model are presented in Tables 8, 9. The material properties are specified from the experimental results.

Figure 10. Finite element model of the representative volume element of the laminated fiberglass composite

Table 8. Parameters of the FE-model

Figure 11. Plain weave within the representative

volume element of the laminated fiberglass composite (red yarn is warp, blue yarn is weft)

Table 9. Material properties

Parameter Value

Element type Solid

Number of elements 20867

Number of nodes 73671

Number of DOFs 221013

Material Material E, MPa

Epoxy Isotropic 3569 0.20

Glass yarn Isotropic 70-103 0.23

So as to calculate the elastic moduli of the composite, numerical experiments were performed on the representative volume element under tension in three main directions, and under shear in three planes. The stresses and strains are calculated by averaging over the elementary volume [30]:

<o> = V V odV, (20)

>>=V i>sdv • (21)

Nekliudova E.A., Semenov A.S., Melnikov B.E., Semenov S.G. Experimental research and finite element analysis of elastic and strength properties of fiberglass composite material 35

where V is the volume of the representative volume element.

Examples of stress and strain field distributions are shown in Figures 12,13.

Figure 12. The distribution of stress field o2 under tension along the weft

Figure 13. The distribution of the strain field s2 under tension along the weft

If we use finite element homogenization, we obtain 9 elastic constants of the composite. The results are presented in Table 10.

Table 10. Elastic moduli of the composite obtained by the finite element homogenization

Constant Value

Eii 8417 MPa

E 22 5511 MPa

E 4257 MPa

V12 0.160

V13 0.217

V23 0.225

G12 2356 MPa

G13 1764 MPa

G23 1797 MPa

Since the composite under consideration belongs to the orthotropic materials class we have the following dependence on direction for its Young's modulus [14]:

E, =

cos4 $

E,,

f

+

1

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V G12

V

E

\

cos2 $sin2 $ +

11J

sin4 $ E.

22

(22)

To check consistency of the results, obtained through finite element computations, with

experimental data, we plot the dependence of Young's modulus Ex of the angle between the warp and

the x-axis. We substitute in (22), the data from table 10 and compare the results with the experiment. For each value of the Young's modulus the error is calculated by formula:

A =

E v E v

Ev

•100%,

(23)

where Ex is FE-modeling results, EXe is experimental results. The results are presented in Table 11 and in Figure 14.

Table 11. Comparison of the Young's modulus depends on the angle between the x-axis and the warp yarn, and is done with the data from FE-calculation and experiment

FE

E

Value Experiment, MPa FE-calculation, MPa A, %

E„ 8308 8417 1.31

E15° 5861 5944 1.42

E 30° 4539 4167 8.20

E5 3585 3647 1.73

E 60° 3969 3867 2.57

E75° 4723 4747 0.51

E ^22 5427 5532 1.93

-FE-calculation

* Experimental data

Figure 14. Comparison of the experimental and FE-homogenized Young's modulus for different

angles between the x-axis and the warp yarn

The comparison is made with the tensile strength experiment, as neither dependence (22), nor built model take into account the differences between properties of the material in tension and compression. Results of the FE computation demonstrate satisfactory consistence with the experiment. When comparing it should be noted that the properties of epoxy resin and glass fiber, defined in the finite element model, have been determined experimentally, which could affect the accuracy of calculation. It should be also taken into account that the experimental data may differ slightly from the actual properties of the composite.

Conclusions

1. Experiments for determination of the ultimate (limit) stresses in tension and compression for different orientations of the load direction with respect to the warp yarns have been made on the laminated fiberglass composite specimens. There is a pronounced anisotropy of the mechanical properties and their sensitivity to the stress form (the difference in tension and compression).

2. Dependences of limiting stresses on the angle between the load application and warp yarns is obtained based on various failure criteria. There is a decrease of limiting stresses when load is applied to the corners at the range of 30-60 ° caused by redistribution of load between the matrix and the reinforcement to the side increasing the load on the epoxy resin. The criteria considering the effect of the first invariant of stress (Tsai-Wu and Zakharov) can predict more accurately the strength of the material at the entire range of loads (both in tension and in compression). However, more experiments are required to identify the constants.

3. The finite element model of the representative volume element of the composite has been proposed. The effective elastic properties of the composite have been determined with the use of the finite element analysis. The simulation results coincide satisfactorily with the experimental data. Further improvement of the model will allow determining in the future the properties of the composite without complex, lengthy and costly experiments.

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Ekaterina A. Nekliudova, St.-Petersburg, Russia +7(921)9253778; e-mail: nekludik@mail.ru

Artem S. Semenov, St.-Petersburg, Russia +7(905)2721188; e-mail: Semenov.Artem@googlemail.com

Boris E. Melnikov, St.-Petersburg, Russia +7(812)5526303; e-mail: kafedra@ksm.spbstu.ru

Sergey G. Semenov, St.-Petersburg, Russia +7(921)9834456; e-mail: ssgrus@gmail.com

doi: 10.5862/MCE.47.3

Experimental research and finite element analysis of elastic and strength properties of fiberglass composite material

Undergraduate E.A. Nekliudova

Saint-Petersburg State Polytechnical University, Saint-Petersburg, Russia

+79219253778; e-mail: nekludik@mail.ru PhD, Associate Professor A.S. Semenov Saint-Petersburg State Polytechnical University, Saint-Petersburg, Russia +79052721188; e-mail: Semenov.Artem@googlemail.com Dr.tech.sci., Head of Department B.E. Melnikov Saint-Petersburg State Polytechnical University, Saint-Petersburg, Russia

+78125526303; e-mail: kafedra@ksm.spbstu.ru Engineer S.G. Semenov Saint-Petersburg State Polytechnical University, Saint-Petersburg, Russia

+79219834456; e-mail: ssgrus@gmail.com

Key words

laminated composite; fiberglass material; experiment; elastic properties; strength; orientation of the reinforcement; failure criteria; orthotropic material; finite-element method

Abstract

This work is devoted to the research of the strength and elastic properties of the laminated fiberglass composite. Experiments were performed on tension and compression of specimens with different orientation of the reinforcement in relation to the loading direction. The predictions of three different failure criteria (Hill criterion, Tsai-Wu criterion, Zakharov criterion) were compared to experimental results.