Research Article  Open Access
Salvatore Brischetto, "ThreeDimensional Exact Free Vibration Analysis of Spherical, Cylindrical, and Flat OneLayered Panels", Shock and Vibration, vol. 2014, Article ID 479738, 29 pages, 2014. https://doi.org/10.1155/2014/479738
ThreeDimensional Exact Free Vibration Analysis of Spherical, Cylindrical, and Flat OneLayered Panels
Abstract
The paper proposes a threedimensional elastic analysis of the free vibration problem of onelayered spherical, cylindrical, and flat panels. The exact solution is developed for the differential equations of equilibrium written in orthogonal curvilinear coordinates for the free vibrations of simply supported structures. These equations consider an exact geometry for shells without simplifications. The main novelty is the possibility of a general formulation for different geometries. The equations written in general orthogonal curvilinear coordinates allow the analysis of spherical shell panels and they automatically degenerate into cylindrical shell panel, cylindrical closed shell, and plate cases. Results are proposed for isotropic and orthotropic structures. An exhaustive overview is given of the vibration modes for a number of thickness ratios, imposed wave numbers, geometries, embedded materials, and angles of orthotropy. These results can also be used as reference solutions to validate twodimensional models for plates and shells in both analytical and numerical form (e.g., closed solutions, finite element method, differential quadrature method, and global collocation method).
1. Introduction
Exact solutions for the threedimensional analysis of plates and shells have been developed by several researchers. In particular, threedimensional static and dynamic analysis of cylinders and cylindrical/spherical shells has received considerable attention in the past few years. The development of plate and shell elements highlights the importance of research on the design of these geometries because they are fundamental for the analysis of general structures in the engineering field. For this reason, plate and shell elements need accurate validation. Threedimensional exact solutions allow such validations and checks to be made, and they also give further details about threedimensional effects and their importance. In the literature, works about exact threedimensional solutions analyze separately the various geometries and they do not give a general overview of plate and shell elements. The present paper aims to fill this gap by proposing a general formulation for the equations of motion in orthogonal curvilinear coordinates that is valid for square and rectangular plates, cylindrical shell panels, spherical shell panels, and cylinders. A general overview is given for those readers interested in both plate and shell analysis. This paper exactly solves the equations of motion in general curvilinear orthogonal coordinates including an exact geometry for shell structures without simplifications. To the best of the present author’s knowledge, this is the first time that this solution is proposed by means of the exponential matrix method for the threedimensional elastic free vibration analysis of plates and shells.
The next paragraph discusses the most relevant works about threedimensional shell analysis. Chen et al. [1] exactly studied the coupled free vibrations of a transversely isotropic cylindrical shell embedded in an elastic medium. The behavior of the cylindrical shell was analyzed based on threedimensional elasticity and three displacement functions were chosen to represent three displacement components to decouple the threedimensional equations of motion of a transversely isotropic body. Fan and Zhang [2] presented the exact solutions for statics, dynamics, and buckling of thick open laminated cylindrical shells by means of the CayleyHamilton theorem. The state equation for orthotropy was established in a cylindrical coordinate system without any assumption about displacement models and stress distribution. Gasemzadeh et al. [3] studied free vibrations of cylindrical shells on the basis of threedimensional exact theory. Simply supported boundary conditions were studied and extensive frequency parameters were obtained by solving frequency equations. The free vibrations of simply supported crossply cylindrical and doubly curved laminates were investigated in [4]. The threedimensional equations of motion, expressed in terms of displacements, were reduced to a system of coupled ordinary differential equations, that were solved using the power series method. Sharma et al. [5] studied the threedimensional free vibrations of a homogenous isotropic, viscothermoelastic hollow sphere whose surfaces were subjected to stressfree, thermally insulated or isothermal boundary conditions. The governing partial differential equations were solved into a coupled system of ordinary differential equations. Fröbenious matrix method was employed to obtain the solution. The same method was also used for the exact threedimensional vibration analysis of a transradially isotropic, thermoelastic solid sphere [6]. Soldatos and Ye [7] proposed exact, threedimensional, free vibration analysis of angleply laminated cylinders. Results were presented and discussed for relatively thick cylinders having a regular symmetric or a regular antisymmetric angleply layup. Armenakas et al. [8] proposed a selfcontained treatment of the problem of plane harmonic waves propagation along a hollow circular cylinder in the framework of the threedimensional theory of elasticity. The results presented frequencies of free vibrations of such cylinders for a wide range of axial and circumferential wavelengths and of shell dimensions. An interesting comparison between frequencies obtained from a refined twodimensional analysis, a shear deformation theory, the Flügge theory, and an exact elasticity analysis were proposed in [9]. Further details about the Flügge classical thin shell theory concerning the free vibrations of cylindrical shells with elastic boundary conditions can be found in [10]. Other comparisons between twodimensional closed form solutions and available exact 3D elastic and analytical solutions for the free vibration analysis of simply supported and clamped homogenous isotropic circular cylindrical shells were also proposed in [11]. Exact elasticity solutions were extended to functionally graded cylindrical shells in [12]. The threedimensional linear elastodynamics equations, simplified to the case of generalized plane strain deformation in the axial direction, were solved using suitable displacement functions that identically satisfy the boundary conditions. Loy and Lam [13] proposed a layerwise approach to study the vibration of thick circular cylindrical shells on the basis of threedimensional theory of elasticity. The governing equation was obtained using an energy minimization principle. Another interesting extension was proposed by Wang et al. [14], who investigated the free vibrations of magnetoelectroelastic cylindrical panels based on the threedimensional theory. Further results about threedimensional analysis of shells that are not given in closed form were shown by Efraim and Eisenberger [15] for the dynamic stiffness matrix method and by Kang and Leissa [16] and Liew et al. [17] for the threedimensional Ritz method for vibration of spherical shells.
Threedimensional analysis of plates is usually performed by using simpler equations that do not allow the analysis of shell geometries. Demasi [18] proposed a Naviertype method for finding the exact threedimensional solution for isotropic thick and thin rectangular plates. The method used the mixed form of Hooke Law to write the boundary conditions on the top and bottom surfaces of the plate directly in terms of transverse stresses. Aimmanee and Batra [19] proposed an analytical solution for free vibrations of a simply supported rectangular plate made of an incompressible homogeneous linear elastic isotropic material. Some frequencies missing in previous analytical solutions for plates made of compressible materials were identified. Some of the inplane modes of free vibration of a simply supported rectangular plate that were missed in previous exact solutions were also proposed in [20]. A threedimensional linear elastic, small deformation theory obtained by the direct method was developed for the free vibration of simply supported, homogeneous, isotropic, thick rectangular plates in [21]. The same method was used in [22] for the flexure of simply supported homogeneous, isotropic, thick rectangular plates under arbitrary loading. This solution, in terms of infinite series, was formally exact and yielded accurate numerical results without undue effort. Useful comparisons between twodimensional models and an exact threedimensional solution for the free vibrations of a simply supported rectangular orthotropic thick plate are shown in [23]. On the basis of threedimensional elasticity, Ye [24] presented a free vibration analysis of crossply laminated rectangular plates with clamped boundaries. The analysis was based on a recursive solution suitable for threedimensional vibration analysis of simply supported plates. Comparisons between 2Ddisplacementbased models and exact results of the linear threedimensional elasticity were also proposed in [25] for natural frequencies, displacement, and stress quantities in multilayered plates. Exact threedimensional elasticity theory was investigated in [26] for isosceles triangular plates by means of a global threedimensional Ritz formulation. The threedimensional elasticity free vibration analysis of a circular plate was analyzed in [27] by means of the Ritz method with a set of orthogonal polynomial series to approximate the spatial displacements. Theoretical analysis of high frequency vibrations is indispensable in a variety of engineering designs. Zhao et al. [28] introduced a novel computational approach, the discrete singular convolution (DSC) algorithm, for high frequency vibration analysis of plate structures. A completely independent approach, the Levy method, was employed to provide exact solutions to validate the proposed method. The importance of high frequency analysis of multilayered composite plates was also confirmed in [29]. Further works about the analysis of high frequency vibrations of structures are given in [30], where the discrete singular convolution (DSC) algorithm was used and then compared with a completely independent approach (the Levy method). In [31] the first nine frequency parameters of circular and annular plates with variable thickness and combined boundary conditions were computed for different thickness to radius ratios. Threedimensional elasticity theory was used in [31] and the Ritz method was applied to derive the eigenvalue equation. Xing and Liu [32] proposed the separation of variables to solve the Hamiltonian dual form of eigenvalue problem for transverse free vibrations of thin plates, and formulation of the natural modes in closed form was performed. The closed form natural mode exactly satisfied the governing equation of the eigenvalue problem of thin plate and was applicable for any types of boundary conditions. The extension of 3D exact analysis to functionally graded plates was performed in [33–35]. Exact closed form solutions (based on threedimensional elasticity theory) were carried out in [33] for both inplane and outofplane free vibration of thick homogeneous simply supported rectangular plates coated by a functionally graded (FG) layer. Vel and Batra [34] presented a threedimensional exact solution for free and forced vibrations of simply supported functionally graded rectangular plates and displacement functions that identically satisfy boundary conditions. Xu and Zhou [35] used the threedimensional elasticity theory to derive the general expressions for the displacements and stresses of the plate under static loads, which exactly satisfy the governing differential equations and the simply supported boundary conditions at four edges of the plate. The extension of threedimensional solutions to plates embedding piezoelectric layers was given in [36–41]. The threedimensional exact solution by Haojiang et al. [36] allowed the free vibration analysis of a circular plate made of piezoelectric material. Baillargeon and Vel [37] obtained an exact threedimensional solution for the cylindrical bending vibration of simply supported laminated composite plates with an embedded piezoelectric shear actuator. The bending and free vibration of an imperfectly bonded orthotropic piezoelectric rectangular laminate were investigated in [38] using a threedimensional statespace approach. Cheng et al. [39] presented an exact threedimensional method for the distribution of mechanical and electric quantities in interior points of a symmetrically inhomogeneous and laminated piezoelectric plate in the framework of linear theory of piezoelectricity. An exact threedimensional (3D) piezothermoelasticity solution was presented in [40] for static, free vibration and steady state harmonic response of simply supported crossply piezoelectric (hybrid) laminated rectangular plates with interlaminar bonding imperfections. Zhong and Shang [41] presented an exact threedimensional analysis for a functionally graded piezoelectric rectangular plate that was simply supported and grounded along its four edges. The state equations of the functionally graded piezoelectric plate were developed based on the state space approach.
The revision of the literature about threedimensional analysis of shells and plates demonstrates that there are a variety of interesting works concerning plate or shell geometry, and they include static and dynamic analysis, functionally graded, composite and piezoelectric materials, displacement, and mixed models. The present work gives a general formulation for all the geometries (square and rectangular plates, cylindrical and spherical shell panels, and cylindrical closed shells). The equations of motion for the dynamic case are written in general orthogonal curvilinear coordinates by using an exact geometry for shells. The system of second order differential equations is reduced to a system of first order differential equations, and afterwards it is exactly solved by using the exponential matrix method. Similar approaches have been used in [25] for the threedimensional analysis of plates in rectilinear orthogonal coordinates and in [7] for an exact, threedimensional, free vibration analysis of angleply laminated cylinders in cylindrical coordinates. The equations of motion written in orthogonal curvilinear coordinates allow general exact solutions for simply supported plate and shell geometries with constant radii of curvature. These equations are exactly solved, for the first time in this paper, by means of the exponential matrix method.
2. Geometrical and Constitutive Equations
A shell is a threedimensional body bounded by two closely spaced curved surfaces where one dimension (the distance between the two surfaces) is small in comparison with the other two dimensions in the plane directions. The middle surface of the shell is the locus of points which lie midway between these surfaces. The distance between the surfaces measured along the normal to the middle surface is the thickness of the shell at that point [42, 43]. Geometry and the reference system are indicated in Figure 1 where curvilinear orthogonal coordinates (, , ) are shown. The threedimensional space (the space in which the three independent variables , , and vary) is an Euclidean space. and are the principal radii of curvature along the coordinates and , respectively. is the thickness coordinate that varies from to (where is the thickness of the structure as shown in Figure 1).
In this work, we will focus on shells with constant radii of curvature (e.g., cylindrical and spherical geometries). The geometrical relations written for shells with constant radii of curvature are a particular case of the straindisplacement equations of threedimensional theory of elasticity in orthogonal curvilinear coordinates (see also [44–46]): where , , and are the displacement components in , , and direction, respectively. Symbol indicates the partial derivatives; the parametric coefficients for shells, with constant radii of curvature, that use the orthogonal curvilinear coordinate system are General geometrical relations for spherical shells degenerate into geometrical relations for cylindrical shells when or is infinite (with or equals one), and they degenerate into geometrical relations for plates when both and are infinite (with = = 1) [46].
Geometrical relations (see (1)) are substituted in threedimensional linear elastic constitutive equations in orthogonal curvilinear coordinates (, , ) for orthotropic material in the structural reference system (see [47, 48]). Partial derivatives , , and are indicated with subscripts , , and . A closed form solution of differential equations of equilibrium for shells is obtained when coefficients , , , and are set to zero (this means orthotropic angle equals or ):
3. Equilibrium Equations
The three differential equations of equilibrium written for the case of free vibration analysis of spherical shells with constant radii of curvature and are here given (the most general form for variable radii of curvature can be found in [45, 49]): where is the mass density and , , and indicate the second temporal derivative of the three displacement components.
Equation (3) is introduced in (4), and the closed form is obtained for simply supported shells and plates made of isotropic material or orthotropic material with or orthotropic angle (in both cases ). The three displacement components have the following harmonic form: where , , and are the displacement amplitudes in , , and directions, respectively. is the coefficient of the imaginary unit, is the circular frequency where is the frequency value, and is the time. In coefficients and , and are the halfwave numbers and and are the shell dimensions in and directions, respectively. Equilibrium equations are for spherical shell panels; they automatically degenerate into equilibrium equations for cylindrical closed/open shell panels when or is infinite (with or equals one) and into equilibrium equations for plates when and are infinite (with and equal one). In this way a unique and general closed formulation is possible for any geometry: The system of equation (6) can be written in a compact form by introducing coefficients for each block : Equation (7) is a system of three second order differential equations. They are written for spherical shell panels with constant radii of curvature but they automatically degenerate into equations for cylindrical shells and plates (see also [7, 25]).
3.1. Solution for the System of Differential Equations
The system of second order differential equations can be reduced to a system of first order differential equations by using the method described in [50, 51]. This methodology allows the following system to be obtained: Equation (8) can be written in a compact form as where and . Equation (9) can be written as with .
In the case of plate geometry coefficients , , , , , , and are zero because the radii of curvature and are infinite. The other coefficients , , , , , , , , , , , and are constant because parametric coefficients and they do not depend on the thickness coordinate ; therefore matrices , , and are constant in the plate case. The solution of (12) can be written as [51, 52] where is the thickness coordinate referred to the bottom of the structure that has values from 0 at the bottom to at the top (see Figure 2). The exponential matrix is calculated with as where is the identity matrix. This expansion has a fast convergence as indicated in [53] and it is not time consuming from the computational point of view. In the case of onelayered plate there is not a necessity to impose the continuity conditions at the interfaces for displacements and transverse shear/normal stresses; for this reason the transfer matrix is equal to the identity matrix : Equation (15) allows the calculation of the matrix as this last matrix permits linking vector calculated at the top of the plate () with vector calculated at the bottom of the plate ():
(a)
(b)
In the case of shell geometry matrices , , and are not constant because of parametric coefficients and that depend on or coordinate (see Figure 2). A first method could be the use of hypothesis (it is valid only for very thin shells) that means . In this case the solution is the same already seen for the plate because matrices , , and are constant. This method is not used in the benchmarks proposed in this paper because it is an approximation that is valid only for very thin shells, and it does not consider the exact geometry of the structure. However, some comparisons between the method using exact geometry and the method using will be given at the end of the section for results. The second method (used in this paper) is the introduction of several fictitious layers where and can exactly be calculated with the thickness coordinate of the middle of the fictitious layers; in this way (12), (13), and (14) are valid for each layer because is here constant. The exponential matrix is calculated in each fictitious layer with the thickness of the layer. The results proposed in this paper for the benchmarks are given with a number of fictitious layers ; this value guarantees the exact convergence to the correct geometry of shells for each case investigated as demonstrated in the section for the preliminary results. In the case of layers for shell geometry, it is necessary to calculate transfer matrices by using for each interface the following conditions: that means each displacement and transverse stress component at the top of the layer is equal to displacement and transverse stress component at the bottom of the layer. The calculated matrices allow linking at the bottom of the layer with at the top of the layer: at the top of the layer is linked with at the bottom of the same layer by means of the exponential matrix : Equation (19) can recursively be introduced in (20) for the interfaces to obtain by defining the matrix for the multifictitiouslayer shells, it is possible to write (21) in analogy with (17): It links calculated at the top of the last fictitious layer with calculated at the bottom of the first layer. Matrices are constant because they are evaluated with , , , and calculated in the midsurface of the shell and with and calculated in the middle of each layer. Matrices are constant because they are evaluated with , , , and calculated in the midsurface of the shell and with and calculated at each fictitious interface. Equation (17) is valid for onelayered plates and (22) is valid for onelayered shells divided in fictitious layers to correctly consider the geometry.
The structures are simply supported and free stresses at the top and at the bottom; this feature means: Equation (23) imposed at the top of the structure has , , , and calculated in the midsurface of the shell, and and are calculated at the top of the shell for : Equation (23) imposed at the bottom of the structure has , , , and calculated in the midsurface of the shell, and and are calculated at the bottom of the shell for : Equations (26) in matrix form are ( means calculated at the top of the shell) Equation (27) in matrix form is ( means calculated at the bottom of the shell) Equations (28)(29) in compact form to express the free stress state at the top and bottom of the shell are in the case of plate, there are no fictitious layers: Equation (22) can be substituted in (30): in this way (33) are grouped in the following system: and introducing the () matrix, (34) becomes: Equation (35) is also valid for plate case where the fictitious layers are not introduced and , , and . The solution is implemented in a Matlab code where only the spherical shell method is considered; it automatically degenerates into cylindrical open/closed shell and plate methods.
The free vibration problem means finding the nontrivial solution of in (35); this means imposing the determinant of matrix equal to zero: Equation (36) needs to find the roots of a higher order polynomial in . For each pair of halfwave numbers () a certain number of circular frequencies are obtained depending on the order chosen for the exponential matrices and the number of fictitious layers.
3.2. Vibration Modes
A certain number of circular frequencies are found when halfwave numbers and are imposed in the structures. For each frequency , it is possible to find the vibration mode through the thickness in terms of the three displacement components. If the frequency is substituted in () matrix , this last matrix has six eigenvalues. We are interested to the null space of matrix that means finding the () eigenvector related to the minimum of the six eigenvalues proposed. This null space is, for the chosen frequency , the vector calculated at the bottom: means the transpose of the vector and the subscript means that the null space is calculated for the circular frequency .
It is possible to find (with the three displacement components , , and through the thickness) for each layer by using (19)–(22); the thickness coordinate can assume all the values from the bottom to the top of the structure. For the plate case the procedure is simpler because there are no fictitious layers and the number equals 1.
4. Results
The threedimensional exact solution proposed has been validated by means of a comparison with three assessments given in the literature for a onelayered isotropic plate [22, 34], onelayered isotropic cylinder [8, 9], and onelayered orthotropic cylinder [7]. After this preliminary validation and the appropriate convergence study, the method has been used to investigate the free vibration analysis of onelayered isotropic and orthotropic square and rectangular plates, cylindrical shell panels, cylinders, and spherical shell panels (see Figure 3). The effects of the curvature terms in and parametric coefficients have also been investigated.
(a)
(b)
(c)
(d)
(e)
4.1. Preliminary Assessments
The assessment proposed in Vel and Batra [34] compares their 3D solution with the 3D solution by Srinivas et al. [22]. The square plate is simply supported embedding one aluminium alloy layer with Young modulus , Poisson ratio , and mass density . The thickness value is . Two different thickness ratios are considered, that is, and . The first six circular frequencies in nodimensional form are given in Table 1 for imposed halfwave numbers . The 3D exact solution proposed in this paper coincides with those proposed by Vel and Batra [34] and by Srinivas et al. [22] for both thickness ratios and for each vibration mode (from the first to the sixth one). A convergence study has been proposed where the number of fictitious layers and the order of expansion for the exponential matrix have conveniently been chosen. For the plate case one fictitious layer is used because there is no effect of parametric coefficients and . For , an order of expansion for the exponential matrix always gives the correct solution for each vibration mode and thickness ratio . The calculation of the exponential matrix is not time consuming. An alternative method could be the use of fictitious layers and a lower order of expansion for the exponential matrix. In this last case, fictitious layers always give the correct solution for each vibration mode and thickness ratio. The use of layers is not time consuming because the matrix has always dimension for any value of layers, even if the proposed method uses a layerwise approach. Solutions with and or with and are coincident for the plate case and their time solution needs a few seconds. In conclusion, the threedimensional exact solution presented here is correct for the free vibration analysis of onelayered plates even when the structures are thick and higher order vibration modes are considered.

The assessment proposed by Khalili et al. [11] compared their 2D closed form solutions for isotropic circular cylindrical shells with the threedimensional analysis by Armenakas et al. [8] adapted from Bhimaraddi [9]. The cylinder is isotropic and onelayered with Poisson ratio . The structure is simply supported and it has radius of curvature and infinite radius of curvature in direction. The circular dimension is ; the thickness is 0.12 and 0.18; that means thickness ratios are and , respectively. Several ratios cylinder length/radius of curvature () are investigated in the case of . The fundamental circular frequency in nodimensional form is given in Tables 2 and 3 (thickness ratio equals 0.12 ad 0.18, resp.) for axial halfwave number and several circular halfwave numbers . The threedimensional exact solution proposed here is coincident with the 3D analysis by Armenakas et al. [8] for each halfwave number, thickness ratio, and cylinder length proposed. For the case of shell, the use of fictitious layers is necessary to approximate the parametric coefficients and . The convergence study is shown for a value for the expansion of the exponential matrix. fictitious layers always give the correct solution for each thickness ratio (see Tables 2 and 3), length of the cylinder, and halfwave numbers in circumferential direction. The present method is not time consuming; layers solution gives the correct results in a few seconds. In conclusion, the solution proposed can be considered as validated for onelayered isotropic shells.


The assessment proposed by Soldatos and Ye [7] gives threedimensional results for multilayered orthotropic cylinders. A comparison with the present method is made for the cases of orthotropic angle equal to or (they allow the closed form solution and it also means onelayered structure). The cylinder is simply supported with a great degree of orthotropy (, , , , and homogeneous mass density ). The length is 10 and the radius of curvature equals 10. The circular dimension is . The cylinder is very thick ; that means thickness ratio is . In Table 4 the first three circular frequencies in nodimensional form are given for halfwave numbers and , and orthotropic angle equals or . The 3D solution by Soldatos and Ye [7] is correctly obtained for each mode and angle by using fictitious layers and order of expansion. (, ) solution is not heavy from the computational point of view because the matrix has always dimension even if the method uses a layerwise approach. In conclusion, the solution is also validated for orthotropic singlelayered thick shells.

All the new benchmarks proposed in Section 4.2 will use (, ) solution for plate cases and (, ) solution for shell cases. Both solutions are very convenient from the computational point of view (they need only a few seconds) and they allow the correct analysis for each thick and thin isotropic/orthotropic plate and shell.
4.2. Benchmarks
Ten different benchmarks are proposed to show a complete overview of the free vibration analysis of onelayered plates and shells. Five different geometries are taken into account in Figure 3. All these structures are simply supported. The square plate has dimensions and thickness ratios . The rectangular plate has dimensions and and the thickness ratios are . The cylindrical shell panel has a radius of curvature and an infinite radius of curvature in direction. The dimensions are and , and the thickness ratios are . The cylinder has the same radii of curvature of the cylindrical shell panel, but it is closed in circumferential direction that means . The other dimension is and the thickness ratios are . The last geometry is the spherical shell panel with radii of curvature , dimensions , and thickness ratios . Each geometry includes two materials: one isotropic layer in aluminium alloy Al2024 with Young modulus , Poisson ratio , and mass density and one orthotropic layer in Gr/Ep with Young modulus components and , shear modulus components and , Poisson ratio components and , and mass density . The benchmarks are onelayered isotropic square plate (see Table 5), onelayered orthotropic square plate (see Table 6), onelayered isotropic rectangular plate (see Table 7), onelayered orthotropic rectangular plate (see Table 8), onelayered isotropic cylindrical shell panel (see Table 9), onelayered orthotropic cylindrical shell panel (see Table 10), onelayered isotropic cylinder (see Table 11), onelayered orthotropic cylinder (see Table 12), onelayered isotropic spherical shell panel (see Table 13), and onelayered orthotropic spherical shell panel (see Table 14). The first three circular frequencies in nodimensional form are calculated in Tables 5–14 for various pairs of halfwave numbers and several thickness ratios. The vibration modes plotted in Figures 4–12 are given in terms of nodimensional values such as , , , and .

