## 4 Numerical Results and Discussion
### Parametric Study
However, the normalized central deflection, \(w^{\star}\), and stress, \(\sigma_{x}{}^{*}\), curves of symmetric [\(0^{\circ}/90^{\circ}/0^{\circ}\)] spherical and cylindrical panels with R\({}_{2}\rightarrow\infty\) are almost the same for the whole range of \(a/h\) ratio, as is shown in Figure 4. The normalized central deflection and stress results obtained with BDM for symmetric [\(0^{\circ}/90^{\circ}/0^{\circ}\)] lamination are exactly matched with GDQ method. Variations of the normalized stress, \(\sigma_{x}{}^{*}\), of antisymmetric [\(0^{\circ}/90^{\circ}\)] and symmetric [\(0^{\circ}/90^{\circ}/0^{\circ}\)] spherical and two cylindrically curved panels for different R/\(a\) ratios are individually displayed in Figures 3b and 4b, respectively. Figures 5 and 6 present the variations of the normalized central deflection, \(w^{\star}\), and stress, \(\sigma_{x}{}^{*}\), of moderately thick (\(a/h=20\)) curved panels (one spherical and two cylindrical) with antisymmetric [\(0^{\circ}/90^{\circ}\)] and symmetric [\(0^{\circ}/90^{\circ}/0^{\circ}\)] laminations with R/\(a\) ratio. Based on the present results, the spherical panel response was found to represent similar character  
Figure 3: (**a**) Variation of the non-dimensional displacement, \(w^{\star}\), and (**b**) non-dimensional stresses, \(\sigma_{x}{}^{*}\), with \(a/h\) ratio for antisymmetric [\(0^{\circ}/90^{\circ}\)] spherical and cylindrical panels (R/\(a=10\)). \begin{table}
\begin{tabular}{c c c c c c c c c} \hline  & **R/\(a\)** & **\(a/h\)** & **Method** & \multicolumn{6}{c}{\(\mathbf{3}\)} & **10** & **20** & **30** & **40** & **50** \\ \hline \multirow{4}{*}{\(\sigma_{y}{}^{*}\)} & \multirow{4}{*}{Plate} & \multirow{4}{*}{20} & BDM & 452.400 & 334.082 & 283.944 & 257.786 & 239.216 & 224.367 \\  & & GDQ & 440.178 & 316.606 & 266.128 & 241.087 & 223.864 & 210.326 \\ \cline{2-10}  & & \multirow{2}{*}{50} & BDM & 993.809 & 632.001 & 496.701 & 439.754 & 405.647 & 381.325 \\  & & GDQ & 992.951 & 627.821 & 491.164 & 433.981 & 399.974 & 375.874 \\ \cline{2-10}  & & \multirow{2}{*}{100} & BDM & 1910.4 & 1142 & 859.2 & 746 & 681.9 & 638.5 \\  & & GDQ & 1947.4 & 1193.2 & 913.2 & 799.1 & 733.2 & 687.7 \\ \hline \end{tabular}
\end{table} 
Table 5: _Cont._istic to those observed for its cylindrical counterpart, with R\({}_{2}\rightarrow\infty\) for each R/_a_ ratio value. Symmetric [0\({}^{\circ}\)/90\({}^{\circ}\)/0\({}^{\circ}\)] laminates also exhibited a similar trend. For symmetric [0\({}^{\circ}\)/90\({}^{\circ}\)/0\({}^{\circ}\)] lamination, non-dimensional displacements, \(w^{\star}\), both for the spherical panel and cylindrical counterparts--as (R\({}_{2}\rightarrow\infty\))--possess a flatter regime after R/_a_> 60, while non-dimensional displacement, \(w^{\star}\), values in the cylindrical panel under R\({}_{1}\rightarrow\infty\) conditions possess a flatter regime after R/_a_> 20. The normalized central deflection results for symmetric [0\({}^{\circ}\)/90\({}^{\circ}\)/0\({}^{\circ}\)] laminations obtained with BDM are exactly matched with the GDQ solution. Variations of the normalized stress, \(\sigma_{x}{}^{\ast}\), of the moderately thick (_a_/_h_= 20) antisymmetric [0\({}^{\circ}\)/90\({}^{\circ}\)] and symmetric ([0\({}^{\circ}\)/90\({}^{\circ}\)/0\({}^{\circ}\)] spherical and two cylindrically curved panels for different R/_a_ ratios are individually displayed in Figures 5b and 6b, respectively. Figure 4: (**a**) Variation of non-dimensional displacement, \(w^{\ast}\), and (**b**) non-dimensional stresses, \(\sigma_{x}{}^{\ast}\), with the _a_/_h_ ratio for symmetric [0\({}^{\circ}\)/90\({}^{\circ}\)/0\({}^{\circ}\)] spherical and cylindrical panels (R/_a_= 10). Figure 5: (**a**) Variation of non-dimensional displacement, \(w^{\ast}\), and (**b**) non-dimensional stresses, \(\sigma_{x}{}^{\ast}\), of moderately thick (_a_/_h_= 20) curved panels (one spherical and two cylindrical) with an R/_a_ ratio for antisymmetric [0\({}^{\circ}\)/90\({}^{\circ}\)] lamination.