Iranian Society of Acoustics and Vibration Journal of Vibration and Sound 2383-1839 14 27 2025 08 23 Numerical and analytical investigation of buckling behavior of a symmetric airfoil made of laminated composite Shell Numerical and analytical investigation of buckling behavior of a symmetric airfoil made of laminated composite Shell 81 98 728211 FA Mohammad خاکباز Master of Science in Aerospace Engineering (Structural), Faculty of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran 0009-0001-7775-9029 Amin Darani Goldarreh Student in Aerospace Engineering (Aero structures), Faculty of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran Alireza Ebrahimi Hesari PhD student in Mechanical Engineering (Applied Design), Faculty of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran 0009-0008-4367-5055 Journal Article 2025 05 10 This study has investigated analytically and numerically the buckling loading and buckling mode shapes of a symmetrical NACA0012 airfoil with a laminated composite skin. The mechanical properties of the composite wing shell with [(0/90/45/-45] ply and AS4/3501-6 material are considered. In this research, first, the theory of thin plate buckling is explained using the potential energy method and the governing equations for the buckling of thin shells, and then numerical modeling is performed in the finite element software Abaqus, with a selected square mesh and the S4R shell element. The results of the buckling modes show that with increasing mode number, the critical buckling load also increases. The results of the analytical and numerical solution of the buckling loading of the layers with a difference of less than 10% show that,. The section [0] suffers the lowest buckling load, while the [90] arrangement shows about 27.6 times more resistance. Also, the use of ribs and stringers significantly increases the critical load by about 10 times compared to The porcelain layer becomes quasi-isotropic, which shows the importance of using internal structural reinforcements. This study has investigated analytically and numerically the buckling loading and buckling mode shapes of a symmetrical NACA0012 airfoil with a laminated composite skin. The mechanical properties of the composite wing shell with [(0/90/45/-45] ply and AS4/3501-6 material are considered. In this research, first, the theory of thin plate buckling is explained using the potential energy method and the governing equations for the buckling of thin shells, and then numerical modeling is performed in the finite element software Abaqus, with a selected square mesh and the S4R shell element. The results of the buckling modes show that with increasing mode number, the critical buckling load also increases. The results of the analytical and numerical solution of the buckling loading of the layers with a difference of less than 10% show that,. The section [0] suffers the lowest buckling load, while the [90] arrangement shows about 27.6 times more resistance. Also, the use of ribs and stringers significantly increases the critical load by about 10 times compared to The porcelain layer becomes quasi-isotropic, which shows the importance of using internal structural reinforcements. https://jvs.isav.ir/article_728211_deeb48e73d502c2f4aefb102610e1020.pdf