University of Tehran Press Journal of Computational Applied Mechanics 2423-6713 57 3 2026 06 01 Influence of Spanwise FGM and Numerical Parameters on the Fluid-Structure Interaction Response of a Cantilevered Plate Wing 391 412 106122 10.22059/jcamech.2026.410596.1778 EN Mohamed S Alzahrani Department of Mechanical Engineering, Faculty of Engineering, King Abdulaziz University, Jeddah, Saudi Arabia Hassan Qanash Department of Mechanical Engineering, Faculty of Engineering, King Abdulaziz University, Jeddah, Saudi Arabia Mohamed S Abdelwaheed Department of Mechanical Engineering, Faculty of Engineering, King Abdulaziz University, Jeddah, Saudi Arabia Mohamed A Elltaher Department of Mechanical Engineering, Faculty of Engineering, King Abdulaziz University, Jeddah, Saudi Arabia Department of Mechanical Design and Production, Faculty of Engineering, Zagazig University, Egypt 0000-0003-3116-2101 Journal Article 2026 02 05 This study investigates the nonlinear aeroelastic response and flutter behavior of a cantilevered plate wing using a two-way fluid–structure interaction framework in ANSYS, coupling Fluent and Mechanical. Both isotropic Aluminum and a spanwise functionally graded Al/Al₂O₃ material system are examined. The aerodynamic solver is validated against published S809 airfoil data, followed by validation of the cantilevered wing model. A sensitivity analysis is performed by varying the time step size (0.02–0.002 s) and the number of coupling iterations (5 and 10). Larger time steps introduce fluctuations in peak oscillation amplitudes and can delay growth through the critical flow speed window, whereas smaller time steps reduce these fluctuations and diminish iteration sensitivity. A mid-range configuration (∆t = 0.005 s, 10 iterations) provides results comparable to the finest settings at substantially lower computational cost. Using these parameters, the aeroelastic response of a spanwise functionally graded wing—constructed by dividing the span into ten segments with linear grading (k = 1)—is assessed. The FGM wing exhibits no flutter within the investigated flow speed range and shows markedly reduced tip displacement, maintaining RMS amplitudes below 0.01 mm, in contrast to the Aluminum baseline, which displays the expected increase in response with flow speed. The results demonstrate that a time step of 0.005 s with ten coupling iterations is sufficient for reliable flutter prediction under ANSYS student license constraints, and that spanwise FGM application significantly enhances aeroelastic stability. https://jcamech.ut.ac.ir/article_106122_13eddc8c84e116fa3a1693f08171890d.pdf