In this work, an integrated aero-structural methodology is presented, combining a MATLAB panel-method aerodynamic solver with ANSYS finite-element analysis to predict the performance of a tapered NACA 2412 wing. The pressure distribution obtained from the panel method gave good agreement with CFD data, with a maximum deviation of 8%, and the lift coefficient prediction improved by 5 to 7% over traditional uncoupled methods. Drag-polar comparisons indicated that the average error reduced by 6%, establishing improved aerodynamic force prediction along the operating angles of attack. At the structural level, the updated pressure mapping reduced the error in deflection prediction by roughly 12%, while the distribution of bending stress was within 4% of reference structural results. These combined results demonstrate that strongly coupling aerodynamics and structure better predicts loading accuracy and the resultant structural response, giving a more reliable basis for preliminary aircraft wing design