Boundary Integral Equations for Time Domain Solution and Reduced Order Modeling of Thin Wings Unsteady Aerodynamics

In this research, thin wings unsteady aerodynamics has been investigated using boundary integral equations. The purpose is to develop a proper basis for the extension of boundary element method applicability to some novel lifting configurations with negligible thickness e.g. membrane wings, flapping and morphing wings. For this purpose, conventional aerodynamic boundary element method that can treat only thick bodies has been formulated and modified so it can be used for thin wings too. Moreover, as boundary element system of equations is expressible in eigenvalue problem form, eigenanalysis of unsteady flow over thin wings has been performed and reduced order aerodynamic models have been constructed based on flow eigenmodes. The proposed boundary element method and BEM-based reduced order models have been used for time domain aerodynamic analysis of various airfoils/wings undergoing different unsteady motions and obtained results are in line with analytical relations, experimental data and verified numerical results.