Numerical modeling and analysis of aerodynamic wake induced by rotating blades

Abstract

This research project proposes a numerical study of the aerodynamic wake generated by a system of rotating wings. The Generalized Dynamic Wake Model, which has been conceived to represent the dynamic states of the inflow induced by the rotor in terms of a finite number of harmonic and radial modes, will be applied in the study. Results presented in the literature show such an aerodynamic model can be numerically integrated with structural models of non-linear rotating beams to provide a compact, accurate and computationally efficient aeroelastic formulation, which is able to simulate the rotor dynamic behavior in operational condition. A piezoelectric element can be introduced in the variational formulation used to the modeling of non-linear beam equations to provide a piezoaeroelastic model suitable to be applied in problems related to aeroelastic stability, energy harvesting and attenuation of mechanical vibration in helicopter rotors. The study focuses on a comprehensive verification of the aerodynamic wake model, based on the physical interpretation of the role played by the eigenvectors and eigenvalues associated with the inflow states. Such an approach plays a significant role to the conceptual understanding required to the reliable implementation of an aeroelastic model, hence helping in the development of both basic research and technological innovation.