Table of Contents
Journal of Wind Energy
Volume 2014 (2014), Article ID 987414, 13 pages
Research Article

On the Deflexion of Anisotropic Structural Composite Aerodynamic Components

Energy and Power Management Research Group, School of Computing, Engineering and Physical Sciences, University of Central Lancashire, Preston, PR1 2HE, UK

Received 8 August 2013; Accepted 30 October 2013; Published 20 January 2014

Academic Editor: Adrian Ilinca

Copyright © 2014 J. Whitty et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


This paper presents closed form solutions to the classical beam elasticity differential equation in order to effectively model the displacement of standard aerodynamic geometries used throughout a number of industries. The models assume that the components are constructed from in-plane generally anisotropic (though shown to be quasi-isotropic) composite materials. Exact solutions for the displacement and strains for elliptical and FX66-S-196 and NACA 63-621 aerofoil approximations thin wall composite material shell structures, with and without a stiffening rib (shear-web), are presented for the first time. Each of the models developed is rigorously validated via numerical (Runge-Kutta) solutions of an identical differential equation used to derive the analytical models presented. The resulting calculated displacement and material strain fields are shown to be in excellent agreement with simulations using the ANSYS and CATIA commercial finite element (FE) codes as well as experimental data evident in the literature. One major implication of the theoretical treatment is that these solutions can now be used in design codes to limit the required displacement and strains in similar components used in the aerospace and most notably renewable energy sectors.