Table of Contents Author Guidelines Submit a Manuscript
Mathematical Problems in Engineering
Volume 2015, Article ID 478457, 9 pages
Research Article

Computational Study of a Transverse Rotor Aircraft in Hover Using the Unsteady Vortex Lattice Method

1Department of Mechanical Engineering, University of New Mexico, Albuquerque, NM 87131, USA
2Department of Mechanical Engineering, Universidad de los Andes, Bogota 111711, Colombia
3Structures Department, Universidad Nacional de Córdoba, 5000 Córdoba, Argentina

Received 12 May 2015; Revised 25 August 2015; Accepted 27 August 2015

Academic Editor: Guangming Xie

Copyright © 2015 Juan D. Colmenares 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 the simulation of a two-rotor aircraft in different geometric configurations during hover flight. The analysis was performed using an implementation of the unsteady vortex-lattice method (UVLM). A description of the UVLM is presented as well as the techniques used to enhance the stability of results for rotors in hover flight. The model is validated for an isolated rotor in hover, comparing numerical results to experimental data (high-Reynolds, low-Mach conditions). Results show that an exclusion of the root vortex generates a more stable wake, without affecting results. Results for the two-rotor aircraft show an important influence of the number of blades on the vertical thrust. Furthermore, the geometric configuration has a considerable influence on the pitching moment.