Optimization of the Aerodynamic Performances of an Unmanned Aerial Vehicle

Authors: Fares Senouci, Bachir Imine

Abstract:

This document provides numerical and experimental optimization of the aerodynamic performance of a drone equipped with three types of horizontal stabilizer. To build this optimal configuration, an experimental and numerical study was conducted on three parameters: the geometry of the stabilizer (horizontal form or reverse V form), the position of the horizontal stabilizer (up or down), and the landing gear position (closed or open). The results show that up-stabilizer position with respect to the horizontal plane of the fuselage provides better aerodynamic performance, and that the landing gear increases the lift in the zone of stability, that is to say where the flow is not separated.

Keywords: Aerodynamics, wind tunnel, turbulence model, lift, drag.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1340178

References:

[1] O. M. Fouatih, et al.―Design optimization of the aerodynamic passive flow control on NACA 4415 airfoil using vortex generators‖, DOI: 10.1016/j.euromechflu, 2015.11.006.
[2] Elsa M. Cárdenas et al.―Design of an Unmanned Aerial Vehicle for Ecological Conservation‖ DOI: 10.2514/6.2005-7056•
[3] Luis Velazquez, ―low-speed wind tunnel testing for an unmanned aerial vehicle airfoil‖, Institute of Thermomechanics AS CR, v.v.i., Prague, October 21 - 23, 2009.
[4] A. Zeghib, Revue des Energies Renouvelables CISM’08 Oum El Bouaghi, 311 – 324, 2009.
[5] Manuel de la TE 44 Subsonic Wind Tunnel.
[6] Fluent 62 User’s Guide. Fluent, Inc, 2005.
[7] F. Senouci, B. Imine―Numerical and Experimental Study of Flow around an UAV ‖SKP Engineering college, TN, India, 16-17, 2011, pp. 400–404, December 2011, unpublished.