الفهرس 
صفحة العنوانOnly 14 pages are availabe for public view
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Abstract
1. INTRODUCTION
Developments in Unmanned Aerial Vehicles (UAVs) technology have seen a recent surge in interest and effort due to increased trust on remotely piloted and autonomous air vehicles in military and homeland security applications. An unmanned vehicle with an additional capability of vertical take-off and landing (VTOL) represents one example of an interest area which has potential for significant research innovation. Therefore, it was necessary to evaluate the types of drones in terms of body and wings to obtain the best aerodynamic performance.
This study presents computational investigation of aerodynamic characteristics of flow over an elliptic airfoil. A computational method studied to get the maximum lift to drag ratio in order to get a best performance to elliptic airfoil for future use in Canard Rotor/Wing (CRW) UAVs. The drag and lift forces can be validated through experiments using wind tunnel testing. The experimental data is taken from investigation by Kwon and Park (2005), The investigation is carried out over a two-dimensional elliptical airfoil using ANSYS FLUENT (version 12.0.18), to obtain the surface pressure distribution, from which drag and lift were calculated using integral equations of pressure over finite surface areas. In addition the drag and lift coefficients were also determined. The fluid used for this purpose is air.
1.1Fundamentals of Design and Aerodynamics for UAVs
For design a UAVs wing, we must know some parameters. This section shows the general requirements of the UAVs, which effect on computational study. To initiate the design process, the physical parameters are first identified. There are two types of parameters,
Chapter 1 Introduction
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dimensional like (chord and span) which responsible on wing geometry as shown in Figure (1.1), and design like (Airfoil, thickness ratio, pressure, angle of attack and so on), because of the influence of these parameters on the lift and drag ratio for elliptic airfoil