Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle

In principle, the tailless model configuration can be equipped with any airfoil as long as the design is compensated with an appropriate combination of some parameter such as aspect ratio, sweep angle and twist. This thesis presents a parametric study of subsonic Tailless UAV conceptual design with...

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Main Author:	Hashim, Afida
Format:	Thesis
Language:	English
Published:	2014
Subjects:	TL500-777 Aeronautics Aeronautical engineering
Online Access:	http://eprints.usm.my/46369/1/Afida%20Binti%20Hashim24.pdf
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spelling	my-usm-ep.463692020-02-27T08:20:29Z Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle 2014-01 Hashim, Afida TL500-777 Aeronautics. Aeronautical engineering In principle, the tailless model configuration can be equipped with any airfoil as long as the design is compensated with an appropriate combination of some parameter such as aspect ratio, sweep angle and twist. This thesis presents a parametric study of subsonic Tailless UAV conceptual design with some parameter trade off. The usages of three types of airfoils of which are the conventional airfoil, reflex airfoil and symmetrical airfoil in tailless configuration have been studied. The design is divided into three cases which are case 1 (conventional airfoil), case 2 (symmetrical airfoil) and case 3 (reflexed airfoil). All cases are designed to meet the same mission requirement. Analyses of aerodynamic characteristics of three cases have been carried out primarily at cruising speed (18m.s-1) using Computational Fluid Dynamic (CFD) simulation with Spalart-Allmaras turbulence model. The fully structured mesh is employed and grid dependency check had been carried out. The results numerically iterated had been verified and compared to the published data. The lift coefficient, drag coefficient, moment coefficient and lift to drag ratio are plotted, compared and analyzed at different Reynolds number. Generally, by comparison the results of these three cases are consistent with other tailless configurations where it shows similarities in their aerodynamic trends. Though it is realized that conventional airfoil have negative pitching moment, but a moderate amount of pitching moment with proper selections of parameters such as static margin, sweep angle, aspect ratio, and twist will enable the design to obtained a sufficient Cmo. Thus, the sweep angle and the body shape at the center body for case 1 are varied. The results showed a significant improvement in aerodynamic characteristic. The pressure contours and velocity magnitude over tailless configuration were also observed. It may achieve higher aerodynamic efficiency if some multidisciplinary optimization is carried out. 2014-01 Thesis http://eprints.usm.my/46369/ http://eprints.usm.my/46369/1/Afida%20Binti%20Hashim24.pdf application/pdf en public masters Universiti Sains Malaysia Pusat Pengajian Kejuruteraan Aeroangkasa
institution	Universiti Sains Malaysia
collection	USM Institutional Repository
language	English
topic	TL500-777 Aeronautics Aeronautical engineering
spellingShingle	TL500-777 Aeronautics Aeronautical engineering Hashim, Afida Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle
description	In principle, the tailless model configuration can be equipped with any airfoil as long as the design is compensated with an appropriate combination of some parameter such as aspect ratio, sweep angle and twist. This thesis presents a parametric study of subsonic Tailless UAV conceptual design with some parameter trade off. The usages of three types of airfoils of which are the conventional airfoil, reflex airfoil and symmetrical airfoil in tailless configuration have been studied. The design is divided into three cases which are case 1 (conventional airfoil), case 2 (symmetrical airfoil) and case 3 (reflexed airfoil). All cases are designed to meet the same mission requirement. Analyses of aerodynamic characteristics of three cases have been carried out primarily at cruising speed (18m.s-1) using Computational Fluid Dynamic (CFD) simulation with Spalart-Allmaras turbulence model. The fully structured mesh is employed and grid dependency check had been carried out. The results numerically iterated had been verified and compared to the published data. The lift coefficient, drag coefficient, moment coefficient and lift to drag ratio are plotted, compared and analyzed at different Reynolds number. Generally, by comparison the results of these three cases are consistent with other tailless configurations where it shows similarities in their aerodynamic trends. Though it is realized that conventional airfoil have negative pitching moment, but a moderate amount of pitching moment with proper selections of parameters such as static margin, sweep angle, aspect ratio, and twist will enable the design to obtained a sufficient Cmo. Thus, the sweep angle and the body shape at the center body for case 1 are varied. The results showed a significant improvement in aerodynamic characteristic. The pressure contours and velocity magnitude over tailless configuration were also observed. It may achieve higher aerodynamic efficiency if some multidisciplinary optimization is carried out.
format	Thesis
qualification_level	Master's degree
author	Hashim, Afida
author_facet	Hashim, Afida
author_sort	Hashim, Afida
title	Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle
title_short	Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle
title_full	Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle
title_fullStr	Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle
title_full_unstemmed	Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle
title_sort	conceptual aerodynamic studies of a small tailless unmanned air vehicle
granting_institution	Universiti Sains Malaysia
granting_department	Pusat Pengajian Kejuruteraan Aeroangkasa
publishDate	2014
url	http://eprints.usm.my/46369/1/Afida%20Binti%20Hashim24.pdf
_version_	1747821658553450496

Conceptual Aerodynamic Studies Of A Small Tailless Unmanned Air Vehicle

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