Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model

Delta wing design is being used in aircraft to obtain high manoeuvre properties. The flow above the delta wing is complicated and dominated by a very complex vortex structure. This research investigates the effects of the propeller locations on the aerodynamic characteristics above a generic 55° sha...

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Main Author:	Kasim, Khushairi Amri
Format:	Thesis
Language:	English
Published:	2017
Subjects:	TJ Mechanical engineering and machinery
Online Access:	http://eprints.utm.my/id/eprint/78655/1/KhushairiAmriKasimMFKM2017.pdf
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id	my-utm-ep.78655
record_format	uketd_dc
spelling	my-utm-ep.786552018-08-29T07:35:40Z Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model 2017-03 Kasim, Khushairi Amri TJ Mechanical engineering and machinery Delta wing design is being used in aircraft to obtain high manoeuvre properties. The flow above the delta wing is complicated and dominated by a very complex vortex structure. This research investigates the effects of the propeller locations on the aerodynamic characteristics above a generic 55° sharp-edged non-slender delta wing Unmanned Aerial Vehicle (UAV) model. This research was performed by an experimental method. The experiments were conducted in a closed circuit Universiti Teknologi Malaysia-Low Speed Tunnel (UTM-LST) wind tunnel at wind speed of 20 m/s and 25 m/s respectively. In this project, the propeller was located at three different locations at front, middle and rear of the wing. The experimental data highlights an impact of propeller locations on lift, drag, pitching moment and vortex characteristic of the UAV model. Rear propeller configuration recorded the highest lift generation. Meanwhile, middle propeller configuration has the highest drag with increment by 2% to 15%. The results also show that the propeller advance ratio plays important roles in development of the primary vortex above the delta-winged model. The higher propeller advance ratio would decrease the development of the vortex on the wing, consequently limiting the lift generation and stall condition in which are disadvantageous for aircraft aerodynamic characteristics. The lift coefficients decrease by 7% when the propeller advance ratio is increased from 0.98 to 1.20. Lastly, suction effect from the propeller has improved the vortex properties better than blowing mechanism in which is beneficial for the delta-winged UAV propeller selection. 2017-03 Thesis http://eprints.utm.my/id/eprint/78655/ http://eprints.utm.my/id/eprint/78655/1/KhushairiAmriKasimMFKM2017.pdf application/pdf en public http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:108780 phd doctoral Universiti Teknologi Malaysia, Faculty of Mechanical Engineering Faculty of Mechanical Engineering
institution	Universiti Teknologi Malaysia
collection	UTM Institutional Repository
language	English
topic	TJ Mechanical engineering and machinery
spellingShingle	TJ Mechanical engineering and machinery Kasim, Khushairi Amri Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model
description	Delta wing design is being used in aircraft to obtain high manoeuvre properties. The flow above the delta wing is complicated and dominated by a very complex vortex structure. This research investigates the effects of the propeller locations on the aerodynamic characteristics above a generic 55° sharp-edged non-slender delta wing Unmanned Aerial Vehicle (UAV) model. This research was performed by an experimental method. The experiments were conducted in a closed circuit Universiti Teknologi Malaysia-Low Speed Tunnel (UTM-LST) wind tunnel at wind speed of 20 m/s and 25 m/s respectively. In this project, the propeller was located at three different locations at front, middle and rear of the wing. The experimental data highlights an impact of propeller locations on lift, drag, pitching moment and vortex characteristic of the UAV model. Rear propeller configuration recorded the highest lift generation. Meanwhile, middle propeller configuration has the highest drag with increment by 2% to 15%. The results also show that the propeller advance ratio plays important roles in development of the primary vortex above the delta-winged model. The higher propeller advance ratio would decrease the development of the vortex on the wing, consequently limiting the lift generation and stall condition in which are disadvantageous for aircraft aerodynamic characteristics. The lift coefficients decrease by 7% when the propeller advance ratio is increased from 0.98 to 1.20. Lastly, suction effect from the propeller has improved the vortex properties better than blowing mechanism in which is beneficial for the delta-winged UAV propeller selection.
format	Thesis
qualification_name	Doctor of Philosophy (PhD.)
qualification_level	Doctorate
author	Kasim, Khushairi Amri
author_facet	Kasim, Khushairi Amri
author_sort	Kasim, Khushairi Amri
title	Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model
title_short	Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model
title_full	Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model
title_fullStr	Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model
title_full_unstemmed	Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model
title_sort	propeller locations study on delta-winged unmanned aerial vehicle (uav) model
granting_institution	Universiti Teknologi Malaysia, Faculty of Mechanical Engineering
granting_department	Faculty of Mechanical Engineering
publishDate	2017
url	http://eprints.utm.my/id/eprint/78655/1/KhushairiAmriKasimMFKM2017.pdf
_version_	1747818038841835520

Propeller locations study on delta-winged unmanned aerial vehicle (UAV) model

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