Wind tunnel testing of hybrid buoyant aerial vehicle

Purpose – Realistic data bank of aerodynamic and stability derivatives is still missing for hybrid buoyant aerial vehicles. Such vehicles take-off and land similar to an aircraft with their partial weight balanced by the aerostatic lift. The purpose of this paper is to use wind tunnel testing for a...

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Main Authors:	UlHaque, Anwar, Asrar, Waqar, Omar, Ashraf Ali, Sulaeman, Erwin, Ali, JS Mohamed
Format:	Article
Language:	English English English
Published:	Emerald Publishing Limited 2017
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/55356/ http://irep.iium.edu.my/55356/ http://irep.iium.edu.my/55356/ http://irep.iium.edu.my/55356/1/55356_Wind%20tunnel%20testing%20of%20hybrid.pdf http://irep.iium.edu.my/55356/2/55356-Wind%20tunnel%20testing%20of%20hybrid%20buoyant_SCOPUS.pdf http://irep.iium.edu.my/55356/3/55356_Wind%20tunnel%20testing%20of%20hybrid_WOS.pdf

id	iium-55356
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spelling	iium-553562017-11-07T09:18:39Z http://irep.iium.edu.my/55356/ Wind tunnel testing of hybrid buoyant aerial vehicle UlHaque, Anwar Asrar, Waqar Omar, Ashraf Ali Sulaeman, Erwin Ali, JS Mohamed TL500 Aeronautics Purpose – Realistic data bank of aerodynamic and stability derivatives is still missing for hybrid buoyant aerial vehicles. Such vehicles take-off and land similar to an aircraft with their partial weight balanced by the aerostatic lift. The purpose of this paper is to use wind tunnel testing for a better understanding of the aerodynamic and static stability behavior of such vehicles. Design/methodology/approach – The effect of wing on the aerodynamic and static stability characteristics of a clean configuration hybrid buoyant is analyzed. The free stream velocity is 20 m/s, and ranges of angle of attack and side slip angle are from 8° to 12° and 16°, respectively. Data are corrected to account for the effect of strut interference and zero load condition. The maximum blockage of the model with respect to the cross-section area of the test section is about 2.7 per cent. Findings – A hybrid model manufactured by using wood and metal is an optimum solution with less number of parts. The vehicle is statically, longitudinally and directionally stable. Wings designed to fulfill the partial requirement of lift contribute significantly to counter the huge moment generated by the voluminous hull for centre of gravity location ahead of the leading edge of the wing. Research limitations/implications – There are number of manufacturing constraints for scaling down a model of a hybrid buoyant aerial vehicle configuration. Specially, the thickness of the wing limits the testing envelop of angle of attack and free stream velocity. Practical implications – The data presented here are a preliminary guide for further work on larger size models. The data may also be used to build and perform flight tests on small full-scale instrumented models and to obtain flight dynamics data. Originality/value – The estimated aerodynamic and stability derivatives and slopes can be utilized in future for multidisciplinary design. Emerald Publishing Limited 2017 Article PeerReviewed application/pdf en http://irep.iium.edu.my/55356/1/55356_Wind%20tunnel%20testing%20of%20hybrid.pdf application/pdf en http://irep.iium.edu.my/55356/2/55356-Wind%20tunnel%20testing%20of%20hybrid%20buoyant_SCOPUS.pdf application/pdf en http://irep.iium.edu.my/55356/3/55356_Wind%20tunnel%20testing%20of%20hybrid_WOS.pdf UlHaque, Anwar and Asrar, Waqar and Omar, Ashraf Ali and Sulaeman, Erwin and Ali, JS Mohamed (2017) Wind tunnel testing of hybrid buoyant aerial vehicle. Aircraft Engineering and Aerospace Technology, 89 (1). pp. 99-105. ISSN 0002-2667 http://www.emeraldinsight.com/doi/abs/10.1108/AEAT-06-2015-0165 10.1108/AEAT-06-2015-0165
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English English
topic	TL500 Aeronautics
spellingShingle	TL500 Aeronautics UlHaque, Anwar Asrar, Waqar Omar, Ashraf Ali Sulaeman, Erwin Ali, JS Mohamed Wind tunnel testing of hybrid buoyant aerial vehicle
description	Purpose – Realistic data bank of aerodynamic and stability derivatives is still missing for hybrid buoyant aerial vehicles. Such vehicles take-off and land similar to an aircraft with their partial weight balanced by the aerostatic lift. The purpose of this paper is to use wind tunnel testing for a better understanding of the aerodynamic and static stability behavior of such vehicles. Design/methodology/approach – The effect of wing on the aerodynamic and static stability characteristics of a clean configuration hybrid buoyant is analyzed. The free stream velocity is 20 m/s, and ranges of angle of attack and side slip angle are from 8° to 12° and 16°, respectively. Data are corrected to account for the effect of strut interference and zero load condition. The maximum blockage of the model with respect to the cross-section area of the test section is about 2.7 per cent. Findings – A hybrid model manufactured by using wood and metal is an optimum solution with less number of parts. The vehicle is statically, longitudinally and directionally stable. Wings designed to fulfill the partial requirement of lift contribute significantly to counter the huge moment generated by the voluminous hull for centre of gravity location ahead of the leading edge of the wing. Research limitations/implications – There are number of manufacturing constraints for scaling down a model of a hybrid buoyant aerial vehicle configuration. Specially, the thickness of the wing limits the testing envelop of angle of attack and free stream velocity. Practical implications – The data presented here are a preliminary guide for further work on larger size models. The data may also be used to build and perform flight tests on small full-scale instrumented models and to obtain flight dynamics data. Originality/value – The estimated aerodynamic and stability derivatives and slopes can be utilized in future for multidisciplinary design.
format	Article
author	UlHaque, Anwar Asrar, Waqar Omar, Ashraf Ali Sulaeman, Erwin Ali, JS Mohamed
author_facet	UlHaque, Anwar Asrar, Waqar Omar, Ashraf Ali Sulaeman, Erwin Ali, JS Mohamed
author_sort	UlHaque, Anwar
title	Wind tunnel testing of hybrid buoyant aerial vehicle
title_short	Wind tunnel testing of hybrid buoyant aerial vehicle
title_full	Wind tunnel testing of hybrid buoyant aerial vehicle
title_fullStr	Wind tunnel testing of hybrid buoyant aerial vehicle
title_full_unstemmed	Wind tunnel testing of hybrid buoyant aerial vehicle
title_sort	wind tunnel testing of hybrid buoyant aerial vehicle
publisher	Emerald Publishing Limited
publishDate	2017
url	http://irep.iium.edu.my/55356/ http://irep.iium.edu.my/55356/ http://irep.iium.edu.my/55356/ http://irep.iium.edu.my/55356/1/55356_Wind%20tunnel%20testing%20of%20hybrid.pdf http://irep.iium.edu.my/55356/2/55356-Wind%20tunnel%20testing%20of%20hybrid%20buoyant_SCOPUS.pdf http://irep.iium.edu.my/55356/3/55356_Wind%20tunnel%20testing%20of%20hybrid_WOS.pdf
first_indexed	2018-09-07T07:29:30Z
last_indexed	2018-09-07T07:29:30Z
_version_	1610932940327354368

Wind tunnel testing of hybrid buoyant aerial vehicle

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