Half model testing for canard of a hybrid buoyant aircraft

Due to the interference effects, the intrinsic aerodynamic parameters obtained from the individual component testing are always fundamentally different than those obtained for complete model testing. Consideration and limitation for such testing need to be taken into account in any design work r...

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Main Authors:	UlHaque, Anwar, Asrar, Waqar, Omar, Ashraf Ali, Sulaeman, Erwin, Syed Mohamed Ali, Jaffar
Format:	Article
Language:	English
Published:	World Academy of Science, Engineering and Technology 2015
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/46474/ http://irep.iium.edu.my/46474/ http://irep.iium.edu.my/46474/1/Half-Model-Testing-for-Canard-of-a-Hybrid-Buoyant-Aircraft.pdf

id	iium-46474
recordtype	eprints
spelling	iium-464742017-11-21T08:28:04Z http://irep.iium.edu.my/46474/ Half model testing for canard of a hybrid buoyant aircraft UlHaque, Anwar Asrar, Waqar Omar, Ashraf Ali Sulaeman, Erwin Syed Mohamed Ali, Jaffar TL500 Aeronautics Due to the interference effects, the intrinsic aerodynamic parameters obtained from the individual component testing are always fundamentally different than those obtained for complete model testing. Consideration and limitation for such testing need to be taken into account in any design work related to the component buildup method. In this paper, the scaled model of a straight rectangular canard of a hybrid buoyant aircraft is tested at 50 m/s in IIUM-LSWT (Low Speed Wind Tunnel). Model and its attachment with the balance are kept rigid to have results free from the aeroelastic distortion. Based on the velocity profile of the test section’s floor; the height of the model is kept equal to the corresponding boundary layer displacement. Balance measurements provide valuable but limited information of overall aerodynamic behavior of the model. Zero lift coefficient is obtained at -2.2o and the corresponding drag coefficient was found to be less than that at zero angle of attack. As a part of the validation of low fidelity tool, plot of lift coefficient plot was verified by the experimental data and except the value of zero lift coefficients, the overall trend has under predicted the lift coefficient. Based on this comparative study, a correction factor of 1.36 is proposed for lift curve slope obtained from the panel method. World Academy of Science, Engineering and Technology 2015 Article PeerReviewed application/pdf en http://irep.iium.edu.my/46474/1/Half-Model-Testing-for-Canard-of-a-Hybrid-Buoyant-Aircraft.pdf UlHaque, Anwar and Asrar, Waqar and Omar, Ashraf Ali and Sulaeman, Erwin and Syed Mohamed Ali, Jaffar (2015) Half model testing for canard of a hybrid buoyant aircraft. International Journal of Mechanical, Aerospace, Industrial, Mechatronic and Manufacturing Engineering, 9 (10). pp. 1544-1547. http://waset.org/publications/10002489/half-model-testing-for-canard-of-a-hybrid-buoyant-aircraft
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL500 Aeronautics
spellingShingle	TL500 Aeronautics UlHaque, Anwar Asrar, Waqar Omar, Ashraf Ali Sulaeman, Erwin Syed Mohamed Ali, Jaffar Half model testing for canard of a hybrid buoyant aircraft
description	Due to the interference effects, the intrinsic aerodynamic parameters obtained from the individual component testing are always fundamentally different than those obtained for complete model testing. Consideration and limitation for such testing need to be taken into account in any design work related to the component buildup method. In this paper, the scaled model of a straight rectangular canard of a hybrid buoyant aircraft is tested at 50 m/s in IIUM-LSWT (Low Speed Wind Tunnel). Model and its attachment with the balance are kept rigid to have results free from the aeroelastic distortion. Based on the velocity profile of the test section’s floor; the height of the model is kept equal to the corresponding boundary layer displacement. Balance measurements provide valuable but limited information of overall aerodynamic behavior of the model. Zero lift coefficient is obtained at -2.2o and the corresponding drag coefficient was found to be less than that at zero angle of attack. As a part of the validation of low fidelity tool, plot of lift coefficient plot was verified by the experimental data and except the value of zero lift coefficients, the overall trend has under predicted the lift coefficient. Based on this comparative study, a correction factor of 1.36 is proposed for lift curve slope obtained from the panel method.
format	Article
author	UlHaque, Anwar Asrar, Waqar Omar, Ashraf Ali Sulaeman, Erwin Syed Mohamed Ali, Jaffar
author_facet	UlHaque, Anwar Asrar, Waqar Omar, Ashraf Ali Sulaeman, Erwin Syed Mohamed Ali, Jaffar
author_sort	UlHaque, Anwar
title	Half model testing for canard of a hybrid buoyant aircraft
title_short	Half model testing for canard of a hybrid buoyant aircraft
title_full	Half model testing for canard of a hybrid buoyant aircraft
title_fullStr	Half model testing for canard of a hybrid buoyant aircraft
title_full_unstemmed	Half model testing for canard of a hybrid buoyant aircraft
title_sort	half model testing for canard of a hybrid buoyant aircraft
publisher	World Academy of Science, Engineering and Technology
publishDate	2015
url	http://irep.iium.edu.my/46474/ http://irep.iium.edu.my/46474/ http://irep.iium.edu.my/46474/1/Half-Model-Testing-for-Canard-of-a-Hybrid-Buoyant-Aircraft.pdf
first_indexed	2023-09-18T21:06:11Z
last_indexed	2023-09-18T21:06:11Z
_version_	1777410948281139200

Half model testing for canard of a hybrid buoyant aircraft

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