Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing

In subsonic wind tunnel testing, a scaled down model should be rigid enough such that due to model deformations, there is no change in the flow field. In this regard, a computational study is carried out to analyze the stress distribution and deformation of a scaled down model of a hybrid buoya...

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Main Authors:	, Anwar-Ul-Haque, Nugraha, Fauzul, Erawan, Dadang F, Asrar, Waqar, Sulaeman, Erwin
Format:	Conference or Workshop Item
Language:	English English English
Published:	IEEE 2017
Subjects:	T Technology (General)
Online Access:	http://irep.iium.edu.my/62919/ http://irep.iium.edu.my/62919/ http://irep.iium.edu.my/62919/ http://irep.iium.edu.my/62919/1/62919%20Structural%20Design%20of%20Hybrid.pdf http://irep.iium.edu.my/62919/2/62919%20Structural%20Design%20of%20Hybrid%20SCOPUS.pdf http://irep.iium.edu.my/62919/13/62919%20Structural%20design%20of%20hybrid%20buoyant%20WOS.pdf

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spelling	iium-629192019-08-18T07:44:38Z http://irep.iium.edu.my/62919/ Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing , Anwar-Ul-Haque Nugraha, Fauzul Erawan, Dadang F Asrar, Waqar Sulaeman, Erwin T Technology (General) In subsonic wind tunnel testing, a scaled down model should be rigid enough such that due to model deformations, there is no change in the flow field. In this regard, a computational study is carried out to analyze the stress distribution and deformation of a scaled down model of a hybrid buoyant (HB) aircraft, while tested in wind tunnel test section at its maximum operational speed. Model is simulated in computational fluid dynamics (CFD) to get the pressure distribution on its surface as an input for computational engineering analysis. Model is assumed as solid model and using aluminum material for the aerodynamic surfaces. Some assumptions such as steady state, smooth wall, incompressible, isotropic material and filled solid are applied to the said model to simplify the computational case. In order to know the maximum stress and deformation of the lifting surfaces of the model, we only analyze HB aircraft at maximum angle of attack, before the stall will occur. The value of angle of attack at given maximum CL was set as HB aircraft’s model position for estimation of the deformations when being simulated using ANSYS®. A number of CFD cases were run to get the coefficient of lift versus angle of attack curve, including the value of angle of attack at maximum coefficient of lift of the wing before the stall. The maximum displacement was found at the tip of the wing and its value is 37 mm. Following any major design change of the airframe of the model, a quick numerical analysis is recommended to determine if there any significant alterations to the original model. IEEE 2017-03-02 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/62919/1/62919%20Structural%20Design%20of%20Hybrid.pdf application/pdf en http://irep.iium.edu.my/62919/2/62919%20Structural%20Design%20of%20Hybrid%20SCOPUS.pdf application/pdf en http://irep.iium.edu.my/62919/13/62919%20Structural%20design%20of%20hybrid%20buoyant%20WOS.pdf , Anwar-Ul-Haque and Nugraha, Fauzul and Erawan, Dadang F and Asrar, Waqar and Sulaeman, Erwin (2017) Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing. In: 14th International Bhurban Conference on Applied Sciences & Technology (IBCAST), 10th-14th January 2017, Islamabad, Pakistan. http://ieeexplore.ieee.org/document/7868043/ 10.1109/IBCAST.2017.7868043
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English English
topic	T Technology (General)
spellingShingle	T Technology (General) , Anwar-Ul-Haque Nugraha, Fauzul Erawan, Dadang F Asrar, Waqar Sulaeman, Erwin Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing
description	In subsonic wind tunnel testing, a scaled down model should be rigid enough such that due to model deformations, there is no change in the flow field. In this regard, a computational study is carried out to analyze the stress distribution and deformation of a scaled down model of a hybrid buoyant (HB) aircraft, while tested in wind tunnel test section at its maximum operational speed. Model is simulated in computational fluid dynamics (CFD) to get the pressure distribution on its surface as an input for computational engineering analysis. Model is assumed as solid model and using aluminum material for the aerodynamic surfaces. Some assumptions such as steady state, smooth wall, incompressible, isotropic material and filled solid are applied to the said model to simplify the computational case. In order to know the maximum stress and deformation of the lifting surfaces of the model, we only analyze HB aircraft at maximum angle of attack, before the stall will occur. The value of angle of attack at given maximum CL was set as HB aircraft’s model position for estimation of the deformations when being simulated using ANSYS®. A number of CFD cases were run to get the coefficient of lift versus angle of attack curve, including the value of angle of attack at maximum coefficient of lift of the wing before the stall. The maximum displacement was found at the tip of the wing and its value is 37 mm. Following any major design change of the airframe of the model, a quick numerical analysis is recommended to determine if there any significant alterations to the original model.
format	Conference or Workshop Item
author	, Anwar-Ul-Haque Nugraha, Fauzul Erawan, Dadang F Asrar, Waqar Sulaeman, Erwin
author_facet	, Anwar-Ul-Haque Nugraha, Fauzul Erawan, Dadang F Asrar, Waqar Sulaeman, Erwin
author_sort	, Anwar-Ul-Haque
title	Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing
title_short	Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing
title_full	Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing
title_fullStr	Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing
title_full_unstemmed	Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing
title_sort	structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing
publisher	IEEE
publishDate	2017
url	http://irep.iium.edu.my/62919/ http://irep.iium.edu.my/62919/ http://irep.iium.edu.my/62919/ http://irep.iium.edu.my/62919/1/62919%20Structural%20Design%20of%20Hybrid.pdf http://irep.iium.edu.my/62919/2/62919%20Structural%20Design%20of%20Hybrid%20SCOPUS.pdf http://irep.iium.edu.my/62919/13/62919%20Structural%20design%20of%20hybrid%20buoyant%20WOS.pdf
first_indexed	2023-09-18T21:29:10Z
last_indexed	2023-09-18T21:29:10Z
_version_	1777412394296803328

Structural design of hybrid buoyant aircraft's model for subsonic wind tunnel testing

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