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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/62919/1/62919%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
http://irep.iium.edu.my/62919/
http://ieeexplore.ieee.org/document/7868043/
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spelling my.iium.irep.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
institution Universiti Islam Antarabangsa Malaysia
building IIUM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider International Islamic University Malaysia
content_source IIUM Repository (IREP)
url_provider http://irep.iium.edu.my/
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/62919/1/62919%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
http://irep.iium.edu.my/62919/
http://ieeexplore.ieee.org/document/7868043/
_version_ 1643619702843375616
score 13.211869

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