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Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil

Take-off and landing are the critical phases of an aircraft flight where there is a high demand of lift force at the lowest stalling speed of aircraft. Use of different techniques to increase the lift force during these phases of flight is one of the prime objectives in the design of an aircraft win...

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Main Authors: Syed Mohamed Ali, Jaffar, Amran, Mohd Farid, Mohamad, Nurul Aziz
Format: Article
Language:English
English
Published: Semarak Ilmu Publishing 2021
Subjects:
TL500 Aeronautics
Online Access:http://irep.iium.edu.my/93524/1/Acceptance%20Proof%20Email.pdf
http://irep.iium.edu.my/93524/8/93524_Experimental%20study%20on%20the%20effect%20of%20boundary.pdf
http://irep.iium.edu.my/93524/
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spelling my.iium.irep.935242021-11-11T06:46:15Z http://irep.iium.edu.my/93524/ Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil Syed Mohamed Ali, Jaffar Amran, Mohd Farid Mohamad, Nurul Aziz TL500 Aeronautics Take-off and landing are the critical phases of an aircraft flight where there is a high demand of lift force at the lowest stalling speed of aircraft. Use of different techniques to increase the lift force during these phases of flight is one of the prime objectives in the design of an aircraft wing. Delaying and eliminating flow separation using boundary layer control (BLC) techniques will improve the aerodynamic characteristics of a wing. This work presents an experimental study on the effect of BLC on the aerodynamic characteristics of NACA 0021 aerofoil. Both the techniques of blowing and suction has been considered in this study. Model was built using composites and tested in a subsonic wind tunnel integrated with a compressor/vacuum pump setting for to control the boundary layer on the aerofoil. Firstly, the model with 20 pressure tappings was tested without BLC and the point of flow separation was noted. Later, the suction and blowing holes were made suitably in the model and equipped with a compressor/vacuum pump to control the boundary layer and study the effects of it on the performance of NACA 0021 aerofoil. As expected, the BLC by both the techniques show improvement in the maximum lift coefficient. Semarak Ilmu Publishing 2021 Article PeerReviewed application/pdf en http://irep.iium.edu.my/93524/1/Acceptance%20Proof%20Email.pdf application/pdf en http://irep.iium.edu.my/93524/8/93524_Experimental%20study%20on%20the%20effect%20of%20boundary.pdf Syed Mohamed Ali, Jaffar and Amran, Mohd Farid and Mohamad, Nurul Aziz (2021) Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences. ISSN 2811 - 3950 (In Press)
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
topic TL500 Aeronautics
spellingShingle TL500 Aeronautics
Syed Mohamed Ali, Jaffar
Amran, Mohd Farid
Mohamad, Nurul Aziz
Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil
description Take-off and landing are the critical phases of an aircraft flight where there is a high demand of lift force at the lowest stalling speed of aircraft. Use of different techniques to increase the lift force during these phases of flight is one of the prime objectives in the design of an aircraft wing. Delaying and eliminating flow separation using boundary layer control (BLC) techniques will improve the aerodynamic characteristics of a wing. This work presents an experimental study on the effect of BLC on the aerodynamic characteristics of NACA 0021 aerofoil. Both the techniques of blowing and suction has been considered in this study. Model was built using composites and tested in a subsonic wind tunnel integrated with a compressor/vacuum pump setting for to control the boundary layer on the aerofoil. Firstly, the model with 20 pressure tappings was tested without BLC and the point of flow separation was noted. Later, the suction and blowing holes were made suitably in the model and equipped with a compressor/vacuum pump to control the boundary layer and study the effects of it on the performance of NACA 0021 aerofoil. As expected, the BLC by both the techniques show improvement in the maximum lift coefficient.
format Article
author Syed Mohamed Ali, Jaffar
Amran, Mohd Farid
Mohamad, Nurul Aziz
author_facet Syed Mohamed Ali, Jaffar
Amran, Mohd Farid
Mohamad, Nurul Aziz
author_sort Syed Mohamed Ali, Jaffar
title Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil
title_short Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil
title_full Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil
title_fullStr Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil
title_full_unstemmed Experimental study on the effect of boundary layer control on the aerodynamics characteristics of NACA 0021 Aerofoil
title_sort experimental study on the effect of boundary layer control on the aerodynamics characteristics of naca 0021 aerofoil
publisher Semarak Ilmu Publishing
publishDate 2021
url http://irep.iium.edu.my/93524/1/Acceptance%20Proof%20Email.pdf
http://irep.iium.edu.my/93524/8/93524_Experimental%20study%20on%20the%20effect%20of%20boundary.pdf
http://irep.iium.edu.my/93524/
_version_ 1717093016866390016
score 13.211869

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