The effects of reynolds number on flow separation of Naca Aerofoil
The purpose of this study is to investigate the flow separation above UTM 2D Airfoil at three different Reynolds numbers which are 1 × 106, 1.5 × 106 and 2 × 106 using pressure distribution method and flow visualization. The experiment was conducted in UTM-LST (Low Speed Tunnel). The pressure distri...
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my.utm.824612019-10-08T08:07:04Z http://eprints.utm.my/id/eprint/82461/ The effects of reynolds number on flow separation of Naca Aerofoil Ab. Wahid, Mastura Abdul Hakim, Muhammad Syahmi Dahalan, Md. Nizam Mansor, Shuhaimi Wan Ali, Wan Khairuddin Othman, Norazila Mat, Shabudin TJ Mechanical engineering and machinery The purpose of this study is to investigate the flow separation above UTM 2D Airfoil at three different Reynolds numbers which are 1 × 106, 1.5 × 106 and 2 × 106 using pressure distribution method and flow visualization. The experiment was conducted in UTM-LST (Low Speed Tunnel). The pressure distribution is done on three different wing span, which are 40%, 50% and 70%m of span and was measured and plotted to observe the flow characteristic at angle of attack from 0° to 35° for all three different Reynolds numbers. The flow visualization method was done at 10m/s, 20m/s and 30m/s airspeed from 0° to 18°. It is concluded that the Reynolds number of 1 × 106 separates at 16° Reynolds number of 1.5 × 106 separates at 18° and Reynolds number of 2 × 106 separates at 20°. 2018 Conference or Workshop Item PeerReviewed Ab. Wahid, Mastura and Abdul Hakim, Muhammad Syahmi and Dahalan, Md. Nizam and Mansor, Shuhaimi and Wan Ali, Wan Khairuddin and Othman, Norazila and Mat, Shabudin (2018) The effects of reynolds number on flow separation of Naca Aerofoil. In: The 1st International Symposium on Fluid Mechanics and Thermal Sciences. |
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TJ Mechanical engineering and machinery Ab. Wahid, Mastura Abdul Hakim, Muhammad Syahmi Dahalan, Md. Nizam Mansor, Shuhaimi Wan Ali, Wan Khairuddin Othman, Norazila Mat, Shabudin The effects of reynolds number on flow separation of Naca Aerofoil |
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The purpose of this study is to investigate the flow separation above UTM 2D Airfoil at three different Reynolds numbers which are 1 × 106, 1.5 × 106 and 2 × 106 using pressure distribution method and flow visualization. The experiment was conducted in UTM-LST (Low Speed Tunnel). The pressure distribution is done on three different wing span, which are 40%, 50% and 70%m of span and was measured and plotted to observe the flow characteristic at angle of attack from 0° to 35° for all three different Reynolds numbers. The flow visualization method was done at 10m/s, 20m/s and 30m/s airspeed from 0° to 18°. It is concluded that the Reynolds number of 1 × 106 separates at 16° Reynolds number of 1.5 × 106 separates at 18° and Reynolds number of 2 × 106 separates at 20°. |
format |
Conference or Workshop Item |
author |
Ab. Wahid, Mastura Abdul Hakim, Muhammad Syahmi Dahalan, Md. Nizam Mansor, Shuhaimi Wan Ali, Wan Khairuddin Othman, Norazila Mat, Shabudin |
author_facet |
Ab. Wahid, Mastura Abdul Hakim, Muhammad Syahmi Dahalan, Md. Nizam Mansor, Shuhaimi Wan Ali, Wan Khairuddin Othman, Norazila Mat, Shabudin |
author_sort |
Ab. Wahid, Mastura |
title |
The effects of reynolds number on flow separation of Naca Aerofoil |
title_short |
The effects of reynolds number on flow separation of Naca Aerofoil |
title_full |
The effects of reynolds number on flow separation of Naca Aerofoil |
title_fullStr |
The effects of reynolds number on flow separation of Naca Aerofoil |
title_full_unstemmed |
The effects of reynolds number on flow separation of Naca Aerofoil |
title_sort |
effects of reynolds number on flow separation of naca aerofoil |
publishDate |
2018 |
url |
http://eprints.utm.my/id/eprint/82461/ |
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1651866660242456576 |
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13.18916 |