Flow visualization over a circular planform wing
circular plan form wing at high Reynolds numbers has been carried out numerically. Commercial software STAR-CCM+ was used for the investigation. The numerical results were presented in terms of flow visualization, pressure over the wing, velocity contour and streamlines, lift and drag coefficients f...
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my.iium.irep.331382013-12-09T04:04:25Z http://irep.iium.edu.my/33138/ Flow visualization over a circular planform wing Suliman , M. M. Ali Omar, Ashraf Ali Syed Mohamed Ali, Jaffar TL500 Aeronautics circular plan form wing at high Reynolds numbers has been carried out numerically. Commercial software STAR-CCM+ was used for the investigation. The numerical results were presented in terms of flow visualization, pressure over the wing, velocity contour and streamlines, lift and drag coefficients for angle of attacks ranging from 0˚ to 30˚ for Reynolds numbers of 55,0000. The results showed that the distribution of the pressure is dominated by vortices at high angle of attack. The results also showed there is a large separation region located on the trailing edge of the elevator and the cockpit region. It is evident from the study that this type of wing configurations plays a very important role in delaying or preventing the flow separation. The result showed a good agreement with available experimental data. 2013 Conference or Workshop Item REM application/pdf en http://irep.iium.edu.my/33138/1/Paper_30158_-_Camera_ready.pdf application/pdf en http://irep.iium.edu.my/33138/4/programbookicmaae13.pdf Suliman , M. M. Ali and Omar, Ashraf Ali and Syed Mohamed Ali, Jaffar (2013) Flow visualization over a circular planform wing. In: 2nd International Conference on Mechanical, Automotive and Aerospace Engineering (ICMAAE' 13), 2-4 July 2013, Kuala Lumpur, Malaysia. (Unpublished) |
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TL500 Aeronautics Suliman , M. M. Ali Omar, Ashraf Ali Syed Mohamed Ali, Jaffar Flow visualization over a circular planform wing |
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circular plan form wing at high Reynolds numbers has been carried out numerically. Commercial software STAR-CCM+ was used for the investigation. The numerical results were presented in terms of flow visualization, pressure over the wing, velocity contour and streamlines, lift and drag coefficients for angle of attacks ranging from 0˚ to 30˚ for Reynolds numbers of 55,0000. The results showed that the distribution of the pressure is dominated by vortices at high angle of attack. The results also showed there is a large separation region located on the trailing edge of the elevator and the cockpit region. It is evident from the study that this type of wing configurations plays a very important role in delaying or preventing the flow separation. The result showed a good agreement with available experimental data. |
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Conference or Workshop Item |
author |
Suliman , M. M. Ali Omar, Ashraf Ali Syed Mohamed Ali, Jaffar |
author_facet |
Suliman , M. M. Ali Omar, Ashraf Ali Syed Mohamed Ali, Jaffar |
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Suliman , M. M. Ali |
title |
Flow visualization over a circular planform wing |
title_short |
Flow visualization over a circular planform wing |
title_full |
Flow visualization over a circular planform wing |
title_fullStr |
Flow visualization over a circular planform wing |
title_full_unstemmed |
Flow visualization over a circular planform wing |
title_sort |
flow visualization over a circular planform wing |
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2013 |
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http://irep.iium.edu.my/33138/1/Paper_30158_-_Camera_ready.pdf http://irep.iium.edu.my/33138/4/programbookicmaae13.pdf http://irep.iium.edu.my/33138/ |
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