Flow separation occurs due to boundary layer formation over the airfoil surface. It has significant effects on aerial application. The wake formation, due to the separation of boundary layer, attenuates the pressure differential on airfoil-especially at high angle of attack. The application of momentum injection via moving surface in the flow field energizes the flow field and improves the adverse pressure gradient and attenuates the wake formation. This study focuses on the drag reduction by improving adverse pressure gradient and narrowing the wake zone of 2D NACA 0012 by moving surface through Numerical Analysis (CFD). Selection of the speed of moving surface for investigation purpose and to get aerodynamic advantage. So one slot with a width of 5% of the chord length is placed at suction surface for single moving surface starting from 0.05c to 0.1c and for double moving surface two slots of 5% of the chord length are placed, one at suction surface starting from 0.05c to 0.1c and the other at pressure side from 0.05c to 0.1c. Momentum injection into the flow field narrows the wake zone in the vicinity of trailing edge of the airfoil. By momentum injection through single moving surface, when the surface speed ratio (u/U) is 1, it is possible to reduce the drag coefficient on an average by 13% and for double moving surface it is possible to reduce the drag coefficient on an average by 14.22%.
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13 July 2018
INTERNATIONAL CONFERENCE ON MECHANICAL ENGINEERING: Proceedings of the 12th International Conference on Mechanical Engineering (ICME 2017)
20–22 December 2017
Dhaka, Bangladesh
Research Article|
July 13 2018
Numerical investigation of drag reduction using moving surface boundary layer control (MSBC) on NACA 0012 airfoil
Md. Iftha Khar;
Md. Iftha Khar
b)
1
Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET)
, Dhaka-1000, Bangladesh
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Kawkab Ahasan;
Kawkab Ahasan
a)
1
Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET)
, Dhaka-1000, Bangladesh
a)Corresponding author: [email protected]
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Mohammad Ali
Mohammad Ali
c)
1
Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET)
, Dhaka-1000, Bangladesh
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Md. Iftha Khar
1,b)
Kawkab Ahasan
1,a)
Mohammad Ali
1,c)
1
Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET)
, Dhaka-1000, Bangladesh
AIP Conf. Proc. 1980, 040011 (2018)
Citation
Md. Iftha Khar, Kawkab Ahasan, Mohammad Ali; Numerical investigation of drag reduction using moving surface boundary layer control (MSBC) on NACA 0012 airfoil. AIP Conf. Proc. 13 July 2018; 1980 (1): 040011. https://doi.org/10.1063/1.5044321
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