scholarly journals Moving Surface Boundary Layer Control Analysis and the Influence of the Magnus Effect on an Aerofoil with a Leading-Edge Rotating Cylinder

2019 ◽  
Author(s):  
Md. Abdus Salam ◽  
Bhuiyan Shameem Mahmood Ebna Hai ◽  
M. A. Taher Ali ◽  
Debanan Bhadra ◽  
Nafiz Ahmed Khan
Keyword(s):  
Boundary Layer ◽  
Free Stream ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Rotating Cylinder ◽  
Boundary Layer Control ◽  
Surface Boundary ◽  
Surface Boundary Layer ◽  
Lower Velocity ◽  
Layer Control

A number of experimental and numerical studies point out that incorporating a rotating cylinder can superiorly enhance the aerofoil performance, especially for higher velocity ratios. Yet, there have been less or no studies exploring the effects of lower velocity ratio at a higher Reynolds number. In the present study, we investigated the effects of Moving Surface Boundary-layer Control (MSBC) at lower velocity ratios (i.e. cylinder tangential velocity to free stream velocity) and higher Reynolds number on a symmetric aerofoil (e.g. NACA 0021) and an asymmetric aerofoil (e.g. NACA 23018). In particular, the aerodynamic performance with and without rotating cylinder at the leading edge of the NACA 0021 and NACA 23018 aerofoil was studied on the wind tunnel installed at Aerodynamics Laboratory. The aerofoil section was tested in the low subsonic wind tunnel, and the lift coefficient and the drag coefficient were studied for different angles of attack. The experiments were conducted for two Reynolds numbers: 200000 and 250000 corresponding to two free stream velocities: 20 m/s and 25 m/s, respectively, for six different angle of attacks (-5°, 0°, 5°, 10°, 15° and 20°). This study demonstrates that the incorporation of a leading edge rotating cylinder results in an increase of lift coefficient at lower angle of attacks (maximum around 33%) and delay in stall angle (from 10° to 15°) relative to the aerofoil without rotating cylinder.

scholarly journals Moving Surface Boundary Layer Control Analysis and the Influence of the Magnus Effect on an Aerofoil with a Leading-Edge Rotating Cylinder

2019 ◽  
Author(s):  
Md. Abdus Salam ◽  
Bhuiyan Shameem Mahmood Ebna Hai ◽  
M. A. Taher Ali ◽  
Debanan Bhadra ◽  
Nafiz Ahmed Khan
Keyword(s):  
Boundary Layer ◽  
Free Stream ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Rotating Cylinder ◽  
Boundary Layer Control ◽  
Surface Boundary ◽  
Surface Boundary Layer ◽  
Lower Velocity ◽  
Layer Control

A number of experimental and numerical studies point out that incorporating a rotating cylinder can superiorly enhance the aerofoil performance, especially for higher velocity ratios. Yet, there have been less or no studies exploring the effects of lower velocity ratio at a higher Reynolds number. In the present study, we investigated the effects of Moving Surface Boundary-layer Control (MSBC) at lower velocity ratios (i.e. cylinder tangential velocity to free stream velocity) and higher Reynolds number on a symmetric aerofoil (e.g. NACA 0021) and an asymmetric aerofoil (e.g. NACA 23018). In particular, the aerodynamic performance with and without rotating cylinder at the leading edge of the NACA 0021 and NACA 23018 aerofoil was studied on the wind tunnel installed at Aerodynamics Laboratory. The aerofoil section was tested in the low subsonic wind tunnel, and the lift coefficient and the drag coefficient were studied for different angles of attack. The experiments were conducted for two Reynolds numbers: 200000 and 250000 corresponding to two free stream velocities: 20 m/s and 25 m/s, respectively, for six different angle of attacks (-5°, 0°, 5°, 10°, 15° and 20°). This study demonstrates that the incorporation of a leading edge rotating cylinder results in an increase of lift coefficient at lower angle of attacks (maximum around 33%) and delay in stall angle (from 10° to 15°) relative to the aerofoil without rotating cylinder.

scholarly journals Numerical Analysis of Effect of Leading-Edge Rotating Cylinder on NACA0021 Symmetric Airfoil

2019 ◽  
Vol 4 (7) ◽  
pp. 11-17
Author(s):  
Md. Abdus Salam ◽  
Vikram Deshpande ◽  
Nafiz Ahmed Khan ◽  
M. A. Taher Ali
Keyword(s):  
Free Stream ◽  
Numerical Study ◽  
Tangential Velocity ◽  
Leading Edge ◽  
Rotating Cylinder ◽  
Aerodynamic Performance ◽  
Stream Velocity ◽  
Surface Boundary ◽  
Lower Velocity ◽  
Numerical Studies

The moving surface boundary control (MSBC) has been a Centre stage study for last 2-3 decades. The preliminary aim of the study was to ascertain whether the concept can improve the airfoil characteristics. Number of experimental and numerical studies pointed out that the MSBC can superiorly enhance the airfoil performance albeit for higher velocity ratios (i.e. cylinder tangential velocity to free stream velocity). Although abundant research has been undertaken in this area on different airfoil performances but no attempt was seen to study effect of MSBC on NACA0021 airfoil for and also effects of lower velocity ratios. Thus, present paper focusses on numerical study of modified NACA 0021 airfoil with leading edge rotating cylinder for velocity ratios (i.e.) between 1 to 1.78 at different angles of attack. The numerical study indicates that the modified airfoil possess better aerodynamic performance than the base airfoil even at lower velocity ratios (i.e. for velocity ratios 0.356 and beyond). The study also focusses on reason for improvement in aerodynamic performance by close look at various parameters.

Movi-ng-Surface Boundary-Layer Control for Aircraft Operation at High Incidence

1981 ◽  
Vol 18 (11) ◽  
pp. 963-968 ◽  
Author(s):  
V. J. Modi ◽  
J. L. C. Sun ◽  
T. Akutsu ◽  
P. Lake ◽  
K. McMillan ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Control ◽  
Surface Boundary ◽  
Surface Boundary Layer ◽  
High Incidence ◽  
Layer Control

scholarly journals FLOW CONTROL USING MOVING SURFACE AT THE LEADING EDGE OF AEROFOIL

2018 ◽  
Vol 47 (1) ◽  
pp. 45-50 ◽  
Author(s):  
Kh Md Faisal ◽  
M A Salam ◽  
M A Taher Ali ◽  
Md. Samad Sarkar ◽  
Wasiul Safa ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Flow Control ◽  
Control Strategies ◽  
Active Flow Control ◽  
Lift Coefficient ◽  
Research Work ◽  
Leading Edge ◽  
Surface Boundary ◽  
Moving Surface ◽  
Surface Boundary Layer

Flow control is a significant topic of research in the field of aviation. Researchers in this field are continuously trying their best to find various flow control strategies in order to extract aerodynamic benefits by applying them. Applying moving surface at the leading edge of aerofoil is a type of strategy among the various types of active flow control strategies. In the present research work a rotating cylinder is added on the leading edge of the aerofoil as a moving surface in order to control the flow over its surface. The moving surface boundary layer control is applied to NACA 0018 airfoil for investigating its aerodynamic benefits and effectiveness. The moving surface is created by rotating a smooth cylinder at the leading edge of the aerofoil. The peripheral velocity of the cylinder injects momentum to the upper surface boundary layer of the aerofoil and thus delays its separation. This results in the gain in both the maximum lift coefficient and the stall angle. The work has been done at four different Reynolds Number i.e., at Re = 1.4 X 10^5, 1.85 X 10^5, 2.3 X 10^5, 2.8 X 10^5 at different angles of attack.

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