Improvement in aerodynamic performance of NACA0021 airfoil using moving surface boundary layer: A computational study

2019 ◽  
Author(s):  
Md. Abdus Salam ◽  
Vikram Deshpande ◽  
Shoyon Panday ◽  
Nafiz Ahmed Khan ◽  
M. A. Taher Ali
Keyword(s):  
Boundary Layer ◽  
Computational Study ◽  
Aerodynamic Performance ◽  
Surface Boundary ◽  
Moving Surface ◽  
Surface Boundary Layer

scholarly journals Moving Surface Boundary Layer Technique For NACA 0012 Airfoil At Ultra-Low Reynolds Number

2019 ◽  
Vol 9 (2) ◽  
pp. 3788-3795
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Low Reynolds Number ◽  
Leading Edge ◽  
Control Technique ◽  
Surface Boundary ◽  
Moving Surface ◽  
Surface Boundary Layer ◽  
Number Range ◽  
Low Reynolds

Application of moving surface boundary layer control technique has been confined to relatively high Reynolds numbers. The present paper reports a numerical study of application of the above flow technique in the ultra-low Reynolds number range. A two dimensional incompressible unstructured grid based Navier Stokes solver has been used for conducting the numerical studies. Moving surface has been applied at three different portions on the airfoil surface, firstly, in the form of a rotating leading edge portion of the airfoil, secondly, a continuous moving surface from leading edge of airfoil to 57% of the chord along the leeward surface of the airfoil and thirdly a continuous moving surface from leading edge to 97% of the chord along the leeward surface of the airfoil. All the moving surface configurations show improvement of aerodynamic performance of the airfoil through enhancement of lift and decrement of drag as compared to a fixed surface one

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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