Effects of Laminar Boundary Layer Control by Suction of a Stationary and Compressible Flow Around a Two-Dimensional Profile
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Abstract
Reducing aircraft energy consumption is a major challenge for aerodynamics specialists. This consumption is closely linked to the drag force. Drag has always hampered the smooth movement of the aircraft. To solve this problem, numerous theoretical and experimental studies have been conducted to eliminate or reduce the negative effects of drag. Knowing that the friction due to the turbulent boundary layer is much higher than that due to the laminar boundary layer, this generates greater energy consumption and, consequently, a degradation of aerodynamic performance. Much research has been conducted to ensure the persistence of the laminar layer while pushing the onset of the turbulent boundary layer towards the trailing edge, which also allows for greater laminarity. Controlling the laminar boundary layer by suction makes it possible to accelerate the tired particles of the boundary layer with reduced wall friction. This study aims to better understand and optimize the laminar boundary layer control parameters, angle, speed, and control range. The results obtained by numerical simulation allowed a gain of more than 10%.
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