Boundary Layer Control of Aerodynamic Flow Over Wing by Active Suction Method

The objective of the study is to enhance aerodynamic performance through investigating the application of active suction techniques for boundary layer control over aircraft wings. An enlarged wing model with integrated suction slots is designed and 3D printed. The suction action is replicated by a small vacuum pump, which delays airflow detachment and lessens boundary layer separation. Lift, drag, and pressure distribution are measured in a wind tunnel while the model is subjected to different suction intensities. Active boundary layer control can increase lift-to-drag ratios, decrease turbulence, and improve overall flight efficiency, as the project demonstrates.