Increasing L/D Ratio of Wing by Delaying Flow Separation for Better Aerodynamic Performance

To improve the aerodynamic efficiency of the aircraft, the article focuses on optimizing the L/D ratio through postponement of flow separation. Elevating the L/D ratio leads to diminished drag and delays stall occurrence at high angles of attack (α). The wing geometry adopts NACA ۶-digit airfoils, specifically NACA ۶۳۴۱۸ and NACA ۶۳۴۱۵. Various aerodynamic devices are explored for their ability to defer flow separation, with passive aerodynamic devices being the prevalent choice. The primary goal of the research is to integrate rotational thin wire elements into the aerodynamic components of the wing, aiming to diminish drag, amplify lift, and enhance overall aerodynamic performance. The analysis spans a range of α, from ۰o to ۲۰o. The study encompasses two scenarios: one without the incorporation of aerodynamic devices and the other with their implementation. Comparative analyses of increases in CL and reductions in CD, with notable improvements observed at a ۱۵o angle of attack, ۲۸.۴۷% increase in CL and ۱۵.۰۷% decrease in CD. Furthermore, the improved performance in the CL/CD, which increases substantially in stall conditions, thereby demonstrating the potential of these aerodynamic modifications to enhance overall aircraft performance.

کلیدواژه ها:

Boundary Layer ، Flow separation ، Drag force ، Lift force ، Circulation