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

Ramesh, L. P.; Mugendiran, V.; Sivaraj, G.

doi:10.47176/jafm.17.12.2611

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

Document Type : Regular Article

Authors

¹ Department of Mechanical Engineering, SRM Valliammai Engineering College, Kanchipuram, Tamilnadu, 603203, India

² Department of Production Technology, Anna University (MIT) Campus, Chennai, Tamilnadu, 600044, India

³ Subsonic Airflow Testing Facility, Research Park, Bannari Amman Institute of Technology, Erode, Tamilnadu, 638401, India

10.47176/jafm.17.12.2611

Abstract

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 6-digit airfoils, specifically NACA 63418 and NACA 63415. 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 0^o to 20^o. The study encompasses two scenarios: one without the incorporation of aerodynamic devices and the other with their implementation. Comparative analyses of increases in C_L and reductions in C_D, with notable improvements observed at a 15^o angle of attack, 28.47% increase in C_L and 15.07% decrease in C_D. Furthermore, the improved performance in the C_L/C_D, which increases substantially in stall conditions, thereby demonstrating the potential of these aerodynamic modifications to enhance overall aircraft performance.

Keywords

Main Subjects

Boundary Layers

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