Recent Papers

This study investigates the pressure distribution over a symmetrical airfoil, specifically the NACA 66(2)-015, at varying angles of attack. The analysis aims to enhance the understanding of aerodynamic performance characteristics and flow behavior around the airfoil, which is crucial for applications in aerospace engineering and design optimization. were employed to model the airflow around the airfoil at angles of attack ranging from -10 to 15. Results indicate a significant variation in pressure distribution with changes in angle of attack. At low angles, the flow remains attached, resulting in a relatively uniform pressure distribution along the upper and lower surfaces. As the angle of attack increases, a notable increase in suction on the upper surface is observed, leading to enhanced lift generation. However, at higher angles, flow separation occurs, causing a dramatic shift in pressure distribution and a decrease in lift efficiency. This study provides valuable insights into the aerodynamic characteristics of the NACA 66(2)-015 airfoil, highlighting the critical relationship between angle of attack and pressure distribution. The findings contribute to the broader field of aerodynamics by informing design strategies that optimize airfoil performance across various flight conditions. Further research is recommended to explore the impact of surface modifications and Reynolds number variations on pressure distribution and overall aerodynamic efficiency.

Copyright © 2025 VIYYAPU PRAVEEN. This is an open access article distributed under the Creative Commons Attribution License.