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Drag Enhancement Techniques on Airfoil during Landing using Computational Fluid Dynamics

AJIN BRANESH*,AJAY KHATRI, MD FAYEZ SK, PRANJUL AGARWAL

This research aims to increase the drag on the airfoil during landing by optimizing the shape of a NACA 2412 airfoil for 80, 90, 100 m/s velocity for commercial aircraft. In this work, we deployed inward and outward rotating spherical section on the top of the airfoil section, and for the next case, dimples are placed throughout the top surface of the airfoil which will disturb the incoming airflow subsequently increase the drag during landing. As a substitute for the aircraft spoiler, this will reduce the additional structural weight. During the landing phase pilot flourish the drag by deploying spoilers. These spoilers disturbed the streamline flow over the wing and formed vortices at the wing-tip which help the aircraft to descend. Spoilers create additional drag to slow down the aircraft but it creates an induced loss of lift. As a result, stalling speed rise and cause strenuous landing. This work is done by importing airfoil coordinates into Ansys Workbench and simulating the NACA 2412 in ANSYS FLUENT using the k-epsilon turbulence model. Numerical analysis was performed for calibrating the coefficient of drag and lift along with the total drag force created. These can be highlighted by providing pressure, velocity, and Mach number contours for various Mach numbers.