Simulation and Computational Analysis of the Leading and Trailing Edges Modified NACA 0012 Airfoil
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Abstract
NACA 0012 symmetric airfoil is commonly used for the aerodynamic analysis of aircraft. This research work investigates modifications in the airfoil design to improve the lift-drag ratios. The initial phase involves computational analysis on the two-dimensional airfoil and later, the obtained results were validated by comparing them to standard data obtained by calculations. The modified airfoil designs are stepped trailing edge, tubercle leading edge and combination of both. The design alterations implemented was based on insights gained from various simulations with the adjustment in angle of attack ranging from 0° to 8°. The stepped design in trailing edge generated less drag and produced less lift. Whereas, the tubercle in leading edge of airfoil exhibited more drag and lift forces. Although generation of lift is favourable for an aircraft, it is of paramount importance to reduce its drag counterpart for efficient flying. Hence, the characteristics of tubercle leading edge and stepped trailing edge airfoil was incorporated into a single airfoil and their aerodynamic performance results were explained in this paper.
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