Analysis for Effect of Angle of Attack on Coefficient of Lift of Wing Structure

Abstract

<div class="section abstract"><div class="htmlview paragraph">Dimensional optimization has always been a time-consuming process, especially for aerodynamic bodies, requiring much tuning of dimensions and testing for each sample. Aerodynamic auxiliaries, especially wings, are design dependent on the primary model attached, as they influence the amount of lift or reduction in drag which is beneficial to the model. This study aims to reduce the time period taken to finalize the design parameter for the same. For a wing, the angle of attack is essential in creating proper splits to incoming winds, even under high velocities with larger distances from the separation point. In the case of a group of wings, each wing is then mentioned as a wing element, and each wing is strategically positioned behind the previous wing in terms of its vertical height and its self-angle of attack to create maximum lift. At the same time, its drag remains variable to its shape ultimately maximizing the C<i>_L</i>/C<i>_D</i> ratio. A high value of C<i>_L</i> indicates a significant component of horizontal drag is converted into a vertical lift. While the value of C<i>_D</i> remains variable to different design factors, adjusting the angle of attack can minimize the drag forces caused by reducing the frontal area of impact. In this study two winged elements were considered for the front wing. Three parameters with 5 levels each were used for the parametric optimization. Twenty-five sets of setup designs were considered as a part of the Taguchi optimization study. The <i>C_L/C_D</i> ratio of X₅ model obtained by CFD analysis is 15.78 and by experimental testing is 15.32. It is found that the <i>C_L /C_D</i> ratio obtained by Numerical analysis and Experimental investigation are well corroborated.</div></div>