Aerodynamic Performance Improvement with Morphing Winglet Design

Abstract

The aim of this study is to reduce unnecessary lift and minimize drag at the same time when the aircraft reaches a certain speed level by using the active morphing method during flight. In this study, the flight performance was improved by designing a morphing winglet. Aerodynamic analysis of the wing in flat level flight at speeds of 15, 20 and 25 m / s has been performed. Morphing winglet of the wing was analyzed separately at 0-20-45-60-75 degree toe angles at speeds of 10-15-20-25-30 m / s. Optimum parameters have been determined to achieve maximum lift and minimum drag.