Rudy Soenoko, Muhammad Iyos Yossie Nur Osria, Endi Sutikno
Winglet is a small wing or additional wing that attached on the main wing tip which is designed in curved or angled up form which would serves to prevent the flow from the bottom of the wing which has a high pressure towards the top which has a low pressure. The air flow from the bottom is going to the wing upper part through the wing tip and will meet with the flow from the upper part wing and form a rotational air or turbulence. This air turbulence on the wing tip would affect the airfoil angle of attack and would result a smaller lift which is able to produce by the wings. In this study the points that would be examined are the winglet angle variations and the airfoil angle of attack by implementing a NACA 2415 airfoil 1, 2. with the aim to determine the airfoil lift coefficient performance and the airfoil drag with the winglet angle variations 15°, 30°, 45°, 60° and without winglets and also the angle of attack variations of 0°, 8°, 10°, 12°, 14°, 16°, 18° until a stall phenomenon. This research method is using the CFD simulation by producing plane wing geometry and tested in a certain air flow speed boundary. And the result of this study to get the highest lift performance is on the winglet angle of 30° and an angle attack of 14°. © 2015, Research India Publications.
Department of Mechanical Engineering Brawijaya University, Malang, Indonesia
