Yatay Kuyruklarda Kıvrık Kanat Ucu Kullanımının Aerodinamik Etkileri

Abstract

In this study, aerodynamic forces on a horizontal stabilizer of commercial aircraft that has NACA 0012 airfoil and new horizontal stabilizers that are designed by mounting two different curved wingtip devices (winglet) to the preliminary horizontal stabilizer at different angle of attack values. The preliminary horizontal stabilizer is designed by the airfoil shape that is composed of 200 points and determined span, root chord, dihedral angle, sweep angle and taper ratio values. This design is defined as C 1 . Two curved wingtip devices that have the same sweep angle, cant angle, taper ratio, span and height but different airfoil thickness ratio at tip are designed and mounted to the C 1 . These are named as C 2 and C 3 , respectively. The aerodynamic analyses of these designs are done by using Fluent that is a well-known computational fluid dynamics program. The analyses are performed at 13 different angle of attack values and the alterations on drag (C D ) and lift (C L ) coefficients of the designed horizontal tails are observed. According to the results, C 2 has higher lift to drag ratio (C L /C D ) values at all angle of attack values. For the C 3 design, the same result has been seen except for the result of -1 degree angle of attack.