Wind Tunnel Test on an Airplane Model with Cylindrical VGs attached on the Wing’s Upper Surface

Abstract

In aerodynamics, there is a lot of research regarding the implementation of vortex generators (VGs) which are placed in certain parts of aircraft to improve aerodynamic performance. Most of the previous study was carried out computationally using CFD software, while the VGs placement part was an airfoil shape only. This research aims to determine the effect of placing cylindrical VGs on the upper surface of the right and left wings of an airplane aerodynamic model, referring to the chord percentage from the leading edge. Apart from that, the effect of placing VGs along 1/3 of the wing length at the base, middle, or tip of the wing of an airplane model was also studied. This experimental approach uses a subsonic wind tunnel and an external balance system to measure aerodynamic force/moment components occurring at various angles of attack. As a result, the installation of VGs does not have a good effect on the lift and drag coefficients. The best maximum lift drag coefficient ratio (CL/CD) is 11.338 which occurs at an angle of attack of 7° with VGs placement at 17% chord. For VGs placement towards the lateral wing, the best maximum CL/CD is 11.481 which occurs as VGs attached at the wing tip and the angle of attack is 7°.