Reducing The Effects of Wakes on A Flapped-Wing

Abstract

This paper deals with the effects of wakes that are formed due to the separation of the laminar boundary layer on an infinite aspect ratio flapped-wing. The model tested was composed of a main element and an external flap made up of NACA 23012 airfoil. Furthermore, this paper proposes a modification in the two-element wing to counter the effects of wakes such as the reduction of lift and the disturbance caused by the wake vortex shedding. The modification is done by disintegrating an elliptical part from the flap surface and translating it perpendicular to the main element chord. The study is divided into two parts. The first part deals with the calculation and study of force coefficients produced, wake velocity deficit and wake widths for the actual and the modified model numerically with a k-? turbulence model at a chord Reynolds number of 1,050,000. The aim of the second part is to record the wake vortex shedding frequency with an SST k-? turbulence model at a chord Reynolds number of 100,000. The incorporated modification exhibited an increase of lift and reduction of the wake vortex shedding frequency relative to the baseline geometry as predicted by the Commercial Navier Stokes solver ANSYS Fluent. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.