Numerical Study of the Effect of Spoiler Configuration on Wake Vortex Alleviation

Abstract

A numerical investigation was undertaken to evaluate the capabilities of a differential spoiler setting (DSS) in modifying the spanwise wing load and reducing the hazard of wake vortices imposed on a following aircraft. Numerical simulations were carried out on a scaled, half-model aircraft under a high lift configuration (HLC) condition for two outboard loading cases and two inboard loading cases in addition to the baseline configuration case. The study has covered the near-wake field and the extended near-wake field regions. The results are presented in terms of velocity contours, vorticity contours, tangential velocity, circulation, and streamlines at several measurement sections downstream, namely, at