Control of Flow Past a Model Aircraft in the Landing Configuration Using Aerodynamic Strakes

Abstract

The results of numerical investigation of a simplified model of the civil aircraft layout in the landing regime are presented. Numerical simulation is performed within the framework of the Reynolds equations. The aerodynamic characteristics of the model are studied in the case in which the flow is controlled by means of mounting strakes (vortex generators) on the nacelle and the fuselage. It is shown that mounting simultaneously the two strakes leads to a considerable increase in the maximum lift of the layout, while in the case in which only one fence is mounted on either the nacelle or the fuselage it increases only slightly.