An experimental study was conducted to investigate the effect of trailing vortices on a strake-wing-body configuration. This configuration was placed trailing a large rectangular leading wing of NACA 0015 airfoil section. The angle of attack of the leading wing was varied to obtain variable induced trailing vortices. The lift, drag and side forces in addition to the yawing, pitching and rolling moments were measured for the trailing configuration at different values of incidence and bank angles. Analysis of the experimental results shows a drop in lift, a slight influence on drag, and practically no effect on the longitudinal stability. In order to maintain the same lift, the results demonstrated that it is imperative to increase the angle of attack which consequently increases the drag and adds a smaller nose-down pitching moment. A negative rolling moment is produced for this symmetric tailless configuration for zero bank angle. During banking flight a small positive yawing moment and a negative side force are produced.