The vortex wake effect on the aerodynamic characteristics of a twin-engine general-aviation aircraft model has been studied in TsAGI's wind tunnel. The airfoil cascade with differentially deflectable sections along the span installed at the wind-tunnel nozzle exit was used to simulate the vortex wake impact. In addition to the landing configuration considered first, this work is devoted to the analysis of the vortex wake effect on the aerodynamic characteristics of the model in cruise and takeoff configurations. Preliminary researches were carried out on the efficiency of some wing control surfaces to compensate for the vortex induced rolling moment. The results of numerical calculation of the vortex wake impact on the aircraft model in cruise configuration is also presented. The algorithm for computing aircraft aerodynamic characteristics has been modified to account of the vertical velocity component of the vortex wake.