<p>The paper presents the results of a study on the influence of a fuselage and controls displacement on the separated flow types. These flow types are generated in a flow past a swept-shaped leading edge of a wing; the experiments are conducted for a subsonic stream in a wind tunnel. This paper is a continuation of an experimental series on separated flows and control of aircraft wing at low Reynolds numbers. The well-instrumented methods for flow visualization and hot-wire anemometry were applied for gaining the experimental data. This provides a comprehensive understanding of the generated separated flows on the windward side of a wing at different attack angles and different aircraft control operations. The issue of control over a separated flow has been studied. The global flow separation can be eliminated through a local impact in selected points.</p>