Abstract
The paper presents the results of experimental studies of the influence of incoming external disturbances on the flow of straight wing and UAV models at different angles of attack and slip. Using the method of hot-wire anemometry, quantitative data were obtained on the structure of the flow near the surface of the model when it flows around a free stream and in the presence of incident external disturbances. Pictures of the visualization of the flow around models under stall conditionswere obtained. It was found that incident external disturbances under certain conditions can significantly change the flow structure.
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