Abstract
In the last decade folding tube launch of UAV became common, for which telescopic wings are reasonable. Nowadays, telescopic wing aerodynamic characteristics are researched much less than constant geometry wing. In present work telescopic wings` aerodynamic characteristics were determined by means of Finite elements (Ansys software) and Panel-vortex methods, as well as results obtained during wind tunnel experiment.Finite element method with unstructured mesh allows to consider vortices on joints between telescopic wing`s sections and as a result to get more accurate values for lift coefficient. Both Panel-vortex and Finite element method allow estimating the decrease of drag due to the telescopic wing span growth. However, the Panel-vortex method is more accurate in prediction the dependence of drag changing versus lift coefficient (if lift increases then drag changing increases as well).
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