The aircraft wing is designed in such a way, that it allows the aircraft to fly in all flight phases at different conditions. The wing is optimal at only one flight condition. Due to the changing flight conditions, the aircraft rarely flies at the most optimal point. One solution to this is morphing wing, which improves aircraft by altering wings geometry to accommodate changing flight conditions. During bachelor thesis, we created a conceptual design of a morphing wing, with variable camber. Aerodynamic properties of the morphing wing were measured in a wind tunnel at different morphed airfoil geometries, Reynolds numbers and angle of attacks. Comparison of data between baseline airfoil and all airfoils showed an increase of max. lift coefficient from 1,09 to 1,52 and lift to drag ratio from 5,76 to 6,9.
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