Abstract
Flutter experiments were performed on a supercritical transport type wing to investigate the transonic dip in the flutter boundaries and to obtain data for verification of a calculation method for unsteady aerodynamic loads Complete transonic dips were measured at three wing angles of attack At the highest wing angle of at tack, a second dip was found Simultaneously, the mean pressure distribution was measured in one chordwise section which could explain the flutter characteristics. Using a flutter damper device, flutter onset could be measured accurately and rapidly This paper deals with the experimental test setup, describes the on line data reduction, and presents the results.
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