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.
Published Version
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