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Aeroelastic Limit-Cycle Oscillations resulting from Aerodynamic Non-Linearities

by Rooij ACLM van

Institution:	Delft University of Technology
Year:	2017
Posted:	02/01/2018
Record ID:	2154859
Full text PDF:	http://resolver.tudelft.nl/uuid:cc2f32f8-6c6f-4675-a47c-37b70ed4e30c;urn:NBN:nl:ui:24-uuid:cc2f32f8-6c6f-4675-a47c-37b70ed4e30c;cc2f32f8-6c6f-4675-a47c-37b70ed4e30c;urn:isbn:978-94-6186-794-0;10.4233/uuid:cc2f32f8-6c6f-4675-a47c-37b70ed4e30c

Abstract

Aerodynamic non-linearities, such as shock waves, boundary layer separation or boundary layer transition, may cause an amplitude limitation of the oscillations induced by the fluid flow around a structure. These aeroelastic limit-cycle oscillations (LCOs) resulting from aerodynamic non-linearities have been studied numerically in this PhD thesis. A frequency domain-based method called ADePK has been developed to study the bifurcation behaviour of the LCO solutions. From several extensive (structural) parameter studies, it was found that aerodynamic non-linearities, especially shock wave motions, can lead to limit-cycle oscillations that occur already below the linearly predicted flutter boundary.Advisors/Committee Members: Bijl, H., Dwight, R.P..