Print Email Facebook Twitter Aeroelastic Limit-Cycle Oscillations resulting from Aerodynamic Non-Linearities Title Aeroelastic Limit-Cycle Oscillations resulting from Aerodynamic Non-Linearities Author van Rooij, A.C.L.M. (TU Delft Aerodynamics) Contributor Bijl, H. (promotor) Dwight, R.P. (copromotor) Degree granting institution Delft University of Technology Date 2017-04-12 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. Subject AeroelasticityLimit-cycle oscillationsUnsteady aerodynamicsBifurcation behaviourStructural parameter variations To reference this document use: https://doi.org/10.4233/uuid:cc2f32f8-6c6f-4675-a47c-37b70ed4e30c ISBN 978-94-6186-794-0 Part of collection Institutional Repository Document type doctoral thesis Rights © 2017 A.C.L.M. van Rooij Files PDF final_version_dissertatio ... _Rooij.pdf 8.82 MB Close viewer /islandora/object/uuid:cc2f32f8-6c6f-4675-a47c-37b70ed4e30c/datastream/OBJ/view