Aeroelastic Limit-Cycle Oscillations resulting from Aerodynamic Non-Linearities

Anouk van Rooij

Research output: ThesisDissertation (TU Delft)

35 Downloads (Pure)


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.
Original languageEnglish
QualificationDoctor of Philosophy
Awarding Institution
  • Delft University of Technology
  • Bijl, Hester, Supervisor
  • Dwight, R.P., Advisor
Thesis sponsors
Award date12 Apr 2017
Print ISBNs978-94-6186-794-0
Publication statusPublished - 2017


  • Aeroelasticity
  • Limit-cycle oscillations
  • Unsteady aerodynamics
  • Bifurcation behaviour
  • Structural parameter variations


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