Aeroelastic Limit-Cycle Oscillations resulting from Aerodynamic Non-Linearities

Doctoral thesis (2017)

Authors

A.C.L.M. van Rooij Aerodynamics - Aerospace Engineering
Research Group
Aerodynamics (Aerospace Engineering) (TU Delft)
Copyright: © 2017 A.C.L.M. van Rooij
DOI: https://doi.org/10.4233/uuid:cc2f32f8-6c6f-4675-a47c-37b70ed4e30c
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Published Date

2017

Language

English

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Aerodynamics

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.