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Identification of freeplay and aerodynamic nonlinearities in a 2D aerofoil system with via higher-order spectra

Part of: APISAT 2015

Published online by Cambridge University Press:  04 October 2017

M. Candon ,
R. Carrese ,
H. Ogawa  and
P. Marzocca
M. Candon*
Affiliation:
RMIT University, School of Engineering (Aerospace and Aviation), Melbourne, Australia
R. Carrese
Affiliation:
RMIT University, School of Engineering (Aerospace and Aviation), Melbourne, Australia
H. Ogawa
Affiliation:
RMIT University, School of Engineering (Aerospace and Aviation), Melbourne, Australia
P. Marzocca
Affiliation:
RMIT University, School of Engineering (Aerospace and Aviation), Melbourne, Australia
*
s3329364@student.rmit.edu.au
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Abstract

Higher-Order Spectra (HOS) are used to characterise the nonlinear aeroelastic behaviour of a plunging and pitching 2-degree-of-freedom aerofoil system by diagnosing structural and/or aerodynamic nonlinearities via the nonlinear spectral content of the computed displacement signals. The nonlinear aeroelastic predictions are obtained from high-fidelity viscous fluid-structure interaction simulations. The power spectral, bi-spectral and tri-spectral densities are used to provide insight into the functional form of both freeplay and inviscid/viscous aerodynamic nonlinearities with the system displaying both low- and high-amplitude Limit Cycle Oscillation (LCO). It is shown that in the absence of aerodynamic nonlinearity (low-amplitude LCO) the system is characterised by cubic phase coupling only. Furthermore, when the amplitude of the oscillations becomes large, aerodynamic nonlinearities become prevalent and are characterised by quadratic phase coupling. Physical insights into the nonlinearities are provided in the form of phase-plane diagrams, pressure coefficient distributions and Mach number flowfield contours.

Keywords

Aeroelasticity; CFDnonlinear aeroelasticitylimit cycle oscillationhigher-order spectrabispectrumfluid-structure interactionfreeplay
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1244 , October 2017 , pp. 1530 - 1560
Copyright
Copyright © Royal Aeronautical Society 2017 

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