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Fast prediction of transonic aeroelasticity using computational fluid dynamics

Woodgate, Mark A. (2008) Fast prediction of transonic aeroelasticity using computational fluid dynamics. PhD thesis, University of Glasgow.

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Abstract

The exploitation of computational fluid dynamics for non linear aeroelastic simulations is mainly based on time domain simulations of the Euler and Navier-Stokes equations coupled with structural models. Current industrial practice relies heavily on linear methods which can lead to conservative design and flight envelope restrictions. The significant aeroelastic effects caused by nonlinear aerodynamics include the transonic flutter dip and limit cycle oscillations. An intensive research effort is underway to account for aerodynamic nonlinearity at a practical computational cost.To achieve this a large reduction in the numbers of degrees of freedoms is required and leads to the construction of reduced order models which provide compared with CFD simulations an accurate description of the dynamical system at much lower cost. In this thesis we consider limit cycle oscillations as local bifurcations of equilibria which are associated with degenerate behaviour of a system of linearised aeroelastic equations. This extra information can be used to formulate a method for the augmented solve of the onset point of instability - the flutter point. This method contains all the fidelity of the original aeroelastic equations at much lower cost as the stability calculation has been reduced from multiple unsteady computations to a single steady state one. Once the flutter point has been found, the centre manifold theory is used to reduce the full order system to two degrees of freedom. The thesis describes three methods for finding stability boundaries, the calculation of a reduced order models for damping and for limit cycle oscillations predictions. Results are shown for aerofoils, and the AGARD, Goland, and a supercritical transport wing. It is shown that the methods presented allow results comparable to the full order system predictions to be obtained with CPU time reductions of between one and three orders of magnitude.

Item Type: Thesis (PhD)
Qualification Level: Doctoral
Keywords: aeroelastic, computational fluid dynamics, reduced order modeling
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics
Colleges/Schools: College of Science and Engineering > School of Engineering > Aerospace Sciences
Supervisor's Name: Badcock, Prof. Ken B.
Date of Award: 2008
Depositing User: Mr Mark A Woodgate
Unique ID: glathesis:2008-923
Copyright: Copyright of this thesis is held by the author.
Date Deposited: 16 Jul 2009
Last Modified: 10 Dec 2012 13:28
URI: http://theses.gla.ac.uk/id/eprint/923

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