Model Reduction
A holy grail of CFD based Aeroelasticity is to have a method that allows systematic model reduction. No satisfactory method has so far been developed (ie a method that accounts for aeroelastic effects and can predict LCO's). A major achievement of our research is to develop such a method. The approach builds on the information calculated as part of the fast flutter method, and in particular the critical eigenvector that is calculated. The full order system is projected onto this eigenvector and a two degree of freedom system in the critical mode is obtained. Deriving this system is technical (2nd and 3rd Jacobians are required) but is beautifully effective. The resulting model is fully parameterised and can be used to calculate damped and LCO responses very cheaply.
Publications
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Woodgate, M.A. and Badcock, K.J., Aeroelastic Damping Model Derived from Discrete Euler Equations, AIAA Journal, 44(11), 2006, 2601-2611.
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Woodgate, M.A. and Badcock, K.J., Fast prediction of Transonic Aeroelastic Stability and Limit Cycles. AIAA Journal, 45(6),1370-1381,2007.
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Badcock, K.J., Woodgate, M.A. and Beran, P.S., Fast Prediction of Wing Rock Limit Cycle Oscillations Based on CFD, AIAA-2007-1071, 45th Aerospace Sciences Meeting and Exhibit, Reno, Nv, 8-11 January, 2007.