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|Title:||Numerical study of effect of control surface on wing flutter in transonic flow||Authors:||Lai, K.L.
|Issue Date:||2014||Citation:||Lai, K.L.,Zhang, X.Q.,Kim, T. (2014). Numerical study of effect of control surface on wing flutter in transonic flow. 55th AIAA/ASMe/ASCE/AHS/SC Structures, Structural Dynamics, and Materials Conference. ScholarBank@NUS Repository. https://doi.org/10.2514/6.2014-1200||Abstract:||A numerical study of the effects of trailing-edge flap on wing flutter in transonic flow has been conducted. The configuration considered consists of a base wing and a trailing-edge flap. The flap is attached to the wing through a hinge with torsional stiffness. The trailingedge flap deflections can be prescribed or calculated and are modeled as a degree of freedom so that the flap dynamic can be captured. The aeroelastic equations of motion of the fully fluid-structure coupled model are solved by using computational aeroelastic techniques.17 The computed time-domain aeroelastic responses are anaylsed with reduced-order modeling (ROM) techniques to give the flutter boundaries. Two types of ROM methodologies have been developed for predicting flutter boudnaries - one based on fluid-structure coupled model using the AAEMS tehnique,12 and another based on fluid-structure decoupled model using the Correlation Method for Hammerstein System Identification (CMHSI).14, 18 The wing-flap configuration considered in the paper is based on the AGARD 445.6 wing. The angle of flap deflection modeled is in the range between ±5°. The flutter boundaries predicted for the wing-flap configuration are compared to that of the baseline AGARD wing.||Source Title:||55th AIAA/ASMe/ASCE/AHS/SC Structures, Structural Dynamics, and Materials Conference||URI:||http://scholarbank.nus.edu.sg/handle/10635/116761||DOI:||10.2514/6.2014-1200|
|Appears in Collections:||Staff Publications|
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