Please use this identifier to cite or link to this item: https://doi.org/10.2514/6.2014-1200
Title: Numerical study of effect of control surface on wing flutter in transonic flow
Authors: Lai, K.L. 
Zhang, X.Q.
Kim, T.
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
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