This paper presents the study of free-play induced flutter and limit-cycle oscillation (LCO) with high-fidelity numerical methods. An accurate FE model has been created for the all-movable horizontal tail. The structural characteristics of the model was tested and published in the prior paper, WADC-TR-54-53 (AD 39949). The time accurate aeroelastic solvers are used to study the flutter and nonlinear limit cycle oscillations (LCO) induced by a free play gap in the actuating mechanism at the root of the tail. The aeroelastic solver includes state-of-the-art CFD schemes that are formally higher-order time-accurate on moving grids, radial based function(RBF) algorithm is used for exchanging aerodynamic loading and structural deformation data at the fluid-structure interface. The computed flutter speed and flutter frequency are compared with the experimental data and good quantitative agreement between two data sets is achieved.
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