Abstract
This paper studies an effective lag damping prediction method for a flexible flap - lag - torsional hingeless rotor model and correlation with the experimental data for a four-bladed rotor. The ONERA dynamic stall models of lift, drag, and pitching moment for each aerodynamic airfoil element and an advanced three-dimensional finite state wake model are used. The nonlinear equations of motion are represented in terms of state variables with 4 x 10 structural state variables. Eight aerodynamic elements for each rotor blade and at least eight wake harmonics are employed. The aerodynamic and wake state variables are 4 x 48 and 45, respectively. A numerical simulation technique is applied to determine the transient response of the hingeless rotor model and to predict the lag damping. Numerical investigations indicate that the present theoretical/numerical method improves the correlation of the theoretical and experimental results compared to an earlier eigenvalue, perturbation analysis.
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