An experimental high-aspect-ratio wing aeroelastic model with a slender body at the tip has been constructed, and the response due to flutter and limit-cycle oscillations (LCOs) has been measured in a wind-tunnel test. A theoretical model has been developed and calculations made to correlate with the experimental data. Structural equations of motion based on nonlinear beam theory are combined with the ONERA aerodynamic stall model to study the LCO hysteresis phenomenon of a high-aspect-ratio wing model. Time simulation and a harmonic balance approach are each used to compute the LCO hysteretic response.The results between the theory and experiment are in good agreement.
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Tang et al. (2002) studied this question.
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