Modeling of the aeroelasticity of a straight wing for a light aircraft by the finite element method was carried out and the simulation results were verified by a binary model. The possibility of using the finite element method for modeling the aeroelasticity of a light-class aircraft is shown. A comparison of the aeroelasticity of a light aircraft wing with and without tapering was performed. The criterion for loss of wing stability during aeroelastic oscillations is the transition from a positive to a negative value of the damping coefficient in the wing-air system at a certain flight speed. Measures to strengthen the wing structure in order to ensure the necessary flight speed are indicated.
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Fedorenko et al. (2024) studied this question.
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