Abstract
The paper briefly describes the main features of the used mathematical model of aerodynamic forces in transonic flow. The model is based on the Euler equations in various approximations, the boundary layer theory and viscous-inviscid interaction. Structural elastic deformations are described by equations in modal coordinates. The algorithm for computation of dynamic aeroelasticity characteristics in transonic flow has been developed on the base of energy method.The problem of transonic self-oscillations and their relationship with the pressure distribution peculiarities and shock waves motion is numerically investigated using the CAST wing section as example. The dependence of aeroelastic stability characteristics on the distributed work of aerodynamic forces along the wing chord is shown. An approach to the creation of a numerical modeling methodology is developed for LCO processes in the time domain.
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