Abstract
The stability of the wing is revisited in this work, the natural modes of the thin wing in incidence under the action of aerodynamic forces are calculated. The wing in this study has two degrees of freedom corresponding to the bending and torsion. Boundary between stable and instable zone are calculated. Wing stabilization by piezoelectric material are considered. The noise level produced by unsteady impinging gust is predicted.
Highlights
The airfoils and plades are involved in many applications nowadays, wind turbine, commercial air planes, turbines, compressor, fans, rotors and propellers are not the unique examples
The flow around an airfoil and blade depends on the geometrical configuration of the airfoil and the nature of the flow in far field
For a stable wing of small angle of attack the flow is attached to the wing and the oscillation of the lift and the vibration of the wing are mainly imposed by turbulence density of far field free stream
Summary
The airfoils and plades are involved in many applications nowadays, wind turbine, commercial air planes, turbines, compressor, fans, rotors and propellers are not the unique examples. Airfoil stall can be either promoted or inhibited depending on the momentum of jet's slot and a corresponding reduction or increase in the lift is obtained [5, 6] This technique is in great interest in wind turbine in order to achieve constant energy supply. The equation of critical curves defining boundary of stable and unstable zones in the control parameters planes are selected configuration here. The solution of the system of partial differential equations is sought in the form of a normal mode, i.e
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