Publicado 6 números por año
ISSN Imprimir: 1948-2590
ISSN En Línea: 1948-2604
MATHEMATICAL SIMULATION OF DYNAMIC EFFECTS OF UNSTEADY AERODYNAMICS DUE TO CANARD FLOW SEPARATION DELAY
SINOPSIS
Results of experimental investigation of unsteady aerodynamic characteristics for the model of a transonic airliner with canard surfaces and high-sweep wing during forced pitch oscillations with various amplitudes and frequencies are considered. Dynamic derivatives versus angle of attack at various oscillation frequencies are obtained using results of small-amplitude oscillations. For the canard configuration of the model a range of angles of attack was found where positive aerodynamic damping was observed. The positive damping value was varied with the frequency of oscillations. For large-amplitude pitch oscillations, nonlinear dynamic hysteresis loops of aerodynamic characteristics were investigated. The traditional linear approach to simulate the unsteady aerodynamic characteristics based on the aerodynamic derivatives concept fails to include the oscillation frequency influence on aerodynamic damping. The nonlinear hysteresis loops of the pitching moment coefficient obtained at large-amplitude oscillations cannot be described with the use of this approach. A new nonlinear state-space mathematical model of the pitch moment coefficient is proposed in the paper. This model is capable of describing all experimentally observed dynamic effects. In the proposed model an additional ordinary differential equation is introduced to simulate the dynamic effects of canard flow separation delay.
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