Abstract
Abstract The characteristics of rotor airfoil dynamic stall in high advance ratio were investigated based on the CFD (Computational Fluid Dynamics)method. The unsteady RANS(Reynolds-averaged Navier-Stokes) equation and overset mesh method were used in CFD calculation, and the variation of Mach and attack Angle were simulated by transitional and pitching motion of the airfoil. The airfoil dynamic lift coefficient, moment coefficient, and flow field of airfoils at different rotor blade positions were analyzed, and the influence of flight parameters and airfoil aerodynamic shape was investigated by comparison with baseline conditions. The results show that the dynamic stall of the rotor airfoil at the retreating blade in a high advance ratio is mainly caused by the extension of trailing edge separation; reducing rotor lift in a high advance ratio by a suitable flight strategy is an effect way to reduce dynamic stall; rotor airfoil leading edge droop can reduce dynamic moment, but will lead to dragging increase and drag divergence Mach decrease, the negative peak of the dynamic moment is reduced by about 60%, the drag coefficient is increased by about 0.01, and the drag divergence Mach is decreased by about 0.01 in present computation.
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