Influence of Trailing Edge Tab on the Aerodynamic Characteristic of Blade Airfoil
The project of adding the trailing edge tabs to the blade was put forward to solve the problem of strong increase of the control high order load caused by the helicopter blade stall flutter.Taking the common helicopter blade airfoil as reference airfoil,aerodynamic characteristics were simulated by solving Navier-Stokes equations.Discrete scheme adopted second order upwind and turbulence model select Spalart-Allmaras model.Results were validated with wind tunnel test data.The effects of the bending angle on the lift coefficient,drag coefficient,pitching moment coefficient and lift-to-drag ratio were analyzed.Simulation results showed that by the increase of the bending angle of the trailing edge tab,lift coefficient and lift-to-drag ratio increased,zero lift angle of at-tack and stall angle of attack decreased.In the range of small angle of attack,the trailing edge had little effect on the drag coefficient of the airfoil.Increase of the trailing tab edge could move back the aerodynamic center and focus of airfoil,but increase the nose-down pitch moment.
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