Numerical analysis of tiltrotor/wing aerodynamic characteristics in continuous conversion mode
A numerical simulation framework was established,which was suitable for simulations of the continuous conversion mode of the tiltrotor based on the overset mesh method.The transition of a rotor/wing system from fixed-wing mode to helicopter mode was simulated for two important components in unmanned aerial vehicles,the rotor and the wing.Reynolds-averaged Navier-Stokes equations were used to analyze the variations of aerodynamic characteristics in different advance ratios and the effects of crosswind velocity on aerodynamic characteristics in conversion mode.Results show that the lift and drag coefficients of the wing decrease with the increase of the tilt angle,and the variation decreases with the increase of the advance ratio.The rotor thrust increases with the increase of the tilt angle,and the variation increases with the increase of the advance ratio.When there is crosswind in the incoming flow,the lift and drag coefficients of the wing decrease.The performance of the wing in low crosswind velocity is improved after the tilt angle reaches 65°.The magnitude of the thrust coefficient of the rotor is not significantly affected by crosswind,but the oscillation amplitude increases as a result.
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