关键词: 混合涡粒子方法, 气动干扰, 倾转旋翼机, 过渡模式, 性能分析

Abstract: Aiming to elucidate the complex aerodynamic interactions between rotor and wing during hovering, forward flight, and transition modes of tiltrotor aircraft, an enhanced hybrid panel-vortex particle method is developed. This method lever-ages Neumann boundary conditions and Hess equivalence principle for efficient computational analysis. By incorpo-rating a novel single panel-multi vortex particle conversion and adaptive vortex particle quantity control, computational efficiency is significantly improved without compromising accuracy. Validation against wind tunnel data demonstrates the method's precision and efficiency compared to traditional viscoelastic vortex particle methods. Subsequent numer-ical simulations and flow field analysis of the rotor/wing model unveil intricate aerodynamic interactions. In hovering mode, while the wing's blocked downwash slightly enhances rotor lift, the dominant negative lift due to significant wing download adversely impacts overall load-carrying capacity. Increasing collective pitch mitigates this lift loss. During transition, the rotor wake initially induces substantial lift loss on the wing, followed by a notable increase and negligible influence in later phases. Conversely, the wing's impact on rotor performance remains minimal. In forward flight, the rotor marginally augments wing lift and drag, albeit with a reduced lift-to-drag ratio. These findings provide valuable insights into the aerodynamic complexities of tiltrotor aircraft, contributing to the development of aeroelastic stability analysis, advanced flight control systems and performance optimization.

Key words: hybrid panel-vortex particle method, aerodynamic interactions, tiltrotor aircraft, transition mode, performance analysis