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涵道本体对于提高飞行器整体拉力起着显著作用。单旋翼和共轴双旋翼高速旋转时在涵道唇口产生绕流,形成低压区,使涵道本体产生附加拉力。基于有限体积法,研究涵道唇口对单旋翼和共轴双旋翼的影响。分析表明,涵道唇口对单旋翼以及共轴双旋的气动特性产生强烈影响,单旋翼产生的拉力随着唇口半径的逐渐增大而增大。对于共轴双旋翼,唇口半径的变化在一定程度上改变上下旋翼拉力分配,使得上旋翼拉力逐渐增大,下旋翼拉力逐渐减小。当半径无限增大,涵道共轴双旋翼机构趋同于共轴双旋翼机构,计算结果也表明,其上下旋翼拉力分配关系与共轴双旋翼的相吻合。
The ducted body plays a significant role in improving the overall pulling force of the aircraft. Single-rotor and coaxial double-rotor high-speed rotation in the ducted lip flow around the formation of low-pressure zone, the tunnel body to produce additional pull. Based on the finite volume method, the influence of the lip of the tunnel on the single rotor and the coaxial double rotor is studied. The analysis shows that the lip of ducts strongly influences the aerodynamic characteristics of single rotor and co-rotating double helix. The pulling force of single rotor increases with the increase of lip radius. For the coaxial double rotor, the variation of lip radius changes the tension distribution of the upper and lower rotor wings to some extent, so that the pulling force of the upper rotor increases gradually and the pulling force of the lower rotor decreases gradually. When the radius increases indefinitely, the tunnel coaxial double-rotor mechanism converges to the coaxial double-rotor mechanism. The calculation results also show that the tension distribution relationship of the upper and lower rotor wings is coincident with that of the coaxial double rotor.