The influence of the lift-share ratio between a rotor and a wing on the aerodynamic performance of a winged compound helicopter in high advance ratio flight is investigated through numerical simulations in this paper. A simplified model constructed with only a rotor and a winged body is considered to focus on the aerodynamic interactions between the rotor and the wing. The effect of the interaction is evaluated through comparison to the isolated rotor and the isolated wing in the same flight condition. A cruising flight condition at which the rotor advance ratio is about 0.7 is considered where the rotor rotational speed is reduced to 75% revolutions per minute. The lift-share ratio between the rotor and the wing is changed by adjusting the wing incidence angle and the wing area. Numerical simulation results show that the aerodynamic performances against the lift-share ratio follow similar trends regardless of the wing incidence change or the wing area change. The lift-to-drag ratios of the rotor and the winged body both degrade due to the aerodynamic interaction between the rotor and the winged body as compared with the isolated configurations. The optimal lift-share ratio of the rotor is about 6–7% of the total lift. When the lift share of the rotor is larger than the optimal value, the overall performance is drastically reduced by the rotor/wing aerodynamic interaction.

通过数值模拟，研究了机翼与机翼的升力分配比对机翼复合直升机在高空速比飞行中空气动力性能的影响。考虑仅由转子和机翼主体构成的简化模型将重点放在转子和机翼之间的空气动力学相互作用上。通过与在相同飞行条件下的隔离式旋翼和隔离式机翼进行比较，可以评估相互作用的影响。考虑了转子前进比为约0.7的巡航飞行状态，其中转子转速降低到每分钟75％转数。通过调节机翼的入射角和机翼面积，可以改变转子与机翼之间的升力分配比。数值模拟结果表明，无论升程变化或机翼面积变化如何，针对升力比的空气动力性能都遵循相似的趋势。与隔离构型相比，由于转子和翼体之间的空气动力学相互作用，转子和翼体的升阻比均降低。转子的最佳升力分配比约为总升力的6–7％。当转子的升力份额大于最佳值时，转子/机翼的空气动力相互作用会大大降低整体性能。与隔离构型相比，由于转子和翼体之间的空气动力学相互作用，转子和翼体的升力/阻力比均降低。转子的最佳升力分配比约为总升力的6–7％。当转子的升力份额大于最佳值时，转子/机翼的空气动力相互作用会大大降低整体性能。与隔离构型相比，由于转子和翼体之间的空气动力学相互作用，转子和翼体的升力/阻力比均降低。转子的最佳升力分配比约为总升力的6–7％。当转子的升力份额大于最佳值时，转子/机翼的空气动力相互作用会大大降低整体性能。