基于动态重叠网格方法的尾翼对螺旋桨滑流的影响

螺旋桨飞机产生的滑流会对其扫掠过的部件产生显著干扰，研究尾翼部件对滑流的影响有助于将滑流与尾翼的干扰进行解耦分解。采用动态重叠网格方法模拟螺旋桨定轴转动，通过求解三维非定常雷诺平均Navier-Stokes （URANS）方程，数值模拟了某螺旋桨飞机带尾翼构型的有/无滑流状态，通过试验结果对计算方法的正确性进行了验证。在此基础上，分别开展了有/无尾翼构型的滑流计算，结果表明：扣除尾翼气动力后，有/无尾翼的升阻力变化规律基本一致，俯仰力矩由于机身后体修形不同呈线性平移关系；对比有/无尾翼空间切面的速度分布云图、不同空间位置和拉力系数下的下洗角和侧洗角变化曲线，发现尾翼对滑流的影响仅局限在其周围，不同拉力系数下尾翼的干扰规律也基本类似。通过研究认为，在飞机初期设计和选型阶段，螺旋桨滑流与尾翼的相互干扰，可简化为滑流单向对尾翼产生影响，尾翼对滑流的影响可以忽略。

Influence of tail wing on propeller slipstream based on dynamic overlapping grid method

The slipstream produced by the propeller airplane will significantly interfere with the swept components. The study of the effect of the tail wing on the slipstream will help to decouple the slipstream and tail wing disturbances. The dynamic overlapping grid method is used to simulate the rotation of the propeller fixed axis. By solving the three-dimensional Unsteady Reynolds Average Navier-Stokes(URANS) equations, the state of a propeller airplane with tail wing with/without slipstream is simulated numerically. The correctness of the calculation method is verified by the experimental results. On this basis, calculations of the slipstream of the configuration with/without tail wing are carried out. The results show that the lift and drag aerodynamics variation law are almost the same after deducting of the aerodynamic force of the tail wing. The pitching moment is different due to the modification of the fuselage rear body. By comparing the slice velocity distribution clouds of the configurations with/without tail wing, variation curves of the down wash angle and the side wash angle at different spatial positions and with different thrust coefficients, it is found that the effect of the tail wing on the slipstream is only limited to the surroundings, and the rules of disturbance of the tail wing with different thrust coefficients are also very similar. Based on the study, it can be concluded that at the preliminary and selection stages of the airplane design, the mutual interference between the propeller slipstream and the tail wing can be simplified to be a one-way effect of the slipstream on the tail wing, and the effect of the tail wing on the slipstream can be ignored.