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摘要:
倾转旋翼机由于需要兼顾垂直起降和高速平飞2种典型工况下的动力需求，采用大直径旋翼作为推进装置会使机翼大部分处于旋翼滑流区内，这与常规螺旋桨飞机存在较大差异。为评估不同数值计算方法并研究旋翼滑流对倾转旋翼机气动特性的影响，针对选取两叶旋翼的某倾转旋翼机方案，利用激励盘模型、多参考系（MRF）模型、滑移网格模型分别进行了巡航状态下旋翼滑流对全机气动特性影响的数值模拟研究。结果表明：相对于无滑流状态，滑流定常影响使全机阻力增大，最大升阻比降低了7.5%，尾翼产生的升力增大，纵向静稳定度增加了17.1%，全机低头力矩增大；当迎角较小时，滑流虽然改变了机翼表面的升力分布，但是全机升力变化不大；滑流非定常影响会使全机气动特性产生周期性波动，升力系数波动幅度为9.0%，阻力系数波动幅度为10.8%，并且随着迎角的增大，波动幅度也越大。
Abstract:The tiltrotor aircraft needs to take into account the power requirements of vertical takeoff and landing and high-speed level flight, and using large diameter rotor as the propulsion device will make most of the wing in the rotor slipstream area, which is different from the conventional propeller aircraft. In order to evaluate different numerical methods and study the effect of rotor slipstream on the aerodynamic characteristics of a tiltrotor aircraft with two-blade rotor in cruise mode, the actuator disk model, the Multiple Reference Frame (MRF) model and the sliding mesh model are used respectively for numerical simulation study. The results show that, compared with no slipstream, the steady effect of slipstream increases the drag of the whole aircraft, and the maximum lift-drag ratio decreases by 7.5%. The lift generated by the tail wing is increased. The longitudinal static stability is increased by 17.1% and the pitch down moment of the whole aircraft is increased. When the angle of attack is small, although the slipstream changes the lift distribution on the wing surface, the lift of the whole aircraft does not change much. The unsteady influence of the slipstream causes periodic fluctuation of the aerodynamic characteristics of the aircraft. The fluctuation range of lift coefficient and drag coefficient are 9.0% and 10.8% respectively. With the increase of the angle of attack, the fluctuation range also increases.
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图 3 激励盘模型动压计算值与试验值对比
Figure 3. Comparison of dynamic pressure between calculation values and test values of actuator disk model
图 6 MRF模型计算值与试验值对比
Figure 6. Comparison between calculation values and test values of MRF model
图 10 有/无滑流全机气动特性对比
Figure 10. Comparison of aerodynamic characteristics of aircraft with and without slipstream
图 11 有/无滑流各部件气动特性对比
Figure 11. Comparison of aerodynamic characteristics of components with and without slipstream
图 12 有/无滑流压力系数云图对比
Figure 12. Comparison of pressure coefficient contour with and without slipstream
图 13 有/无滑流机翼截面压力系数分布对比
Figure 13. Comparison of pressure coefficient distribution of wing section with and without slipstream
图 14 有/无滑流速度云图对比
Figure 14. Comparison of velocity contour with and without slipstream
图 17 有/无滑流速度云图与流线对比(α=6°, Y=0.48 m)
Figure 17. Comparison of velocity contour and streamline with and without slipstream (α=6°, Y=0.48 m)
图 18 有/无滑流V尾截面压力系数分布对比(α=6°, Y=0.48 m)
Figure 18. Comparison of pressure coefficient distribution of V-tail section with and without slipstream (α=6°, Y=0.48 m)
图 19 全机气动特性随时间变化情况(α=0°)
Figure 19. Variation of aerodynamic characteristics of aircraft with time (α=0°)
图 20 激励盘与MRF模型计算的压力系数云图对比(α=0°)
Figure 20. Comparison of pressure coefficient contour calculated by actuator disk and MRF models (α=0°)
图 21 激励盘与MRF模型压力系数云图及流线对比(α=6°, Z=0.16 m)
Figure 21. Comparison of pressure coefficient contour and streamline between actuator disk and MRF models (α=6°, Z=0.16 m)
图 22 激励盘模型X=1 m截面当地迎角增量变化
Figure 22. Increment of local angle of attack of X=1 m section of actuator disk model
图 24 MRF模型4种旋翼相位角气动特性曲线
Figure 24. Aerodynamic characteristic curves of four rotor phase angles of MRF model
图 25 MRF模型与滑移网格模型计算结果对比(α=0°)
Figure 25. Comparison of results calculated by MRF and sliding mesh models (α=0°)
图 26 MRF模型与滑移网格计算的压力系数云图对比(α=0°)
Figure 26. Comparison of pressure coefficient contour calculated by MRF and sliding mesh models (α=0°)
参数 数值或翼型 旋翼半径/m 0.914 桨毂半径/m 0.229 旋翼翼型 NACA0012 旋翼弦长/m 0.1 旋翼桨距/(°) 11 旋翼片数 2 转速n/(r·min-1) 1 167 
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表 2 倾转旋翼机参数
Table 2. Parameters of tiltrotor aircraft
参数 数值 机翼翼展/m 3.5 机翼面积/m2 1.18 机翼安装角/(°) 3 巡航高度/km 4 平均气动弦长/m 0.33 飞行速度/(km·h-1) 150 旋翼转速n/(r·min-1) 1 500 旋翼直径/m 1.5
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表 3 不同迎角下Point 1与Point 2的动压监测值
Table 3. Dynamic pressure of Point 1 and Point 2 at different angles of attack
α/(°) qU1/Pa qP1/Pa Δ1/% qU2/Pa qP2/Pa Δ2/% 0 674.6 689.6 2.22 699.8 739.5 5.67 3 620.4 650.6 4.87 700.9 762.4 8.77 6 562.8 600.9 6.77 702.8 789.8 12.38 9 580.6 630.6 8.61 705.4 817 15.82
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表 4 三种数值方法评估
Table 4. Evaluation of three numerical methods
方法 旋翼模型 网格量 计算时间 精度 适用范围 激励盘 虚拟 少 短 低 定常 MRF 真实 多 中 中 定常 滑移网格 真实 多 长 高 非定常
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