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摘要:
分布式电推进飞机大量采用螺旋桨，存在显著的桨-翼气动耦合效应。通过改变轴向诱导速度分布控制螺旋桨滑流，从而得到螺旋桨弦长和扭转角分布，提出一种考虑滑流效应的高效螺旋桨设计方法，并验证方法的可行性。计算所设计螺旋桨在孤立和分布式构型的巡航和悬停气动特性，并和最小诱导损失方法进行对比。结果表明：巡航升力系数相同时，所设计螺旋桨效率比最小诱导损失法高3.4%～6.6%；不同转速时，单独螺旋桨悬停效率比最小诱导损失法高10.4%～13.5%；分布式构型，设计螺旋桨悬停效率为比最小诱导损失法高13%。设计螺旋桨在巡航和悬停状态都能满足其设计要求，且都保持较高的效率运行。
Abstract:Propellers are widely used in distributed electric propulsion aircraft, where a significant propeller-wing aerodynamic coupling effect exists. By changing the axial induced velocity distribution to control the propeller slipstream, the propeller chord length and torsion angle distributions were obtained. An efficient propeller design method considering the slipstream effect was proposed, and the feasibility of the method was verified. The cruise and hover aerodynamic characteristics of the designed propellers in isolated and distributed configurations were calculated and compared with the minimum induced loss method. The results show that, for the same cruising lift coefficient, the efficiency of the designed propeller is 3.4%–6.6% higher than that of the minimum induced loss method. The hovering efficiency of a single propeller is 10.4%–13.5% higher than that of the minimum induced loss method at different rotational speeds. In the distributed configuration, the designed propeller’s hover efficiency is 13% higher than that of the minimum induced loss method. The designed propeller meets its design requirements in both cruise and hover states, maintaining high-efficiency operation.
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图 3 滑流管模型涡系在任意点P的诱导速度
Figure 3. Induced velocity of slipstream tube model vortex system at any point P
图 6 不同螺旋桨弦长和扭转角分布
Figure 6. Distribution of different propeller chord lengths and twist angles
图 8 螺旋桨滑流轴向速度不同值对比
Figure 8. Comparison of axial induced velocity in propeller slipstream
图 9 机翼、螺旋桨/机翼构型计算模型和坐标系定义
Figure 9. Wing, propeller/wing configuration calculation model and coordinate system definition
图 10 3种构型气动系数-攻角曲线
Figure 10. Aerodynamic coefficient-angle of attack curves for three configurations
图 11 不同设计方法设计的螺旋桨在不同攻角下的气动性能对比
Figure 11. Comparison of aerodynamic performance of propellers designed by different methods at different angles of attack
图 12 2°攻角机翼上表面压力系数分布对比及近壁面流线分布
Figure 12. Comparison of pressure coefficient distribution on the upper surface of wing at 2° angle of attack and streamline distribution near wall
图 14 悬停状态的计算模型及坐标系定义
Figure 14. Calculation model of hover state and definition of coordinate system
图 16 悬停构型x=0.2 m截面速度分布和表面流线分布
Figure 16. Velocity and surface streamline distribution for hovering configuration at x=0.2 m section
表 1 不同螺旋桨巡航状态下的性能参数对比
Table 1. Comparison of performance parameters of different propellers in cruise state
螺旋桨类型 拉力T/N 力矩Q/(N·m) 效率η/% CST螺旋桨 796 207 73.13 MIL螺旋桨 841 224 71.67 
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表 2 分布式构型计算模型参数和计算条件
Table 2. Distributed configuration calculation model parameters and conditions
参数 数值 机翼展长/m 10 机翼弦长/m 1 螺旋桨半径R/m 0.48 螺旋桨轮毂半径Rhub/m 0.096 螺旋桨位置坐标 (0, ±5, 0.333)(0, ±3.74, 0.178)(0, ±2.48, 0.178) 巡航速度V0/(m·s−1) 60 巡航高度/m 500 机翼攻角αw/(°) 0、2、4、6 螺旋桨转速/(r·min−1) 3 000 马赫数Ma 0.176 雷诺数Re/106 7
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表 3 3种构型升阻特性对比
Table 3. Comparison of lift and drag characteristics of three configurations
攻角
αw/(°)Cl Cd Cl/Cd 构1 构2 构3 构1 构2 构3 构1 构2 构3 0 0.69 0.028 24.80 0.83 0.032 26.33 0.83 0.031 26.53 2 0.85 0.044 20.91 1.01 0.046 21.84 1.00 0.045 22.38 4 1.01 0.057 17.71 1.18 0.064 18.52 1.17 0.062 18.79 6 1.17 0.075 15.63 1.34 0.086 15.57 1.33 0.084 15.79
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表 4 螺旋桨悬停状态的气动性能参数
Table 4. Aerodynamic performance parameters of propeller in hover state
转速/(r·min−1) 拉力/N 悬停效率/% CST MIL CST MIL 2 000 242 114 68.48 56.85 2 500 383 180 68.62 58.23 3 000 556 262 68.71 57.18 3 500 765 356 68.68 56.02 4 000 1 010 469 68.64 55.10
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表 5 分布式构型悬停状态计算模型参数和计算条件
Table 5. Calculation model parameters and conditions for distributed configuration in hover state
参数 数值 螺旋桨坐标 (−0.045, ±5, 0.696)(−0.2, ±3.74, 0.696)(−0.2, ±2.48, 0.696) 速度V1(m·s−1) 0 转速/(r·min−1) 4 000 雷诺数Re/106 2
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表 6 螺旋桨悬停状态的气动性能参数
Table 6. Aerodynamic performance parameters of configuration 4 propeller in hover state
类型 拉力/N 悬停效率/% CST MIL CST MIL Prop1 978 479 61.13 48.35 Prop2 970 472 60.40 47.30 Prop3 978 480 61.10 48.51 Prop4 979 480 61.04 48.51 Prop5 969 466 60.53 46.40 Prop6 976 479 61.10 48.35
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