Influence of propeller/wing system on aerodynamic performance at asymmetrical inflow
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摘要:
针对“螺旋桨/机翼”系统在复杂非对称入流情况下的非定常气动相互干扰问题，采用混合结构-非结构滑移网格方法，结合非定常雷诺平均Navier-Stokes方程，研究了偏航角及入流条件（包括攻角和来流风速）对螺旋桨/机翼相互气动干扰和滑流流场的影响，并与无滑流模型计算结果进行对比。结果显示：在三维非对称入流的影响下，偏航角从0°增加到20°时，机翼升、阻力系数分别降低了4.9%和10.64%，但是螺旋桨的拉力系数和推进效率则大幅提升了18.36%和7.26%，非对称入流机翼升力系数曲线变化幅度为对称入流的4倍。在攻角不变，改变偏航角时，螺旋桨滑流增加了机翼俯仰力矩稳定性裕量。但是随着攻角的变化，飞机纵向不稳定性逐渐增加，在桨后气流的影响下，两侧机翼上表面吸力峰均向左和向前移动，上下表面的吸力峰值均明显增大。在不同的风速下，有滑流影响的机翼升力特性相对无滑流影响的机翼增加量均在20%附近，且不断增大。
Abstract:In order to address the problem of the unsteady aerodynamic mutual interference of propeller/wing system in cases of complex asymmetrical inflow, the hybrid structured-unstructured sliding mesh method combined with the unsteady Reynolds-averaged Navier-Stokes equation was used. This approach assessed the influences of yawed angel and inflow conditions (e.g., angle of attack and freestream velocity) on mutual aerodynamic interference of the propeller/wing and the propeller slipstream, and compared with the calculation results of the no-slipstream model. The results revealed that under the influence of three-dimensional asymmetric inflow, the wing lift coefficient and drag coefficient fell by 4.9% and 10.64%, respectively, when the yawed angle increased from 0° to 20°. However, the thrust coefficient and propulsion efficiency of the propeller improved significantly by 18.36% and 7.26%. Additionally, the fluctuation range of the lift coefficient of the asymmetrical inflow was four times that of the symmetrical inflow condition. When the angle of attack remained constant and the yawed angle changed, the propeller slipstream enhanced the stability margin of the wing pitching moment. Unfortunately, with a fluctuating angle of attack, the longitudinal instability of the wing gradually increased. Meanwhile, under the influence of the airflow behind the propeller disk, the suction peaks on the upper surface of the wing on both sides of the nacelle moved leftward and forward, while the absolute values of the peak on both the upper and lower surfaces increased considerably. With varying wing speed, the increase in wing lift performance with slipstream was around 20%, compared with the wing without the influence of slipstream. Besides, the lift performance continued to increase with wind speed.
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图 3 计算模型表面网格划分和混合网格示意图
Figure 3. Surface grid of the computational model and the refined grid
图 5 一个旋转周期内“螺旋桨/机翼”系统气动特性变化
Figure 5. Aerodynamic performance of “propeller/wing” system during one revolution
图 8 不同偏航角下诱导因子沿径向分布曲线
Figure 8. Radial distribution of induced factors at different yaw angle
图 9 不同攻角下，有/无螺旋桨滑流时机翼升阻特性的对比
Figure 9. Comparison of wing aerodynamic coefficients with and without propeller slipstream at different angle of attack
图 10 展向切片空间站位示意图和不同攻角下压力系数分布对比
Figure 10. Sketch of slices location along the span direction and pressure coefficient distribution at different angle of attack
图 11 25 m/s风速、不同桨叶相位角时桨后滑流区切向和轴向风速云图
Figure 11. Contours of tangential and axial velocity distribution of propeller slipstream under freestream velocity of 25 m/s at different blade azimuth angles
表 1 单独螺旋桨网格无关性研究
Table 1. Grids-dependency study for the isolated rotating propeller
网格编号 ${T_{\rm{avg} } } $ $\Delta {T_{\rm{avg} } }$/% ${Q_{\rm{avg} } } $ $\Delta {Q_{\rm{avg} } }$/% ${L_{\rm{avg} } } $ $\Delta {L_{\rm{avg} } }$/% ${D_{\rm{avg} } } $ $\Delta {D_{\rm{avg} } }$/% Grid-1 28.33 3.85 2.47 5.56 52.42 0.87 7.47 9.69 Grid-2 29.42 0 2.34 0 51.97 0 6.81 0 Grid-3 29.42 0 2.32 0.85 51.93 0.08 6.48 4.85 Grid-4 27.41 0.03 2.32 0.85 51.92 0.10 6.40 6.02 
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表 2 “螺旋桨/机翼”系统时均气动特性随偏航角的变化
Table 2. Variation of time-averaged aerodynamic performance of propeller/wing system with yawed angle
工况 $C_{T_{\rm{avg}}} $ $C_{P_{\rm{avg}}} $ η/% $C_{L_{\rm{avg}}} $ $C_{D_{\rm{avg}}} $ ASYM-3-0 0.1291 0.1598 72.72 0.2508 0.0423 ASYM-3-5 0.1307 0.1611 73.05 0.2527 0.0422 ASYM-3-10 0.1354 0.1644 74.10 0.2517 0.0416 ASYM-3-15 0.1429 0.1697 75.78 0.2470 0.0402 ASYM-3-20 0.1528 0.1763 78.00 0.2385 0.0378
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表 3 非对称入流的无滑流影响机翼力矩计算结果
Table 3. Result of wing moment without slipstream influence at asymmetrical inflow
工况 俯仰力矩/
（N·m）偏航力矩/
（N·m）滚转力矩/
（N·m）ASYM-3-0 0.333 0.026 1.127 ASYM-3-5 0.293 0.062 1.347 ASYM-3-10 0.298 0.098 1.555 ASYM-3-15 0.313 0.138 1.685 ASYM-3-20 0.361 0.200 1.815
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表 4 受螺旋桨滑流影响的机翼力矩
Table 4. Wing moments influenced by the propeller slipstream
工况 俯仰力矩/
（N·m）偏航力矩/
（N·m）滚转力矩/
（N·m）ASYM-0-5 0.268 0.064 −1.709 ASYM-3-5 0.366 −0.004 −1.627 ASYM-6-5 0.432 −0.079 −1.484 ASYM-9-5 0.456 −0.144 −1.266
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表 5 不同风速下，有/无滑流对机翼升阻特性的对比
Table 5. Comparison of wing aerodynamic coefficients with and without propeller slipstream under different freestream velocity
工况 $C_{\rm{lavg} }$ $\Delta C_{{\rm{lavg} } }$/% $C_{{\rm{davg} } }$ Δ$C_{{\rm{davg} } }$/% $C_{{\rm{lavg} } }$/$C_{{\rm{davg} } }$ （Δ$C_{{\rm{lavg} } }$/$C_{{\rm{davg} } }$）/% ASYM-3-10-20-Pro-on 0.252 18.96 0.043 4.88 5.886 15.23 ASYM-3-10-20-Pro-off 0.211 0.041 5.108 ASYM-3-10-25-Pro-on 0.252 20.00 0.042 2.44 5.977 16.69 ASYM-3-10-25-Pro-off 0.210 0.041 5.122 ASYM-3-10-30-Pro-on 0.252 21.74 0.042 2.44 6.013 19.09 ASYM-3-10-30-Pro-off 0.207 0.041 5.049
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