Coupled flow characteristic of inlet and tail-mounted propeller in tail-propelled unmanned aerial
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摘要:
针对尾部螺旋桨推进无人机，研究进气道与螺旋桨的流动耦合特性。采用瞬态数值模拟与滑移网格技术，分析地面与高空巡航状态下螺旋桨旋转对进气道内外流场的影响。建立包含机身、进气道和五叶螺旋桨的一体化模型，使用六面体与多面体混合网格。结果表明：地面状态下，螺旋桨滑流通过诱导流场扭转和收缩，使总压恢复系数提高0.17%，但总压畸变指数（
δ 60）因局部扰动呈周期性波动；巡航状态下，螺旋桨对进气道性能影响微弱，总压恢复系数波动仅0.05%，气动交界面（AIP）旋流角变化小于1.6°。在大迎角或侧滑角工况下，滑流可抑制流动分离，改善总压恢复与畸变，但对旋流特性改善有限。研究揭示了滑流与进气道流动的演化规律，为推进系统一体化设计提供依据。Abstract:The coupled flow between an inlet and a tail-mounted propeller in unmanned aerial vehicles was examined using unsteady simulations with a sliding mesh technique. The influence of propeller rotation on the inlet flow field was analyzed in ground and cruise states. An integrated model of the airframe, inlet, and five-blade propeller was established with a hybrid hexahedral/polyhedral mesh. Results showed that in ground state, the propeller slipstream increased the total pressure recovery coefficient by 0.17% due to flow twisting and contraction, while the total pressure distortion index
δ 60 fluctuated periodically. During cruise, propeller effects on the inlet were negligible, with total pressure recovery varying within 0.05% and swirl angle at the aerodynamic interface plane (AIP) changing less than 1.6°. Under high angles of attack or sideslip, the slipstream suppressed flow separation, improved pressure recovery and reduced distortion, but had limited effect on swirl patterns. The findings revealed the evolution of slipstream-inlet interactions, providing a support for integrated propulsion system design.-
Key words:
- unmanned aerial /
- vehicle inlet /
- propeller /
- tail propulsion /
- swirling flow
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图 4 试验与仿真的机身/进气道对称面壁面静压曲线对比
Figure 4. Comparison of static pressure curves on symmetry plane wall of fuselage/inlet between experiment and CFD
图 6 地面状态下螺旋桨进气道耦合空间流线（相位角φ=30°）
Figure 6. Coupled spatial streamlines of propeller and inlet in ground state （phase angle φ=30°）
图 7 地面状态速度云图及二次流线
Figure 7. Velocity contour and secondary streamlines in ground state
图 8 地面状态带螺旋桨不同相位下进气道的气动性能
Figure 8. Aerodynamic performance of inlet with propeller at different phases in ground state
图 9 地面状态带螺旋桨不同相位下进气道的旋流特性
Figure 9. Swirl characteristics of inlet with propeller at different phases in ground state
图 10 地面状态带螺旋桨不同相位下AIP二次流线图
Figure 10. Secondary streamlines diagram of AIP with propeller at different phases in ground state
图 11 巡航状态下不同相位下进气道的无量纲气动力系数
Figure 11. Dimensionless aerodynamic force coefficients of inlet at different phases in cruise state
图 12 巡航状态下机身/进气道/螺旋桨三维流线图
Figure 12. Three-dimensional streamlines diagram of fuselage/inlet/propeller in cruise state
图 13 巡航状态对称面（x=0 m）和螺旋桨中心截面（y=11.725 m）速度流线图
Figure 13. Velocity streamlines diagram of symmetry plane（x=0 m） and propeller central section （y=11.725 m）in cruise state
图 14 巡航状态螺旋桨拉力随相位角变化曲线图
Figure 14. Propeller thrust variation curve with phase angle in cruise state
图 15 巡航状态有无螺旋桨不同相位下进气道的气动性能
Figure 15. Aerodynamic performance of inlet with and without propeller at different phases in cruise state
图 16 巡航状态有无螺旋桨不同相位下进气道的旋流特性
Figure 16. Swirl characteristics of inlet with and without propeller at different phases in cruise state
图 17 不同相位下AIP总压恢复系数云图
Figure 17. Total pressure recovery coefficient contour of AIP plane at different phases
图 19 巡航大侧滑角（α=0°，β=16°）状态不同相位下进气道的气动性能
Figure 19. Aerodynamic performance of inlet at different phases in cruise state with large sideslip angle （α=0°, β=16°）
图 20 巡航大侧滑角（α=0°，β=16°）状态不同相位下进气道的旋流特性
Figure 20. Swirl characteristics of inlet at different phases in cruise state with large sideslip angle （α=0°, β=16°）
图 21 巡航大迎角（α=16°，β=0°）状态不同相位下进气道的气动性能
Figure 21. Aerodynamic performance of inlet at different phases in cruise state with high angle of attack （α=16°, β=0°）
图 22 巡航大迎角（α=16°，β=0°）状态不同相位下进气道的旋流特性
Figure 22. Swirl characteristics of inlet at different phases in cruise state with high angle of attack （α=16°, β=0°）
图 23 巡航大迎角（α=16°、β=0°）状态不同相位下AIP总压恢复系数云图
Figure 23. Total pressure recovery coefficient contour of AIP at different phases in cruise state with high angle of attack （α=16°, β=0°）
图 24 巡航大迎角（α=16°、β=0°）状态不同相位下AIP二次流线
Figure 24. Secondary streamlines of AIP at different phases in cruise state with high angle of attack （α=16°, β=0°）
表 1 螺旋桨相关几何参数及计算参数
Table 1. Propeller-related geometric parameters and calculation parameters
参数 数值 桨距角/（°）（0.7R处） 24.50（地面） 33.08（巡航） 转速/（r/min） 2 000 螺旋桨直径D2/mm 2415 螺旋桨旋转中心距
进气道入口距离L2/mm2424.89 参考面积S/m2 32.26 
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