Underlying mechanisms of propeller wake interaction with a wing
Underlying mechanisms of propeller wake interaction with a wing
复制标题
螺旋桨尾流与机翼相互作用的基本机制
DOI：
10.1017/jfm.2020.792
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发表时间：
2020
影响因子：
3.7
通讯作者：
M. Felli
中科院分区：
文献类型：
--
作者：
M. Felli
摘要本文研究了螺旋桨尾涡与无翼尖无升力机翼相互作用的基本机理。该研究包括对具有高厚度参数的参考螺旋桨机翼配置进行全面的实验调查，并基于时间分辨可视化以及详细的流量和壁压测量。实验的目的是研究螺旋桨叶片涡的动态过程中的方法，遇到和穿透阶段的相互作用和下游的身体。为此，制造了三种不同的机翼模型，其中包括一个透明的有机玻璃模型，该模型对于在穿透阶段同时可视化机身压力侧和吸力侧的涡流分支的演变至关重要。研究深入了解螺旋桨桨尖和叶片尾涡和机翼之间的复杂相互作用的基本潜在机制，为不同的螺旋桨负载。据发现，在遭遇和早期穿透阶段，叶尖涡行为受到其与机翼边界层相互作用的强烈影响，这表现为沿着机翼压力侧和吸力侧行进的涡部分的非对称演化和破裂。在穿透阶段，源自涡核和机翼附面层内的涡线之间的重新连接保持了涡的压力侧部分和吸力侧部分之间的联系，并促使它们在机翼下游重新结合。
Abstract The present study investigates the fundamental mechanisms of interaction between the propeller wake vortices and an untipped non-lifting wing. The study consists of a comprehensive experimental survey of a reference propeller–wing configuration with a high thickness parameter and is based on time-resolved visualisations and detailed flow and wall-pressure measurements. The experiment was designed to investigate the dynamics of the propeller blade vortices during the approach, encounter and penetration phases of the interaction and downstream of the body. To this end, three different models of the wing were manufactured including a transparent Perspex model that was crucial to simultaneously visualise the evolution of the vortex branches on the pressure and suction side of the body during the penetration phase. The study gains insight into the fundamental underlying mechanisms of the complex interaction between the propeller tip and blade trailing vortices and the wing for different propeller loadings. It is found that, during the encounter and the early penetration phases, tip vortex behaviour is strongly influenced by its interaction with the boundary layer of the wing that is manifested by a non-symmetrical evolution and breakdown of the vortex portions travelling along the pressure and suction sides of the wing. Reconnection between the vortex lines originating within the vortex core and the wing boundary layer maintains the linkage between the pressure and suction side portions of the vortex during the penetration phase and drives their rejoining downstream of the wing.
刀片涡流切割过程中的涡重连接
影响因子：
3.7
作者：
Saunders, D. Curtis;Marshall, Jeffrey S.
通讯作者：
Marshall, Jeffrey S.
非零轴流涡流切割过程中叶片上的瞬态升力
影响因子：
3.7
作者：
Saunders, D. Curtis;Marshall, Jeffrey S.
通讯作者：
Marshall, Jeffrey S.