翼上涵道风扇布局被认为是分布式电推进飞行器最具有发展潜力的动力-机翼融合构型之一，而对于涵道风扇与机翼耦合下升推特性的认知和表达是此类飞机设计的关键。针对涵道风扇–机翼耦合效应定量表征仍缺乏统一方法的问题，采用低速风洞试验与数值模拟相结合的方法，开展了单独机翼、单独涵道风扇以及翼上涵道风扇三种构型的气动特性研究，对比了涵道风扇与机翼在有/无耦合下的气动特性，并分析了在单位能量消耗下翼上涵道风扇布局相比翼段和涵道风扇简单叠加后的升推特性改善效应，进一步地，提出了能够表征涵道风扇-机翼作用规律的耦合因子，为此类飞机的总体设计和气动布局优化提供了新的关键表征参数。研究结果表明，翼上涵道风扇在低速工况下能够产生明显的升力增益，在中速区间表现出显著的综合效率优势，而在更高速域耦合效应逐渐转变为推力主导，其增益作用趋于减弱。该规律性认识为分布式电推进飞机的总体气动/推进一体化设计提供了理论基础与方法支撑。
The wing-mounted ducted fan configuration is regarded as one of the most promising power–wing integration layouts for distributed electric propulsion (DEP) aircraft. Understanding and characterizing the lift–thrust coupling between the ducted fan and the wing is crucial for the design of such aircraft. To address the lack of a unified quantitative method for describing ducted fan–wing coupling effects, this study combines low-speed wind tunnel experiments with numerical simulations to investigate the aerodynamic characteristics of three configurations: an isolated wing, an isolated ducted fan, and a wing-mounted ducted fan combination. The aerodynamic performance under coupled and uncoupled conditions is compared, and the improvement in lift–thrust characteristics per unit energy consumption is analyzed relative to the simple superposition of the individual components. Furthermore, coupling factors are proposed to quantitatively represent the interaction mechanism between the ducted fan and the wing, providing new key parameters for the overall design and aerodynamic layout optimization of DEP aircraft. The results show that the wing-mounted ducted fan generates significant lift augmentation at low speeds and demonstrates a distinct overall efficiency advantage in the medium-speed regime, while at higher speeds the coupling effect gradually transitions to thrust dominance, with diminishing gain. These findings establish a theoretical and methodological foundation for the integrated aerodynamic–propulsive design of distributed electric propulsion aircraft.
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