As distributed electric propulsion has continued to gain popularity as an enabling aircraft technology, further research is required to understand the complete implications of aeropropulsive coupling effects for distributed propulsion systems integrated into actual aircraft geometries. A set of low-speed wind-tunnel tests was performed at the University of Illinois at Urbana-Champaign to characterize the aerodynamic performance of a semispan Cirrus SR22T wing-body model that was equipped with an array of four ducted fans integrated into the upper-surface, trailing edge of the wing. Aerodynamic performance and aeropropulsive coupling effects were investigated through six-component load-cell measurements of the forces and moments experienced by the model, supplemented by chordwise pressure distributions at four stations along the span of the wing. Additionally, a set of unsteady force and moment measurements were taken to investigate time constants associated with the response of aerodynamic forces and moments to step changes in fan speed. It was found that the fan tip-speed ratio dictates the aerodynamic performance of the model, with primary effects including an increased lifting force, yawing moment, rolling moment, and nose-down pitching moment as the tip-speed ratio increased. Additionally, the lift-curve slope changed with tip-speed ratio as a function of thrust setting in relation to thrust required.

随着分布式电力推进作为一种使能飞机技术继续受到欢迎，需要进一步研究以了解集成到实际飞机几何结构中的分布式推进系统的气动推进耦合效应的完整含义。在伊利诺伊大学厄巴纳-香槟分校进行了一组低速风洞测试，以表征半跨 Cirrus SR22T 翼体模型的空气动力学性能，该模型配备了集成到上部的四个涵道风扇阵列。表面，机翼后缘。通过对模型所经历的力和力矩的六分量测力传感器测量，并辅以沿机翼跨度的四个站的弦向压力分布，研究了空气动力学性能和气动推进耦合效应。此外，还进行了一组非定常力和力矩测量，以研究与空气动力和力矩对风扇速度阶跃变化的响应相关的时间常数。结果表明，风扇叶尖速比决定了模型的空气动力学性能，主要影响包括随着叶尖速比增加而增加的升力、偏航力矩、滚动力矩和机头向下俯仰力矩。此外，作为与所需推力相关的推力设置的函数，升力曲线斜率随叶尖速比而变化。主要影响包括随着叶尖速比增加而增加的升力、偏航力矩、滚动力矩和机头向下俯仰力矩。此外，作为与所需推力相关的推力设置的函数，升力曲线斜率随叶尖速比而变化。主要影响包括随着叶尖速比增加而增加的升力、偏航力矩、滚动力矩和机头向下俯仰力矩。此外，作为与所需推力相关的推力设置的函数，升力曲线斜率随叶尖速比而变化。