过渡期间升力+巡航eVTOL构型的螺旋桨-机翼相互作用
Propeller-wing interactions of a lift + cruise eVTOL configuration during transition
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中文总结 AI 辅助
本研究通过风洞试验，探究升力+巡航eVTOL过渡阶段螺旋桨与机翼间距及电机方向对气动性能的影响，发现后电机正装且短间距可提升升阻比，前螺旋桨靠近机翼正装可改善特定前进比下的性能。
中文摘要 AI 辅助
在从悬停过渡到前飞的阶段，升力+巡航飞机的垂直升力螺旋桨的尾流与机翼相互作用。本研究探讨了垂直升力螺旋桨与机翼之间的轴向和纵向间距变化如何影响这一关键阶段的空气动力性能。通过将电机相对于机翼在两个纵向位置设置为正装或倒装，引入了轴向变化。对由此产生的升力+巡航机翼构型进行了风洞试验，雷诺数范围为52,000至377,000，使用毛线束、压力测点和测力传感器来捕捉空气动力行为。结果表明，早期过渡阶段（前螺旋桨前进比在0至0.25之间）对构型变化特别敏感。后电机方向有显著影响：当在最短纵向间距下正装时，主动升力螺旋桨使设计的升阻比提高了约4个单位，而在后电机倒装的情况下，设计的升阻比降低了4个点。减小纵向间距放大了后螺旋桨的有益升力贡献和前螺旋桨通常不利的影响。然而，在正装方向下将前螺旋桨靠近机翼，在前进比0.11至0.25之间提升了性能，这是由于机翼与前螺旋桨的尾随涡之间有利的相互作用。
英文摘要
The wakes of a lift + cruise aircraft's vertical lift propellers interact with the wing during the transition from hover to forward flight. This study investigates how variations in axial and longitudinal separations between the vertical lift propellers and the wing affect aerodynamic performance during this critical phase. Axial variations were introduced by orienting the motors either upright or inverted at two longitudinal positions relative to the wing. Wind tunnel tests were conducted on the resulting lift + cruise wing configurations over a Reynolds number range of 52,000 to 377,000, using tufts, pressure taps, and load cells to capture aerodynamic behaviour. Results show that the early transition phase (front propeller advance ratios between 0 and 0.25) is particularly sensitive to configuration changes. Rear motor orientation had a pronounced effect: when oriented upright at the shortest longitudinal separation, the active lift propellers increased the lift-drag ratio of the design by approximately 4 units, whereas in the rear motor inverted case the design suffered a 4-point reduction in the lift-drag ratio. Decreasing the longitudinal separation amplified both the beneficial lift contribution of the rear propeller and the generally adverse effects of the front propeller. However, placing the front propeller closer to the wing in the upright orientation enhanced performance at advance ratios between 0.11 and 0.25, due to favourable interactions between the wing and the front propeller's trailing vortices.
