| Citation: | HU Yu, ZHANG Xuepeng, WANG Qiang, et al. Improved design of hovering efficiency of ducted propeller with large blade tip clearance based on grooved duct configuration[J]. Journal of Aerospace Power, 2025, 40（3）：20220650 doi: 10.13224/j.cnki.jasp.20220650
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In order to improve the aerodynamic efficiency of the ducted propeller, high machining and assembly accuracy were required to maintain a small clearance between the blade tip and the duct, resulting in a significant increase in the processing, operation and maintenance costs. To solve this problem, the design philosophy of improving hovering efficiency with large blade clearance was studied based on the grooved duct configuration. Calculation was carried out based on Reynolds averaged NS equation and multiple reference frame model. Firstly, based on the baseline design of a conventional ducted propeller, it was found that when the blade tip clearance ratio increased to four times the reference tip clearance ratio, the hovering efficiency decreased by more than 25%. Therefore, the increase of the blade tip clearance led to a significant decrease in the hovering efficiency. Secondly, based on parametric analysis, it was found that tip position and groove shape are key variables determining the hovering efficiency. By properly extending the blade tip into the groove, the hovering efficiency can be equivalent to that of the baseline design when the blade tip clearance ratio reached 6.7 times of the reference tip clearance ratio. If the circular groove was used, the hovering efficiency can be increased by 5.2% when the blade tip clearance ratio was 2 times of the reference tip clearance ratio. The results of numerical simulation and experiments indicated that the grooved duct configuration can improve the aerodynamic efficiency and reduce costs with a large tip clearance ratio.
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