桨叶翼型弯度对摆线桨悬停状态的气动性能影响

钱悦; 黄典贵

doi:10.13224/j.cnki.jasp.2018.06.024

桨叶翼型弯度对摆线桨悬停状态的气动性能影响

doi: 10.13224/j.cnki.jasp.2018.06.024

钱悦,
黄典贵

上海理工大学能源与动力工程学院，上海 200093

基金项目: 国家自然科学基金（51536006）；上海市科委科研计划项目（17060502300）；上海市科委基地建设项目（13DZ2260900）

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出版历程
- 收稿日期: 2016-11-27
- 刊出日期: 2018-06-28

Effect of blade camber on aerodynamic performance of cycloidal propeller under hovering status

摘要

摘要: 以悬停状态下的摆线桨为研究对象，利用数值模拟方法，分别研究了桨叶相对弯度X和最大弯度位置Y对摆线桨气动性能的影响。结果表明：与桨叶为对称翼型的摆线桨相比，当桨叶具有一定弯度且最大弯度位置适中时，摆线桨气动性能得到很大的提升。当桨叶相对弯度X为4%C(C为翼型弦长)、最大弯度位置Y距离前缘40%C~50%C时，摆线桨升力和气动功耗比较低，悬停效率最高，整体气动性能更好。
- 摆线桨 /
- 悬停 /
- 相对弯度 /
- 最大弯度位置 /
- 气动性能
Abstract: A series of cycloidal propellers were studied numerically under hovering status. The effects of the blade relative camber X and the location of the maximum camber Y of the blade on the aerodynamic performance of cycloidal propeller were studied respectively. The results indicated that compared with the cycloidal rotors with the blades of symmetrical airfoils, the aerodynamic performance of cycloidal propeller was improved greatly under the moderate camber and appropriate location of the maximum camber of the blade chord. When the relative camber X was 4%C (C was chord length) and the location of the maximum camber Y was at 40%C-50%C from the leading edge, the lift and power of the cycloidal propeller were relatively lower, the hovering efficiency was higher than other conditions, and the overall aerodynamic performance was better.
- cycloidal propeller /
- hovering /
- relative camber /
- location of the maximum camber /
- aerodynamic performance

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参考文献(21)

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