混合翼型对扑翼推进性能影响分析
Propulsive Performance of Complex Flapping Foils
查看参考文献13篇
文摘
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以NACA0006翼型为基准翼型,将其前缘部分更换为相对最大厚度较大的NACA0008、NACA0010、NACA0015和NACA0020翼型前缘部分,组成混合翼型.通过流体仿真软件Fluent 14.5对基准翼型及混合翼型进行数值模拟计算,并分析扑翼运动的推进性能.结果表明:混合翼型相较于基准翼型对扑翼运动推力系数和推进效率有显著提高. |
其他语种文摘
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The NACA0006 foil was used as the baseline, the leading edge of complex flapping foils was replaced as the counterpart of thicker NACA foil (NACA0008, NACA0010, NACA0015 and NACA0020). Fluent 14.5 was used in numerical studies, considering the propulsive performance of all complex flapping foils. The conclusion indicates that complex flapping foils have a more propulsive performance. |
来源
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上海交通大学学报
,2016,50(8):1228-1232,1240 【核心库】
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DOI
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10.16183/j.cnki.jsjtu.2016.08.014
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关键词
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扑翼
;
混合翼型
;
推进性能
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地址
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1.
西北工业大学航海学院, 西安, 710072
2.
中国船舶重工集团公司第七一三研究所, 郑州, 450000
3.
中国科学院沈阳自动化研究所, 沈阳, 110016
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语种
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中文 |
文献类型
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研究性论文 |
ISSN
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1006-2467 |
学科
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力学 |
基金
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西北工业大学研究生创意创新种子基金
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文献收藏号
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CSCD:5791665
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参考文献 共
13
共1页
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