摘要
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Fluent14.5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.
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 14.5was 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.
出处
《上海交通大学学报》
EI
CAS
CSCD
北大核心
2016年第8期1228-1232,1240,共6页
Journal of Shanghai Jiaotong University
基金
西北工业大学研究生创意创新种子基金(Z2015054)资助
关键词
扑翼
混合翼型
推进性能
flapping foils
complex foils
propulsive performance
