摘要
旋转机翼无人机由于兼具垂直起降和高速巡航性能而备受青睐,旋转机翼翼型不同于固定翼,对旋转机翼翼型的设计和气动特性的研究具有实际意义。针对旋转机翼翼型展开有弯度的前后对称翼型设计,通过亚音速多工况数值计算筛选出升阻特性最优的翼型——弯度10%、厚度12%的上凸下凹前后对称翼型GOE-10-12。为了验证数值计算的准确性,进行了3种低速工况(20 m/s、30m/s、40 m/s)的风洞试验,结果表明数值计算和试验获得的升力系数和阻力系数吻合较好,新设计的翼型具有良好的升阻力特性,适合应用于旋转机翼。
An unmanned aerial vehicle （ UAV） with rotational wings is popular because it can take off and land vertically and cruise at high speed. The airfoil with rotational wings is different from the airfoil with fixed wings. The difference is significant for the design of the airfoil with rotational wings and for the study of its aerodynamic charac-teristics. Therefore, we design a cambered （ upper surface convex and lower surface concave/USCLSC） and fore-and-aft symmetrical airfoils for the UAV with rotational wings. The subsonic numerical calculation is performed to determine the airfoil with the optimal lift drag ratio, whose maximum camber is 10%, and maximum thickness is 12%. To verify the accuracy of the numerical calculation, we conduct wind tunnel tests under three low speed work conditions：V=20 m/s, 30 m/s and 40 m/s. The test results, given in Figs.3 through 9, and their analysis show preliminarily that the lift coefficient and drag coefficient obtained with the numerical calculation agree well with those obtained with the test results, which indicate that the airfoil we thus designed has good aerodynamic charac-teristics and is suitable for a rotational wing.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2014年第3期341-345,共5页
Journal of Northwestern Polytechnical University
基金
2012年国家大学生创新训练计划项目(201210699018)资助
关键词
旋转机翼
前后对称翼型
上凸下凹
CFD
风洞试验
气动特性
aerodynamics, airfoils, computational fluid dynamics, design, drag coefficient, lift drag ratio, turbu-lence models, unmanned aerial vehicles （UAV）, wind tunnels, wings, rotational wing, fore-and-aftsymmetrical airfoil
wind tunnel test
aerodynamic characteristics
