摘要
本文以低雷诺数下小型多旋翼无人喷洒机的翼型为研究对象。由于微小型旋翼尺寸小,凹凸翼型前后缘比较尖,造成该部分在结构强度和刚度偏低,易受到损伤。考虑其对气动性能、高结构强度和制造方便及轻量化的要求,对某凹凸翼型的前后缘结构进行了改进:对距前缘3.6%b和距后缘4.5%b处进行12.9°的倾斜剪除,其余部分不变。采用基于二维定常、不可压缩Navier-Stoke方程的数值仿真方法计算了该翼型在雷诺数为40000~100000,迎角α=1°~12°下的气动性能,并分析了该翼型上下表面的压力系数分布图和马赫数分布图,结果表明该翼型具有良好的气动性能且前后缘强度也得到了加强。
The airfoil of small multi rotor unmanned sprayer is studied under low Reynolds number in this paper. Due to the small size of the small rotor, the front and rear of the convex airfoil is relatively sharp, resulting in its structural strength and stiffness is low, it is vulnerable to damage. Considered the aerodynamic performance, convenient manufacture, high structural strength and lightweight requirements, an improvement on the structure of the concave trailing edge airfoil is put forward： cutting off 12.9 degrees at 3.6%b from the leading edge and 4.5%b from trailing edge, and the same of the remaining part. In this paper the method of numerical simulation of two-dimensional steady and incompressible Navier- Stoke equations based on the calculation of the airfoil at a Reynolds number 40000-100000, angle of attack =1 ~12 degrees of aerodynamic performance is used, and we study the airfoil pressure coefficient distribution map and the Maher number distribution on the surface of the airfoil ,The results show that the airfoil has good aerodynamic performance and the strength of the front and rear edges is also strengthened.
出处
《设计》
2017年第11期100-102,共3页
Design
基金
国家自然基金项目(工程NO.51505131)
河南教育厅自然基金(2009A630062)
河南理工大学博士基金(B2009-32)
关键词
低雷诺数
改进翼型
气动性能
仿真
Low Reynolds number Improved airfoil Aerodynamic performancesimulation
