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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。
In this paper, the airfoils of small multi-rotor unmanned airplanes at low Reynolds number are studied. Due to the small size of the miniature rotor, the leading and trailing edges of the concave and convex airfoils are relatively sharp, which results in the structure being less prone to damage in structural strength and stiffness. Considering its requirements on aerodynamic performance, high structural strength and ease of manufacturing and lightweighting, the front and rear edge structures of a concave and convex airfoil have been improved with an increase of 3.6% b from the leading edge and from 4.5% b from the trailing edge to 12.9 ° Tilt cut off, the rest unchanged. The aerodynamic performance of the airfoil with Reynolds number of 40000 ~ 100000 and angle of attack α = 1 ° ~ 12 ° was calculated by numerical simulation based on two-dimensional steady and incompressible Navier-Stoke equations. Surface pressure coefficient distribution and Mach number distribution chart, the results show that the airfoil has good aerodynamic performance and front and rear edge strength has also been strengthened.