摘要
以NACA0018为基准翼型,采用Fluent数值模拟的方法,对比研究了襟翼几何长度对翼型流场结构及升、阻力特性的影响;分别选取襟翼几何长度分别为0.2、0.3和0.4,翼缝相对宽度为1.5%,分析了襟翼几何长度对翼型气动性能的影响。结果表明,由于襟翼对翼型周围主涡发展和变化的影响,不仅改善了翼型的失速特性,同时也提高了翼型的气动性能。襟翼翼型的失速攻角在此次研究范围内均大于基准翼型,在攻角小于失速攻角时,襟翼翼型的升力系数均小于基准翼型,阻力系数均高于基准翼型,但升力系数的最大值均高于基准翼型。
Based on symmetrical airfoil NACA0018 airfoil,using Fluent software numerical simulation method,the influence of flap relative length on airfoil flow field structure and the resistance properties was compared and studied.When the flap relative length were 0. 2,0. 3,0. 4 and slot relative width of 1. 5%,effect of the flaps relative length on airfoil aerodynamic performance was analyzed. The numerical results showed that,due to the impact of the main vortex development and change around the airfoil by flap,the airfoil stall characteristics were improved,and the aerodynamic performance of airfoil was improved. Flap airfoil stall angle of attack within the scope was greater than that of the benchmark airfoils. When the angle of attack was less than the stall angle of attack,the wing flap type of lift coefficient was less than the benchmark airfoils,drag coefficient was higher than benchmark airfoils,but the maximum lift coefficient was higher than the benchmark airfoil.
出处
《能源工程》
2015年第2期8-12,20,共6页
Energy Engineering
基金
国家自然基金资助项目(E51176129)
上海市教育委员会科研创新(重点)资助项目(13ZZ120)
上海市教育委员会科研创新项目(13YZ066)
教育部高等学校博士学科点专项科研基金(博导类)资助项目(201231200110008)
关键词
襟翼
翼型
几何长度
攻角
flap
airfoil
relative length
angle of attack
