摘要
采用虚拟压缩方法求解三维不可压缩N-S方程，数值模拟了无弯度、有弯度两类微型飞行器低雷诺数小展弦比薄翼的流场，将得到的结果与实验进行了对比，数据间有较好的一致性。然后在此基础上分析了弯度、展弦比等因素对小展弦比薄翼气动力特性的影响以及翼尖涡随攻角、展弦比的变化规律，发现翼尖涡是影响小展弦比薄翼气动力的一个重要因素。
The three-dimensional incompressible Navier-Stokes equations are solved by artificial compressibility approach , the flows around two kinds of low-aspect-ratio thin wings, flat and cambered, are simulated, numerical results agree well with the experimental data. Then the effect of camber and aspect ratio on aerodynamic characteristics of low-aspect-ratio thin wings is analyzed. The development of wing tip vortex with alterations of angle-of-attack and aspect ratio is investigated, it is found that wing tip vortex is an important factor that affects the aerodynamic characteristics of low-aspectratio thin wings.
出处
《空气动力学学报》
CSCD
北大核心
2007年第B12期114-120,共7页
Acta Aerodynamica Sinica
关键词
虚拟压缩方法
微型飞行器
小展弦比薄翼
低雷诺数
翼尖涡
artificial compressibility approach
micro air vehicles
low-aspect-ratio thin wings
low Reynolds number
wing tip vortex
