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,数据间吻合较好。然后在此基础上分析了小展弦比薄翼的气动力特性,详细研究了小展弦比薄翼流场中翼尖涡的涡态结构及形成规律,在对小展弦比薄翼流场尾迹区的翼尖涡采用近似模型的基础上,对尾迹区翼尖涡的强度进行了分析。结果表明,翼尖涡是影响小展弦比薄翼气动力和流动分离特性的一个重要因素。
The three-dimensional incompressible Navier-Stokes equations are solved by artificial compressibility approach, the flows around two kinds of low-aspect-ratio thin wings for Micro Air Vehicles, flat and cambered, are simulated at low Reynolds number, numerical results agree well with the experimental data. Then the aerodynamic characteristics of low- aspect-ratio thin wings are analyzed, The structure and formation of wingtip vortex in flows around low-aspect-ratio thin wings are studied in all details. Based on the approximate model of wingtip vortex, the strength of wingtip vortex in wake region of low-aspect-ratio wings flows is also analyzed. Results show that wingtip vortex is an important factor to affect the aerodynamics and flow separation of low-aspect-ratio thin wings.
出处
《空气动力学学报》
CSCD
北大核心
2008年第3期310-316,共7页
Acta Aerodynamica Sinica
基金
国家"863"课题(2007AA04Z129)
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
wingtip vortex
