摘要
利用简化的飞机模型,通过改变尾翼的迎角及展弦比,试图建立一种能加速自我消亡的尾流涡系统。该实验在拖曳水槽中进行,运用SPIV(体视粒子图像测速技术)系统进行测量,获得了一系列空间切面的2D/3C(二维/三分量)数据,给出了三种不同尾翼情况(两种有尾翼情况及一种无尾翼情况)下的SPIV观测结果,并将这几种情况作了对比。
An experimental study with a simplified model was carried out to establish a self-destructing vortex wake by changing the attack angle and the aspect ratio of HTW （Horizontal Tail Wing）. A SPIV（Stereo- Particle Image Velocimetry） system was employed in a water towing tank to obtain the sets of 2D/3C（2D -2 dimentional field, 3C-three component velocity measurements） velocity field data in different special slices. The results from three kinds of tail settings （2 with and 1 without HTW） are exhibited and compared with each other.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2009年第1期18-22,共5页
Journal of Experiments in Fluid Mechanics
基金
中德(BUAA&DLR)国际合作基金
