摘要
本文应用二维非定常比拟和恪子涡(Vortex-in-Cell)方法,数值模拟了三角翼前缘涡层的卷起以及与尾涡的相互作用。由于使用了数千个点涡和较小的空间网格,获得了前缘涡层小涡配对出现的较大的离散涡,模拟了紧卷涡层的不稳定现象。这是以前类似的工作未曾实现的。
The rolling-up of the leading-edge vortex sheet and interaction with the trailing-edge vortex are simulated numerically by using the two-dimensional unsteady analogue and vortex-in-cell method. By using several thousands of point vortices and small space mesh, we obtain the large scale discrete vortices on the vortex sheet as result of the pairing of small point vortices, thus simulate the instability phenomena of the rolling-up vortex sheet. Within our knowledge, no numerical research has ever obtained the similar result.
出处
《空气动力学学报》
CSCD
北大核心
1991年第3期294-299,共6页
Acta Aerodynamica Sinica
基金
国家自然科学基金
关键词
三角翼
涡
脱体涡
涡层
飞机
前缘
delta wing, vortex method, detached vortex, vortex sheet.
