摘要
采用非定常涡格法 ,计算了三角形和矩形薄翼突冲起动和等速上仰这两种常见的非定常运动 ,得到了前 (侧 )缘分离涡及尾涡非定常卷起的流动图象及气动特性。分析了展弦比和攻角的影响。等速上仰的计算结果显示 ,仰起的动态过程能明显抑制分离涡面的破碎倾向 ,提高升力系数。
With unsteady vortex lattice method(VLM),impulsive starting and upward ramp motion at constant angular rate are calculated for delta and rectangular wings. The results include unsteady pattern of leading/side edge vortex rollup and aerodynamic characteristics. Effects of the aspect ratio and angle of attack are analysed. Simulation results show that the upward ramp motion can significantly restrain the vortex breakdown and increase the lift coefficient.Present results are in convincing accordance with available experiments.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1995年第6期641-646,共6页
Acta Aeronautica et Astronautica Sinica
关键词
涡格法
非定常流
机翼
三角翼
脱体涡
vortex lattice method,unsteady flow,delta wings,trapped vortices
