Numerical Simulation of the Interaction Between Leading-Edge Vortex and Vertical Tail
Numerical Simulation of the Interaction Between Leading-Edge Vortex and Vertical Tail
复制标题
前缘涡与垂直尾翼相互作用的数值模拟
DOI：
10.2514/2.174
复制
发表时间：
1997
期刊：
影响因子：
2.5
通讯作者：
D. Rizzetta
中科院分区：
文献类型：
--
作者：
D. Rizzetta
流向涡旋对气动表面（如尾翼或尾翼）的冲击会导致效率损失、严重的非定常载荷、振动以及不利的稳定性和控制。这种旋涡通常由现代战斗机配置产生，用于补充升力，提高大攻角亚音速飞行状态下的性能和机动能力。在这种流动情况下，可能会发生涡流破坏，导致尾表面的冲击，并有可能导致疲劳引起的结构破坏。本研究考虑在自由流马赫数为0.2、根弦雷诺数为1.89 X 10.6的情况下，气流在攻角为23.2度的情况下，通过一个锋利的前缘70.0度后掠三角翼。
The impingement of a streamwise vortex on an aerodynamic surface, such as a fin or tail, can result in efficiency loss, severe unsteady loading, vibration, and adverse stability and control. Such vortices, commonly generated by modern fighter aircraft configurations, are employed to supplement lift and enhance performance and maneuvering capabilities in the high-angle-of-attack subsonic flight regime. In these flow situations, vortex breakdown can occur, leading to buffet of the tail surface with a potential for fatigue induced structural failure. The present investigation considers airflow at a freestream Mach number of 0.2 and root chord Reynolds number of 1.89 X 10 6 past a sharp leading-edge 70.0-deg swept delta wing at an angle of attack of 23.2 deg.