中文摘要：

采用微可压缩模型（SCM）做为双三角翼低速流动控制方程,采用二阶Roe格式和LU-SGS方法离散控制方程。研究20°根弦名义攻角下,76°/40°双三角翼具有不同静态滚转角下的定姿态涡流特性。研究给出了不同滚转角下的空间涡流及表面极限流线,对滚转引起的攻角、侧滑角效应以及后掠角效应进行了分析,并对这些效应引起的流场结构、表面压力分布及气动力/力矩特性的变化进行了分析。结果表明：SCM能够较好地模拟低速双三角翼背风区的复杂涡流场,方法稳定性、收敛性较好 静态滚转导致双三角翼背风区涡流呈现复杂的非对称现象和涡破裂特征,并导致升力下降、横向稳定性变差。

英文摘要：

The Slightly Compressible Model （SCM） was employed as the control equations for low Mach number flow and was discretized by the spatial 2nd order Roe Scheme and LU- SGS scheme. The vortexes flow- fields of the 76/ 40- deg double- delta wing in fixed attitude with 20- deg nominal attack angle and varies static roll angle were presented. The spatial vortexes flow trajectories and the extreme surface streamlines were presented to illustrate the effects arose by roll- induced attack angle and slide angle, furthermore, the varieties of flow structures, surface pressure distribute, aero- force and aero- moment which were brought by these effects were analyzed also. The results indicates： the SCM can well predict the complicate vortexes flow- field of low speed double- delta wing with a nice performance of stability and convergence ; static roll angle can lead unsymmetrical phenomena and burst of the leeward vortexes flow on double- delta wing, hence, lead reduction of lift force and slack of transverse stability.