分别采用数值方法和实验方法研究了大后掠角三角翼大攻角条件下，背风面开缝吸气对流场结构和气动力特性所造成的影响。数值模拟采用 Ｈａｒｔｅｎ Ｙｅｅ 的二阶精度隐式 Ｔ Ｖ Ｄ 格式和 Ｎ Ｓ方程；实验采用激光蒸汽屏流场显示和应变天平测力技术。通过在三角翼背风面开缝吸气，抽掉低能气流，实现增升的效果不理想，同二维吸气涡控制增升效果相差很远，这主要是由于二维同三维分离产生机理上的差异所造成的。 Numerical and experimental methods were used to study the influence of open-air suction on the structure and aerodynamic characteristics of the flow field under the large angle of attack of the large sweepback wing. The second-order implicit T V D format and NS equation of HartenYee are used in the numerical simulation. The flow field of laser vapor screen and force measurement of strain balance are used in the experiment. It is not very good to lift the low-energy airflow to remove the low-energy airflow because of the slits in the leeward of the delta wing, which is far behind that of the two-dimensional suction vortex control. This is mainly due to the mechanism of two-dimensional and three-dimensional separation Caused by the difference.