本文采用单方程S—A湍流模型计算了尾缘襟翼与主体翼型连接处的凹槽对二维翼型气动特性及流场的影响。选用带有30％弦长固定偏斜20°角度尾缘襟翼的NACA0015翼型作为研究对象，分析了流场的相关特性。数值计算结果表明：凹槽对于带有尾缘襟翼的二维翼型气动特性有一定影响，在负攻角及较小正攻角时，减小翼型升力系数；随着攻角增大，出现驻涡或周期性脱落涡，在计算及实际应用中不能忽略该部分细小几何结构的影响；攻角继续增大，分离区覆盖连接处后，凹槽对流场基本没有影响。
Influence of a slot located at the 70% chord from the leading edge of a NACA0015 airfoil with a 30% chord trailing edge flap deflected 20° on the aerodynamic properties and flow field of the airfoil is analyzed using S-A turbulence model. The calculated results indicate that the slot has an obvious effect on the aerodynamic properties of the two dimensional airfoil. At the negative and low positive angles of attack, the slot decreases the lift coefficients of the airfoil. When the angle of attack increases, there are stationary or periodic shedding vortices near the trailing edge flap. But when the angle of attack is large enough, the slot has few influences on the flow field. The geometry near the airfoil/flap junctures requires much attention.
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