计及边界层汇流效应的多段翼型失速特性计算

 本文给出计及边界层汇流效应的多段翼型失速特性的解法。用高阶奇点分布面元法（Panel Method）求位流解,然后进行各翼段粘性尾迹形状迭代,并解出正常边界层和汇流边界层特性。当翼段上有后缘分离时,还要确定分离尾迹的形状,用位移厚度当量源（汇）模拟粘性效应。进行粘/位流迭代直至收敛。上述方法在超过多段翼型失速迎角时仍然有效。计算结果与实验数据比较,符合良好。

PREDICTION OF THE STALL CHARACTERISTICS OF MULTIELEMENT AIRFOILS WITH CONFLUENT BOUNDARY LAYER

A computing model with confluent boundary which computes the stall characteristics of multielement airfoils in a separated flow has been developed. A high order singularity panel method is used for the potential flow solution. The characteristics of ordinary and confluent boundary layer and viscous wake based on potential flow solution are obtained. A sparated wake model is used when the separation at the trailing edge of a certain element of the multielement airfoils occures. The final viscous solution is obtained by representing the boundary layer displacement thickness withan appropriate source distribution and by a viscous-potential interative technique. The calculated pressure distribution, the lift and the drag for angles of attack up to stall are in well agreements with experimental measurements.