多段翼型失速分离特性的计算

本文用高阶奇点分布板块法(Panel Method》及边界层理论,对多段翼型的失速性能进行计算。采用分离尾迹的模型,按尾迹是流线用迭代法求出分离尾迹边界(此为内迭代)。在尾迹上配置奇点,然后把尾迹考虑在内进行粘/位流迭代(此为外迭代)。收敛后可得多段翼型空气动力特性,且可计算到失速以后的情况。算例有单段翼型GA(W)-1,NACA 4412,和F111飞机的三段翼剖面,所得结果与实验值能很好地符合。

A PREDICTION OF THE STALLING OF THE MULTIELEMENT AIRFOILS

The multi-component airfoil program which computes the stall characteristics has been developed. A higher order singularity panel method is used for the potential flow solution. The vorticity and sources distribution in each panel was assumed linear with respect to the arc length of the panel. A separated wake model is used when the separation occurs at the trailing edges of the elements of the multielement airfoils. The final viscous solution is obtained by representing the boundary layer displacement thickness with an appropriate source distribution and by a viscous-potential itieration technique. The calculated pressure distribution, the lift for angles of attack up to the stall are in good agreement with experimental measurement.