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本文讨论优化前缘缝翼位置的位流设计方法。优化变量为缝翼相对于主翼的缝隙(Gap)、覆盖量(Ouerlap)和偏角δ_s,目标函数为主翼上的压力峰值。应用高阶面元法计算多段翼型压强分布。用Powell优化法使主翼上压力峰值减至最小,以延迟多段翼型的失速,增大最大升力系数。本方法已用于计算NACA64A010两段和四段翼型以及Foster三段翼型,所得结果与实验数据和位流/边界层耦合设计法的结果有很好的一致性。
This article discusses the design of a bitstream that optimizes the position of the slat. The optimization variables are the gap (Gap), the coverage (Ouerlap) and the declination δ_s of the slat with respect to the main wing. The objective function is the pressure peak on the main wing. Application of Higher Order Panel Method to Calculate Multi - Stage Airfoil Pressure Distribution. Powell optimization method to minimize the pressure peak on the main wing to delay the stalls of multi-section airfoil, increase the maximum lift coefficient. This method has been used to calculate the NACA64A010 two-stage and four-stage airfoils and the Foster three-stage airfoil. The results are in good agreement with the experimental data and the results of the coupled flow-boundary / boundary layer design.