机翼平面形状参数摄动面元法

 在内部Ｄｉｒｉｃｈｉｅｔ边界条件的基础上,藉助于对奇异积分的解析微分,可用解析法计算偶强密度对机翼平面形状乡数的敏感性偏导致（建立一般敏感性方程所需）。机翼平面形状参数摄动后其偶强分布即可藉线性外推得出。从而,压力分布、升力和俯仰力矩系数即可快速确定。振动面元法与相应的低阶面无法计算结果表明,该方法有良好的准确度且使计算工作量大大减少（摄动外推所需ＣＰＵ时间比相应的低阶面元法少两个量级）。

CALULATION OF PERTURBATION PANEL METHOD ON THE PARAMETERS OF WINGPLANFORM

The sensitivity partial derivatives of doublet strength density with respect to the parameters of wing planfomi(bi-direction perturbation) which are needed to build the general senaitivity equations can be calculated with analytic method based on the intemal Dirichlet prob-leni fonnufation and analytical differentiation cascaded on singular integral8,and then the solu-tion of doublct strength distribution is generated for any perturbed wing planform by linear extrapolation.Thus the pressure distrlbuti on,lift and pitehing moment coefflcients are deter-mined very rapidly.The comparison between the calculated results of the present perturbation panel method and the corresponding lower-order panel method shows that the present algorithm is of fine accuracy and can substantially reduce computing cost required(CPU time req uired for perturbation extrapolation is two orders of magnitude less than that of the corresponding lower-order panel method).