本文由边界元方法出发,将适用于单连通空间Laplace问题的边界积分方程推广到带环量的多连通空间中,并对离散边界积分方程中的矩阵元积分式解析化,以避免在翼型尾缘处尖点附近直接利用数值积分计算矩阵元导致的数值振荡,对于以翼型表面压力分布为收敛目标的反设计问题,利用Newton-Raphson迭代求解满足该目标压力的非线性方程组,从而构造关于二维不可压缩流动翼型反设计问题的一个简便有效的隐式迭代算法。我们采用不同的数值算例对该算法予以检验,数值算例显示本文提出的隐式反设计算法收敛范围和来流攻角无关,且明显大于依赖于来流攻角的显式反设计算法的收敛范围,另外该算法精度高且具有很快的收敛速度。该翼型反设计算法有望在可变形翼型气动性能的研究中得到应用。 Based on the boundary element method, the boundary integral equations applicable to the Laplacian problems in the single connected space are generalized to the multi-connected spaces with loops. The matrix elements in the discrete boundary integral equations are analytically resolved to avoid the problem that the airfoils The numerical oscillation is directly calculated by the numerical integral method near the tail point of the trailing edge. For the inverse design problem that the airfoil surface pressure distribution is convergent, the Newton-Raphson iterative method is used to solve the nonlinear equations satisfying the target pressure. A Simple and Effective Implicit Iterative Algorithm for Two Dimensional Incompressible Flow Airfoil Anti-Design. We use different numerical examples to test the algorithm. The numerical examples show that the convergence range of the implicit inverse algorithm proposed in this paper is independent of the angle of attack, and is obviously larger than the explicit inverse algorithm that depends on the angle of attack Convergence range, in addition the algorithm has high precision and fast convergence speed. The airfoil inverse design algorithm is expected to be applied in the study of aerodynamic performance of deformable airfoils.