大迎角分离流动控制对于提高低雷诺数翼型气动性能、降低流致结构振动和噪声具有重要意义。针对当前经验试错及后验分析式流动控制效率低下的问题，结合预解分析理论和外形优化设计，提出了一种翼型绕流稳定性优化设计方法，从而实现表面变形被动控制。首先构建流动系统的输入-输出动力学模型，通过预解分析揭示不同频率谐波激励下响应最强的激励（强迫模态）和感受性最强的状态（响应模态）以及二者之间的放大倍数（预解增益）；其次建立预解增益与流动稳定性的定量关联：当流动系统满足秩1近似条件时，最大预解增益的降低直接对应流动稳定性的提升；进而以最大增益最小化为目标函数，结合罚函数及非线性共轭梯度法，构建了高效外形优化设计框架。以设计状态下Ma=0.1，Re=200，a=15度的NACA0012翼型为研究对象，通过设置不同罚函数因子得到优化构型Opt.1与Opt.2。计算结果表明：优化翼型Opt.1与Opt.2在小攻角气动性能无损失甚至有所提升的前提下，最大预解增益分别降低63.49%和54.44%，超临界攻角下流动稳定性显著提高，升力脉动幅值平均衰减16.2%和13.79%，同时时均阻力系数下降2.44%和1.84%。流场演化分析表明，大攻角下翼型前缘和后缘分离涡的交替生成、脱落导致了升力的显著振荡，外形优化则有效抑制了流动分离，实现了翼型气动性能-流动稳定性的协同提升。本研究为分离流动控制提供了新的理论指导，建立的基于预解分析的外形优化设计方法有望推广到不同失稳类型的分离流动问题。

Control of flow separation at high angles of attack plays a crucial role in enhancing the aerodynamic performance of airfoils under low-Reynolds-number, as well as in reducing flow-induced structural vibrations and noise. To address the inefficiency of current empirical trial-and-error and a posteriori-based flow control methods, we propose a novel approach that integrates resolvent analysis with airfoil optimization design to achieve passive surface deformation control of unsteady flows. We first construct an input-output dynamical model of the flow system. The excitation with the strongest response (i.e., forcing modes), the states with the highest receptivity (i.e., response modes) and the amplification between them (i.e., resolvent gains) under harmonic inputs at varying frequencies can be identified through resolvent analysis. Secondly, a quantitative correlation between the resolvent gain and flow stability is established. When the flow system satisfies the rank-1 approximation condition, a reduction in the maximum resolvent gain directly corresponds to an improvement in flow stability. Finally, an efficient shape optimization framework is developed, with the objective function defined as the minimization of the maximum gain, and the optimization process combining a penalty function approach with the nonlinear conjugate gradient method. The NACA0012 airfoil at the design condition Ma=0.1，Re=200，a=15 is selected as the test case, and optimized airfoils Opt.1 and Opt.2 are obtained by varying the penalty parameters. The computational results demonstrate that, under the condition of no loss or even an improvement in aerodynamic performance at small angles of attack, the maximum resolvent gain of Opt.1 and Opt.2 is reduced by 63.49% and 54.44%, respectively. The flow stability at supercritical angles of attack is significantly enhanced, with the amplitude of lift fluctuations attenuating by an average of 16.2% and 13.79%. Additionally, the time-averaged drag coefficient decreases by 2.44% and 1.84%, respectively. Analysis of the flow field evolution reveals that the alternating generation and shedding of leading-edge and trailing-edge separation vortices at high angles of attack lead to significant lift oscillations. The shape optimization effectively suppresses flow separation, achieving a synergistic improvement in both the aerodynamic performance and flow stability of the optimized airfoils. This study provides new theoretical guidance for airfoil separation flow control and establishes a resolvent-based shape optimization design method that is anticipated to be applicable to separation flow problems involving various types of flow instabilities.