In this paper, an aerodynamic optimization is carried out to analyze the effect of leading edge shape on the aerodynamic performance for high pressure capturing wing (HCW) configurations. First, a parameterized method for the wing leading edge of an HCW is developed by combining a power function and a cosine function. The lift-to-drag ratio of the configuration is chosen as the goal of maximization. Next, a numerical optimization flow is constructed by combining with the uniform experimental design method, the computational fluid dynamics, the radial basis function surrogate model method and the genetic algorithm on the basis of the comparison of the accuracy between the polynomial surrogate model and the radial basis functional surrogate model. At last, the sensitivity analysis of optimization results for each parameter is implemented. As the comparison of the optimal to the baseline, the results show that the lift coefficient increased by 8.1%, the drag coefficient is decreased by 12.2%, the lift-to-drag ratio increased by 23.4%. In addition, the sensitivity analysis results show that the lift-to-drag ratio presents non-linear relationship with the five design parameters and the angle of wingspan had the greatest influence, followed by the exponential curve parameter, the effect of other three parameters on the lift-to-drag ratio is relatively weak.