Optimum aerodynamic design of transonic wing based on response surface methodology

In recent years the response surface methodology (RSM) has been applied in many design field, because of its high efficiency and practicality. In this paper, the optimization design of the transonic wing at single and multiple design-points is performed by RSM. The flow solver is based on 3D Euler equations. The quadratic polynomials are employed to construct RS model and the set of candidate design points in design space is selected to satisfy D-optimality. The optimum shape is obtained based on the RS model. A M6 wing is chosen as the base wing. The design results indicate that the RSM can capture the nonlinear behavior of the objective function and smooth out high-frequency noises in transonic regime. The model fitting quality is satisfied to the design. The fitting errors are less than three percent. These features enable the method to be utilizable and valid. The drag coefficient can be reduced about 19 percent in the single design-point for wing drag design.