Computational aerodynamic optimization of wing-design concept at supersonic conditions by means of the response surface method

Abstract

In this paper, by means of computational fluid dynamics, a significant study has been made on the effects of geometric parameters of wing with capability of flying efficiently and cost-effectively at supersonic condition. Multi-objective optimization has been performed for the aerodynamic shape optimization of the wing configuration. The three-dimensional wing shape defined by four design variables is optimized. For achieving the most desirable aerodynamic efficiency (lift-to-drag ratio), Response Surface Method and Genetic Algorithm is utilized. To ensure the reliability of the solution and validating the numerical evaluation, flow around a delta wing is simulated and results are compared with credible numerical works. Furthermore, the particular design variables, which have serious effects on the objective functions, are found. Wing sweep angle along with aspect ratio has strong effects on the main outputs. Given that the current flow regime is supersonic, counteracting the negative effects of shock waves is one the most important design points. Among the studied parameters, leading edge sweep angle has the greatest impact on the main objectives of this research and it is the primary factor for delaying the formation of shock waves over the wing surface. Lift and drag coefficients, as primary objective functions, have higher sensitivity to changes in aspect ratio. By comparison to best geometry among initial cases, aerodynamic efficiency is increased by approximately 15% as a result of optimization study of this supersonic wing geometry.