Improving aerodynamic performance of a wing using cfd based parametric optimization method

In this study, the aerodynamic shape of a wing is optimized using the response surface method. The aim of the study is to optimize the aerodynamic shape of the wing in such a way as to maximize the lift coefficient and minimize the drag coefficient while keeping the critical angle of attack above 10º. Optimization of the aerodynamic shape of the ONERA M6 wing, which has a typical symmetrical profile, was performed, and the optimization parameters were selected as sweep angle, taper ratio and root chord. Aerodynamic coefficients are obtained by the Computational Fluid Dynamics method and isolated wing model is used during the optimization. In this parametric optimization study, ANSYS Fluent was used and Reynolds Averaged Navier-Stokes solver and SST k-ω model were used for turbulence modal. First of all, the independence study from the mesh was carried out, 6 different mesh were studied to determine the optimum mesh and the results were compared with the experimental data. As a result of the comparison, the most suitable and feasible mesh for the study was selected. The Face Centered Composite (FCC) method was adopted for the Design of Experiment. In this context, response surface have been fitted and the optimized design has been obtained by using 30 Design Points whose critical angle of attacks obtained by evaluating every angle of attack of Design Points starting from 0º to up to 20º increasing by 1º. Response Surface Method is used in this parametric optimization study the effect of the wing planform parameters on aerodynamic coefficients are studied and discussed in detail. As a result of the study, wing planform is optimized to achieve 5% decrease and 3% increase in coefficient of drag and coefficient of lift, respectively, at the critical angle of attack value of above 10 º.