Numerical Study of Aerodynamic Characteristics of Flow over a Serrated Double Delta Wing at Different Angles of Attack

Abstract

Since the dawn of flight, one of our objectives has been to enhance the aerodynamic performance of flying objects. Due to their great sweep, delta wings have a flow that is significantly more three-dimensional than wings with a high aspect ratio. A leading-edge vortex system on the lee side of the wing controls the flow pattern in subsonic flow conditions. It is necessary to understand the flow characteristics completely before the aerodynamic performance of the delta wing aircraft. In the present study, a simplified serrated double delta aircraft model has been considered and the flow characteristics over model were studied both numerically and experimentally. The simulation was carried out using Reynolds-averaged Navier Stokes (RANS) equations with k-omega turbulence model. The stall was observed at an angle of attack of α = 28 and lift has started falling from there onwards for the increase of α. Using the k-nearest neighbour (k-NN) clustering technique, principal component analysis it was confirmed that, out of seven significant flow variables, vorticity plays a major role in the study of flow characteristics.