Abstract Lift augmentation and drag reduction on wedge surfaces at transonic flight regimes is challenging due to boundary layer-shock interactions. This research proposes a novel drooped wedge body configuration with five sequential leading-edge drooped steps and half wedge angle of 22.5°. The design was analysed at Mach 1.2 using computational fluid dynamics. 283 simulations were executed through Response Surface Methodology coupled with Genetic Algorithms to identify the optimal geometric designs. Analytical validation was performed using Garabedian-Korn methodology. Efficient solution processing is achieved using MATLAB. Through the optimization process the most efficient aerodynamic designs were identified. These designs were capable of delaying the separation of shock waves. 28.7 % reduction in drag coefficient and 19.2 % enhancement in lift coefficient were obtained compared to the baseline. Results indicate that modified wedge design provides better aerodynamic performance and can be incorporated in next-generation aerospace vehicles.
Rinchu et al. (Wed,) studied this question.