CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance

The wing of missile can be considered as an effective factor for determination lift to drag ratio. However, there are few studies that investigate effect on aerodynamics. Therefore, the purpose this study is indicate aerodynamics and optimize geometry enhancement aerodynamic efficiency. designed tail-fin configuration selected from a previous which contains experimental data. In beginning study, Computational Fluid Dynamics (CFD) simulations performed compared with Wing then mounted CFD solution repeated modified at 6º angle attach (AoA) subsonic supersonic speeds. shows good performance in point when baseline model. addition, optimized improve using Multi-Objective Genetic Algorithm (MOGA). Objective functions determined coefficients. parameters design variables optimization. After optimization process, results showed coefficients improved geometry. response surface analysis presented show more forces. findings optimum efficient terms performance. method procedure applied or different