Research Information System
Journal of the Faculty of Engineering and Architecture of Gazi University, vol.38, no.4, pp.1995-2008, 2023 (SCI-Expanded)
Missile aerodynamic design studies require flight control of an aircraft that passes through diverse flight regimes with extreme maneuvering requirements, using a minimal control surface set. These challenging goals are achieved typically using a simplified pre-design tool among thousands of body-fin alternatives. Alternative geometries found at this stage are then transferred to the computational domains, and CFD analyses are conducted to ensure aerodynamic performance. However, this new stage involves a costly and time-consuming preprocessing workload. For this reason, the number of missile geometries transferred from the pre-design stage is very limited. Considering that pre-design tools cannot provide sufficiently precise results, it is seen that this transfer mechanism should be replaced with a new method that is less costly than traditional workflow but more precise than pre-design tools. This study presents a new software tool that uses Missile DATCOM design terminology to generate solution domain and computational mesh automatically. This technology generates a remarkably high-quality structured mesh around the missile geometry. Fin control angles can be applied, and CFD analyses are performed at desired flight conditions. CFD analyses are performed using an in-house compressible CFD tool, and a good match with the experimental results is observed.