Numerical Investigation on Supersonic Airflow Around Tangent Ogive Wedge of Varying Fineness Ratio

The purpose of this study is to report the numerical investigation on the aerodynamic performance of tangent ogive wedge of varying fineness ratio from 2 to 4 when fully submerged in an incoming supersonic airflow having a velocity of Mach 2.5 and at zero degrees angle of attack. Numerical simulations have been carried out for flow over tangent ogive wedge using ANSYS CFD. A computation domain was created with appropriate geometrical constraints and was meshed into elements of optimum size. The supersonic airflow was simulated to observe and analyze the effects of change in fineness ratio of tangent ogive wedge on various aerodynamic parameters of interest under given boundary conditions and flow physics. It was observed that tangent ogive wedge with increasing fineness ratio experienced decreasing pressure drag force. The nature of shock generated for various tangent ogive wedge has been compared to understand airflow/shock interactions. The presented study revealed the dependency of different aerodynamic parameters on the fineness ratio of tangent ogive wedge, which may be efficiently utilized in missiles, rockets, and bullet design. The reported findings would contribute towards optimizing tangent ogive wedge shapes for supersonic missiles, rockets, and bullets, delivering optimum aerodynamic performance under given operating conditions.