Numerical study of axisymmetrical transsonic impact based on the SST turbulence model

This study presents a comprehensive numerical simulation of the aerodynamic behavior of an axisymmetric model featuring a spherical convex radome at transonic Mach numbers, employing the Comsol Multiphysics software package for advanced computational analysis. The primary focus is on the shock wave dynamics that develop at the upper section of the spherical convex fairing, a critical aspect for understanding the aerodynamic performance and stability of aerospace vehicles. By simulating various conditions, the study seeks to capture the intricate interactions between the incoming airflow and the radome structure, which are crucial for optimizing design parameters. The numerical results obtained are rigorously compared with experimental data from the research conducted by Bachalo and Johnson, illustrating a close alignment that reinforces the accuracy and reliability of the numerical calculations. These simulations utilize the Shear Stress Transport (SST) turbulence model, which is adept at handling complex flow features, further validating the significance of these findings for future aerospace applications.