This study examines the impact of varying obstacle widths on supersonic airflow within a 2D convergent–divergent nozzle. Using computational fluid dynamics (CFD) simulations, flow characteristics such as shockwave formation, pressure distribution, and wake region behavior were analyzed for different obstacle widths positioned at the nozzle exit. In this context, the term “tab” is used to describe the obstacles. The research aims to understand how obstacle width affects flow dynamics under supersonic conditions and its implications for nozzle performance in practical applications. The results indicate that variations in obstacle width have minimal influence on shockwave intensity, wake size, and overall flow stability. However, the changes in key performance parameters remain negligible across different widths. This study offers valuable insights into the role of obstacle width in optimizing nozzle designs for aerospace and propulsion systems, highlighting the necessity for further research on other geometric parameters and their combined effects to achieve a more comprehensive understanding.