Installation location of inlet is crucial for minimizing the length of the propulsion system and improving the overall performance of the hypersonic vehicles. This study investigates the impact of inlet installation location on overall performance and operational range extension. Employing numerical simulation techniques, a parameterized simplified model integrating the forebody with a 2D inlet is utilized for comprehensive aerodynamic performance evaluations. While maintaining inlet shape and airflow compression direction, the study examines how varying installation locations affect hypersonic inlet performance metrics. Results indicate a decrease in airflow capture rate and compression efficiency with increasing distance from the nose to the inlet location, accompanied by a linear increase in the critical self-starting Mach number.