<p>The design of the air intakes varies distinctly based on their application in regard to the flight speed. Among the multitude of requirements to meet the prerequisites of subsonic flight application, the flow field interaction with the compressor downstream of the intake plays a fundamental role in determining the stability of the engine. The performance of the compressor of the gas turbine engine relies on the degree of the spatial perturbations being fed at the inlet which eventually leads to determining performance of the engine on the whole. In the present case study, a steady pressure-based numerical integration of submerged air intake with first-stage axial flow compressor of a small gas turbine is performed. A critical flight operating within the flight envelope is chosen and the performance of the air intake due to the influence of the rotating downstream component is analyzed. The pressure distortion coefficient along with total pressure recovery are considered as the primary performance evaluating markers. The objective of the paper is to understand the influence of the axial compressor on the intake performance and study the extent of synchronization of flow field matching occurring between the aforementioned components.</p>