Effects of Flow Pulsation on Shock Wave/Boundary Layer Interaction in Supersonic Isolator

In scramjet engine, inlet isolator is used to provide stable compressed flow to the combustors. A series of oblique shocks are used to compress the flow by increasing static pressure. The shock wave/Boundary layer Interaction (SWBLI) is one of the major phenomenon in inlet isolator flow. Intel-Isolator is designed for fixed flow conditions, but flights can face fluctuating condition for various reasons which may affect the compression and separation characteristics inside the isolator. In our present study, a computation on the effect of pulsating flow on the shock wave/boundary layer interaction in supersonic inlet isolator is performed. The inlet flow condition is sinusoidal with different frequencies but with same amplitude with mean Mach number of 4.9. The different flow parameters at different flow conditions inside the isolator are observed. The hysteresis phenomena and dependency on the frequency of the cycle are examined in the study.