摘要: Shock wave boundary layer interaction is one of the prominent aspects of the hypersonic flow, which governs intake performance. The cowl tip shock impinges on the floor of the isolator wall over which the boundary layer is develop... 展开 Shock wave boundary layer interaction is one of the prominent aspects of the hypersonic flow, which governs intake performance. The cowl tip shock impinges on the floor of the isolator wall over which the boundary layer is developing and may separate it to form a separation bubble. Further, it acts as a blockage to the incoming air and may lead to mass spillage and cause the intake to unstart. The present numerical campaign is based on determining the size of the separated bubble for the intake model experimentally tested by Fischer and Oliver using two different free-stream conditions corresponding to different flow enthalpies. This paper further analyses the wall temperature effects on the separation bubble size by modeling it as isothermal with elevated wall temperature between 300 K -1000 K and the insulated wall for each free-stream condition. Ultimately, this paper reports the intake's performance quantified by Total Pressure Recovery (TPR), Flow Distortion (FD), and Mass Flow Ratio (MFR) operating under these varied free-stream conditions. 收起