This paper deals with a numerical investigation of bleed effects on supersonic inlet performance under various bleed conditions such as location, width, and pressure in the plenum, and inlet conditions such as inflow Mach number and Throttling Ratio (TR). Because of high computational cost of direct simulation for each bleed hole, the bleed boundary condition model introduced by Slater is used. The boundary condition is implemented and validated by solving two validation cases, and then flow around a supersonic inlet used in Nagashima's experiments with bleed is simulated in order to show the effects of bleeds on inlet performance. The Kriging metamodeling in conjunction with the Genetic Algorithm (GA) is employed to find the optimal condition of bleeds at which the total pressure recovery in the air chamber is maximized. The Expected Improvement (EI) method is also used to find additional sample points that can enhance the initial metamodel. The optimal conditions of bleeds are obtained for each Mach number and TR, and then a specific condition where the total pressure recovery is increased for all Mach numbers and TR's is obtained. The numerical results show the total pressure recovery is substantial when the terminal normal shock is located near the throat, and the inlet mass flow is increased as the state of flow around the inlet becomes nearly critical.
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