Numerical Investigation of Symmetrical Supersonic Inlet with Boundary Layer Suction

In this study, an input stream of symmetrical supersonic inlet with boundary layer suction has been investigated by using of two-dimensional full Navier Stokes equations. The analysis has been performed for three various Mach numbers. The main purpose of this study is reduction of adverse pressure gradient for performance improvement of supersonic air-intake. At this paper, the upper leading edge has been considered round because the sharp leading edge cannot withstand the high thermal loading in supersonic flow. The results show that the high pressure gradient across the crossing shock waves has been minimized by the use of boundary layer suction. So, the input mass flow rate to air-intake has been increased. Viscose and non-viscose Turbulent flow analysis has been done by McCormack explicit method. Modeling of turbulent flow has been done with Wilcox k-w two equations model. The results have been compared with the prestigious experimental papers at the end.