Abstract
A Reynolds-averaged Navier Stokes (RANS) solver was used to study the flow through an axisymmetric, supersonic inlet with an annular bypass duct at freestream Mach numbers of 0, 0.3 and 1.7. The effects of struts in the flowfield and shock wave boundary layer interaction on total pressure recovery and distortion were studied. Three dimensional calculations were performed at angles of attack (AOA) of 0 ◦ and 3 ◦ at cruise, and 0 ◦ and 5 ◦ at takeoff. Two orientations of struts with respect to the crossflow direction were studied. The effect of reversed flow in the bypass duct at low Mach numbers was studied.
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