Controlling and directing the boundary layer on the surfaces of a flight vehicle are two of the most demanding challenges in\nadvanced aerodynamic designs. The design of highly integrated and submerged inlets with a large offset between the entrance\nand compressor face is particularly challenging because of the need for controlling or reducing the adverse effects of the\nboundary layer on propulsive efficiency. S-duct diffusers are used widely in flight vehicles when the compressor face needs to be\nhidden, and their performance is generally sensitive to the quality of ingested boundary layer from the fuselage. Passive or active\nflow control mechanisms are needed to prevent flow separations at the bends. In this paper, a new method is presented for\noptimal inlet/body integration based on a pair of ridges ahead of the inlet and its effects on the performance of a semicircular Sduct\ninlet integrated on a flat surface using CFD. In this design, the ridge changes an inefficient inlet concept to one with\nacceptable performance. The new method of integration is practicable for top-mounted inlet configurations where the use of\ndiverters and other mechanisms results in higher amounts of drag, weight, and complexity.
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