An investigation was conducted at low speed of an air—induction system having twin scoop—type inlets on the sides of the fuselage of a model of an airplane designed for flight at supersonic Mach numbers. The leading edge of the lip of the scoop was rounded and there were provisions for control of the boundary layer ahead of the inlet.nAn analysis of the data indicated that high external drag was associated with separation of the flow from the external surface of the lip. Several different profiles for the lip were investigated and one was chosen for further tests of the air—induction system. There was no separation from the external surface of the lip selected for mass—flow ratios above 0.75 at angles of attack between 1° and 11°, and at 0° angle of attack the ram—recovery ratio was the highest obtained.
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