Flow deflectors which extended forward of an open-nose inlet for improving positive angle-of-attack performance and auxiliary scoops for use at off-design engine air-flow conditions were investigated at low angles of attack to determine their effect on net inlet performance. Tests were conducted on two flow deflectors and two auxiliary scoops in the Ames 6- by 6-foot supersonic wind tunnel. The Mach number range of these tests was from 0 to 1.50.nThe results show that a deflector inlet and a basic open-nose inlet have about the same net performance at low angles of attack although the flow steadiness characteristics of the deflector inlet are the less desirable. Thus, a flow deflector which improves performance at angles of attack causes no significant loss in performance at the conditions for high-speed flight.
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