PRESSURE DISTRIBUTIONS FOR A RECTANGULAR SUPERSONIC INLET AT SUBSONIC SPEEDS

摘要

An investigation has been conducted to provide pressure distribution data for a super¬sonic rectangular inlet at subsonic speeds. Variations in cowl and ramp geometry as well as sideplate sweep were investigated. Tests were made in the Langley 16-foot transonic tunnel and the Langley high-speed 7- by 10-foot tunnel for Mach numbers of 0.6, 0.7, and 0.8. Angles of attack investigated were 0°, 4°, and 8° for a range of mass-flow ratios.