Inlets, exits, and cooling problems I : inlets

摘要

As design flight speeds are pushed progressively higher, the supersonic inlet becomes an increasingly important component of air-breathing propulsion systems. Currently, the turbojet engine is being considered for application at Mach numbers up to approximately 4 and the ramjet engine for application in the hypersonic region, or Mach numbers of t and above. Herein the inlet situation is surveyed and the merits of various inlet-design philosophies are assessed on the basis of recent experimental data obtained at Mach numbers up to 5. These trends are then extrapolated into the hypersonic range for an analysis of the performance potentialities of the various ramjet-inlet configurations. (author)