Investigation of the Low-Speed Characteristics of Two Sharp-Edge Supersonic Inlets Designed for Essentially External Supersonic Compression

摘要

Wind-tunnel investigation was made on supersonic air inlets to obtain information on surface-pressure, drag, and pressure-recovery characteristics. Two types of sharp-edged annular inlets tested were designed for Mach numbers of from 1 to 3. Surface pressure distribution, minimum surface pressures, and critical Mach numbers were tested. It is concluded that sharp pressure peaks occur outside small velocity range, separation is confined to bubble at leading edge, external drag is higher than on round-edged cowlings, and better pressure distribution is possible with slight modification.