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NASA NTRS · 19930089848

High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser

James F Connors·Richard J Flaherty
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Abstract

A zero-cowl-drag, all-external-compression inlet with an abrupt area discontinuity or subsonic dump diffuser has been proposed and demonstrated for high Mach number application. Isentropic compression was focused at the lip of a cylindrical cowl and limited by the requirements for shock attachment. Theoretical calculations of the performance of such an inlet showed that it may be suited for application at Mach numbers of 4 and above. In an experimental investigation at Mach 3.85, a 4.75-inch-diameter inlet attained a total-pressure recovery of 0.41 at a corresponding mass-flow ratio of 0.92. Subsonic diffusion over an area ratio of about 3.5 to 1.0 was accomplished in 1.25 inlet diameters. Essentially no difference in performance was obtained in a comparison of the dump and a conventional subsonic diffuser. On a range basis, the over-all performance of this inlet was at least comparable with that of the best on-design isentropic external-compression inlet previously reported. A variable Mach number configuration utilizing a telescoping spike with a subsonic dump diffuser is also included.

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James F Connors, Richard J Flaherty. 1958-05-12. High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser. https://ntrs.nasa.gov/citations/19930089848

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