Survey of Supersonic Inlets for High Mach Number Applications

James F Connors; John L Allen

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NASA NTRS · 19710065526

Survey of Supersonic Inlets for High Mach Number Applications

James F Connors·John L Allen

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Abstract

The various inlet design philosophies are assessed on the basis of recent experimental results obtained at Mach numbers up to 5. The basic compression systems (external, internal, and combined external-plus-internal) are compared for both Mach 4.0 turbojet and hypersonic-cruise ramjet engines. The inlet that appears best suited for the Mach 4.0 turbojet application is that with combined external-plus-internal compression. Because of the severe cooling and weight problems associated with variable geometry at hypersonic flight speeds, the fixed-geometry self-starting characteristics of external-compression systems may be the overriding factor in the selection of an inlet for the hypersonic-cruise ramjet.

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James F Connors, John L Allen. 1958-04-01. Survey of Supersonic Inlets for High Mach Number Applications. https://ntrs.nasa.gov/citations/19710065526

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