Investigation of the air-flow regulation characteristics of a translating-spike inlet with two oblique shocks from Mach 1.6 to 2.0
The pressure recovery of an axially symmetric translating-spike inlet was essentially the same as for a single cone with the same total angle. In order to match a turbojet engine over the Mach range of 1.6 to 2.0, the spike translation must be larger than it is for a single cone.
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| Sprache: | eng |
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| Zusammenfassung: | The pressure recovery of an axially symmetric translating-spike inlet was essentially the same as for a single cone with the same total angle. In order to match a turbojet engine over the Mach range of 1.6 to 2.0, the spike translation must be larger than it is for a single cone. |
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