Shock structure modified to eliminate associated noise. Shock wave repeats in supersonic flow adjoining subsonic flow layer. When supersonic layer is added, shock wave is partially transmitted at interface. Result is almost total elimination of shock pattern after one or two reflections. Technique applicable to inverted as well as to normal-velocity-profile coannular jets and used to eliminate or reduce shock noise of turbojet engines.
Reduced Aircraft-Engine Noise
NASA Tech Briefs ; 7
01.08.1983
Sonstige
Keine Angabe
Englisch
British Library Conference Proceedings | 1999
|NTIS | 1989
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