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- W1974657999 abstract "A transonic wind tunnel fluctuating-pressure test involved 21.6-in.-diam models of spacecraft shrouds. This large size, coupled with small microphones (116-in. diam) allowed detection of fine-grained effects from mutual interactions between terminal shock, vorticity, and boundary layer condition: sometimes interacting in pairs, sometimes three conjunctively, depending on relative strengths. This paper presents some static pressure and microphone data that suggest vorticity interaction with the shock structure, distorting the shock front. For a model with regularly spaced external corrugations, fluctuating pressure environments are described in terms of circumferentially periodic rippling of the shock that induces a broad zone of intense fluctuations. Coexisting with this zone, and about 3 dB more intense, is a localized environment associated with the highest-order nearfields from the unsteadily undulating shock front. The total environment is inexplicable in terms of shock discontinuity alone and illustrates that designing for decreased pressure fluctuations can sometimes involve more complications than merely decreasing shock strength." @default.
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- W1974657999 date "1970-01-01" @default.
- W1974657999 modified "2023-09-26" @default.
- W1974657999 title "Some Wind-Tunnel Test Developments Relating to Fluctuating Pressures of Transonic Shock-Boundary Layer Interaction" @default.
- W1974657999 doi "https://doi.org/10.1121/1.1974645" @default.
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