Abstract
The pressure fluctuations on a rigid cylinder owing to the scattering of an obliquely incident plane acoustic wave have been determined. This result is used to study the correlation pattern of the pressure fluctuations on the S‐IC vehicle owing to the noise of the exhaust gas mixing, when the vehicle is at the test or launch stand with the exhaust flow deflected. The plume is replaced by a series of discrete‐frequency sources, set at various positions in the exhaust gas, with sources of the whole spectrum of the noise generated occurring in each uncorrelated volume of the exhaust flow. The problems have involved obtaining a correct representation of the uncorrelated nature of the various sources, both in space in the exhaust gas and time for each individual source. Curves of the resultant pressure correlation patterns around the vehicle have been calculated for various frequency bands. [Work supported by NASA‐Marshall Space Flight Center, directed through Brown Engineering Company, Huntsville, Alabama.]
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