The present investigation is motivated by vibration problems in solid-propell ant rocket motors. A class of interior flows modeled to simulate flow conditions inside rocket motor cavities is considered. The turbulence generated pressure fluctuation consists of two components, acoustic and hydrodynamic. The Bernoulli enthalpy theory of aeroacoustics is employed to extract acoustic pressure spectra from experimentally obtained turbulence data and acoustic impedance values at flow boundaries. The effects of turbulence intensities, sidewall acoustic impedance, length-to-diameter ratio of the cavity, and different mass flux on the acoustic pressure level are investigated in experimental configurations. Typical pressure levels inside rocket motor environments are calculated utilizing the A-B representation for propellant response.
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Hegde et al. (1985) studied this question.
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