Abstract
It is established that self–oscillations in the gas cavity of a solid rocket motor are due to instability and periodic changes of large–scale compact vortex structures in the stagnation zones of the main flow of combustion products. Indirect data of full–scale tests and experimental studies show that compact stagnation zones are formed between the side wall of the gas cavity and the submerged nozzle and near the up bottom of the motor. A procedure was designed to calculate and predict Strouhal numbers and acoustic resonance phenomena in the gas cavity of a motor chamber due to changes of compact large–scale vortex structures.
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Sukhinin, S.V., Akhmadeev, V.F. Self–Oscillations in the Gas Cavity of a Solid Rocket Motor. Combustion, Explosion, and Shock Waves 37, 36–45 (2001). https://doi.org/10.1023/A:1002812624408
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DOI: https://doi.org/10.1023/A:1002812624408