Abstract
The complex three-dimensional flow field produced by secondary injection of hot gases in nozzle of a rocket motor for the thrust vector control is analyzed by solving three-dimensional governing equations, using Fluent code, with appropriate boundary conditions. Various system performance parameters like secondary jet amplification factor, axial thrust augmentation are computed as part of the flow field solution and compared with the previous experimental and computational studies. The agreement is good within the practical range of secondary injectant flow rates for thrust vector control applications.
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