Abstract
To test a method of calculating the boundary layer in liquid rocket engine (LRE) nozzles, developed by the authors and based on a differential three-parameter model of turbulence, nozzle flow with tangential-slot coolant injection in subsonic part of the nozzle is studied numerically. The effect of nozzle flow acceleration on the turbulence parameters and the dependence of the gas film effectiveness on the nozzle-inlet turbulence intensity are investigated. The numerical results are compared with available experimental data.
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