| Abstract: | A method of calculating of the boundary layer in liquid rocket engine (LRE) nozzles, developed by the authors and based on a differential three-parameter turbulence model, is tested using the known experimental data for the boundary layer on a plate in zero-pressure-gradient flow with tangential gas injection. Over a wide range of both bulk flow and injected gas parameters and for variable slot geometry, the calculations for both integral and local flow and heat transfer characteristics satisfactorily agree with experiment. The study has made it possible to obtain the governing parameters which significantly affect the gas film effectiveness. |
