Computational modeling of non-stationary processes of the internal supersonic gas flow on the example of the exit of the rocket from the starting container

Methods of calculations was developed. This method include non-stationary processes of internal supersonic gas flow on an example of an exit of the rocket from the starting container. By means of various techniques of research it was possible to carry out the analysis of influence of design data of the starting container for speed of movement of the rocket not only qualitatively, but also quantitatively. The same techniques allowed to estimate influence of an external temperature factor on parameters of an exit of the rocket from the starting container.