Numerical research of the influence of changes in the nozzle outlet section on the main force of the rocket engine

Abstract

The paper presents a numerical research of the effect of reducing the diameter of the nozzle exit section on the characteristics of the rocket engine of an unmanned aerial vehicle. Additionally, an analytical research of the problem of gas outflow from the nozzle was carried out. Comparison of the results of numerical and analytical research methods is given. The expediency of taking into account dissipation losses and flow non-uniformity in analytical calculations is shown. Additional applications of the results of a numerical study of the characteristics of a rocket engine are identified