DETERMINATION OF GAS FLOW PARAMETERS IN THE NOZZLE OF A SOLID FUEL ROCKET ENGINE BY ANALYTICAL METHOD

Abstract

In this paper, a mathematical model is built to determine the working
parameters on the combustion chamber of a solid fuel rocket engine. Based on the
theoretical basis established for this model, the parameters of the gas flow in the
nozzle of the solid fuel rocket engine such as velocity, pressure, and temperature
are determined by Matlab software. Selected C5K solid-fuel rocket engine for
model verification. The results of the article are the theoretical basis for the
process of calculating the nozzle design to ensure high accuracy.