Numerical model for hybrid rocket internal ballistic

In order to predict the propulsion characteristic of an hybrid rocket, the knowledge of its internal ballistic is essential. The purpose of this work is to write a numerical code, in FORTRAN environment, in order to predict and analyze the propulsion characteristics of the rocket itself. The thermo-fluid dynamics is performed using a zero-dimension non steady model and it is coupled with a mono-dimensional quasi-steady one. In contrast with other codes, in this, one a moving combustion surface is used, in order to better model the internal fluid-dynamic during all the simulation itself. Even though, due to the high complexity level, some approximation are used. Finally the code is validate and set, with good final results, using some real tests having GOX and HTPB as oxidizer and fuel.