There are different ways to model combustion in a rocket engine, depending on the level of detail and accuracy required. One common approach is to use a one-dimensional (1D) model that assumes the combustion chamber is a uniform cylinder and the flow is steady and axial. This simplifies the equations of mass, momentum, energy, and species conservation, and allows for easy calculation of the chamber pressure, temperature, and thrust. However, this approach ignores the effects of turbulence, heat transfer, and chemical kinetics, which can be significant in some cases.
Another approach is to use a two-dimensional (2D) or three-dimensional (3D) model that accounts for the spatial variations of the flow and the geometry of the combustion chamber and nozzle. This requires solving the Navier-Stokes equations with appropriate boundary and initial conditions, and using numerical methods to discretize and integrate them. This approach can capture more realistic features of the flow, such as shock waves, boundary layers, and recirculation zones, but it also requires more computational resources and time.