Rocket

Fluid Mechanics Model

Simple Momentum Equation

Titan Rocket

High I_sp requires high R (low molecular weight), high T₀.

T₀ (also flame temperature) is dictated by chemical combination of fuel/oxidizer mixture

Throat Relations

The design of the throat is critical for rocket engines. They sustain a particular mass flow rate at certain exit conditions.

The combustion chamber is idealized to have a stagnation conditions, and therefore the relations between the combustion and throat can be established by the compressible flow relations