Dynamic Characteristics of LOX/Kerosene Variable Thrust Liquid Rocket Engine Test System Based on General Modular Simulation Method

Table 2

Thermodynamic parameters of the thrust chamber in pretest condition.

Parameters	Combustion chamber	Throat	Exit
Temperature T (K)	2010.7	1753.2	1037.4
Characteristic velocity C (m/s)	1521.5
Theoretical specific impulse (m/s)	2212.6
Expansion ratio	4.55