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

Table 3

Design parameters of the thrust chamber.

Parameters	Symbol	Unit	Value
Total flow		kg/s	2.0
Mixing ratio		1.3
Liquid oxygen flow		kg/s	1.13
Kerosene flow		kg/s	0.87
Chamber pressure		MPa	3
Expansion ratio		5
Throat diameter		mm	36
Exit diameter		mm	80.5
Chamber diameter		mm	140
Chamber length		mm	280
Ideal thrust		N	4440.66