Monopropellant rocket engines use a single substance as both fuel and oxidizer. The propellant decomposes or undergoes a chemical reaction to produce thrust. Specific details, such as the heating value of the propellant, mass flow rates, and mixture ratio values, would need to be obtained from engine performance data or technical specifications for the specific monopropellant rocket engine being considered.
The propulsive efficiency is a crucial parameter in evaluating the performance of a rocket engine, indicating how well it converts propellant energy into useful thrust. Practical rocket engines often have propulsive efficiencies less than 100% due to factors like incomplete combustion, heat losses, and other inefficiencies in the propulsion system.
The propulsive efficiency () is defined by the following formula:
where,
- is the propulsive efficiency,
- is the thrust produced by the rocket engine,
- is the effective exhaust velocity of the rocket,
- ṁp is the mass flow rate of the propellants,
- is the specific impulse of the rocket engine,
- g0 is the acceleration due to gravity (approximately 9.81 m/s²).