Propulsive Efficiency of a Methalox Rocket Engines Calculator

The propulsive efficiency of a rocket engine that uses methane (CH₄) as fuel and liquid oxygen (O₂) as oxidizer, often referred to as a “methalox” engine, can be calculated similarly to the general case explained earlier.

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,
  • p 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).

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