Liquid bipropellant engines are rocket engines that use two liquid substances, typically a fuel and an oxidizer, as propellants. Liquid bipropellant engines are commonly used in various space missions due to their controllability and versatility. The specific details of the engine’s performance depend on the choice of propellants, combustion efficiency, and the design of the engine components.
The thrust equation for a turbojet engine using control volume analysis is expressed as:
where,
- is the thrust force,
- ṁe is the mass flow rate of exhaust gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle exit in meters per second (m/s).
- ṁ0 is the mass flow rate of inlet gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle Inlet in meters per second (m/s).
- is the Pressure at the nozzle exit in pascals (Pa).
- is the Pressure at the nozzle inlet in pascals (Pa).
- is the Area of the nozzle exit in square meters (m²).