The Saturn V was the launch vehicle used in the Apollo program, and it had multiple stages, each with its own rocket engines and nozzles. The first stage, known as the S-IC stage, was powered by five Rocketdyne F-1 engines, and the second stage, known as the S-II stage, was powered by five Rocketdyne J-2 engines. Each of these engines had its own specific characteristics, including nozzle design and performance parameters.
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).