Thrust chamber pressure calculator

Thrust chamber pressure refers to the internal pressure within the combustion chamber of a rocket engine during operation. It is the pressure generated by the combustion of propellant inside the engine. This pressure is crucial for the propulsion system as it drives the expulsion of exhaust gases through the engine nozzle, producing the thrust necessary to propel the rocket.

Where:

  • Ë™ is the mass flow rate of propellant,
  • is the exhaust velocity of the propellant,
  • is the area of the throat or exit of the nozzle, and
  • is the pressure at the exit of the nozzle (exit pressure).

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