Velocity of Exhaust Gases At The Nozzle For a Rocket Engine Calculator

The velocity of the exhaust gases at the nozzle exit (�exit) for a rocket engine is a critical parameter that directly influences the thrust generated by the engine. The velocity can be calculated using the rocket equation, which is derived from the conservation of momentum and mass.

For a rocket engine, the nozzle is designed to accelerate the exhaust gases to high velocities, resulting in a high exit velocity. The relationship between , , , and depends on the specific design of the rocket nozzle.

The continuity equation is based on the principle of mass conservation, and Bernoulli’s equation expresses the conservation of energy.

The continuity equation is given by:

where:

  •  and  are the cross-sectional areas at the nozzle entrance and exit, respectively,
  •  and  are the velocities at the nozzle entrance and exit, respectively.

which gives

where,

  • A1 is the Cross-sectional area at the throat of the nozzle in m2 
  • A2 is the Cross-sectional area at the exit of the nozzle in m2
  • V1 is the Velocity of the exhaust gases at the throat in m/s
  • V2 is the Velocity of the exhaust gases at the nozzle exit in m/s

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