In the context of a turbojet engine, the relationship between the nozzle inlet and exhaust air velocities can be expressed using the continuity equation, which is derived from the conservation of mass.
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 Area of Nozzle Inlet in m2
- A2 is the Area of Nozzle Exhaust in m2
- V1 is the Inlet air Velocity in m/s
- V2 is the Exhaust Air Velocity in m/s