The mass flow rate through a convergent nozzle is a crucial parameter in fluid dynamics, especially in the context of compressible flows like those found in rocket nozzles or jet engine exhausts.
A convergent nozzle is a geometric configuration where the cross-sectional area of the flow decreases in the direction of the flow. In the context of a rocket or jet engine, the nozzle is where high-velocity, high-temperature gases are expelled to generate thrust.
you can express the mass flow rate through a convergent nozzle in terms of known parameters like pressures, temperatures, and throat area:
where,
- ṁ is the mass flow rate of the nozzle
- P is the pressure
- R is the gas constant for the working fluid
- T is the Temperature
- A is the throat nozzle area
- M is the Mach Number
- a is the speed of sound in the medium