Nozzle Mass Flow Rate For a Solid Propellent Rocket Engine in Terms of Speed of Sound Calculator

In a solid propellant rocket engine, the mass flow rate is determined by the rate at which the solid propellant is burned and expelled. Unlike liquid or gaseous propellants, the mass flow rate in solid rocket engines is not easily adjustable during operation.

The mass flow rate for a solid propellant rocket engine is the rate at which the combustion gases are expelled from the rocket nozzle due to the burning of the solid propellant.

The velocity ($V$) in terms of the local speed of sound ($a$) is given by:

which gives,

where,

• ṁ is the mass flow rate of the nozzle
• $\rho$ is the density of the exhaust gases at the throat
• A is the throat nozzle area
• I_sp is the Specific Impulse of the Rocket 
• g₀ is the acceleration due to gravity (approximately 9.81 m/s² for Earth).