To calculate the mass flow rate through a rocket nozzle, we can use the following general equation:
\[ \dot{m} = \rho \cdot A \cdot v \]
where:
- \(\dot{m}\) is the mass flow rate (in kg/s),
- \(\rho\) is the density of the gas (in kg/m³),
- \(A\) is the cross-sectional area of the nozzle (in m²),
- \(v\) is the velocity of the gas at the nozzle exit (in m/s).
To proceed with the calculation, we need the values for the density \(\rho\), the exit area \(A\), and the exit velocity \(v\). If you provide me with those values, I can calculate the mass flow rate for you.