Hot gas with a density of 0.4 kg/m 3 is exhausted from a rocket engine through a nozzle of exit diameter 1 m. If the mass flow rate through the nozzle is 370 kg/s, calculate the exhaust-gas velocity...

Hot gas with a density of 0.4 kg/m³
is exhausted from a rocket engine through a nozzle of exit diameter 1 m. If the mass flow rate through the nozzle is 370 kg/s, calculate the exhaust-gas velocity and the volumetric flow rate. If the sound speed for the gas is 550 m/s, calculate the Mach number of the exhaust-gas flow. Can the exhaust flow be considered incompressible?