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I'm no engineer, but I have a question regarding engine thrust and nozzles:

Consider a simple model rocket motor with no nozzle (i.e. just a straight cylindrical pipe with its mass flow coming out the back) that has a mass flow rate of 2kg/s. Since F = v dm/dt we would have dm/dt = 2kg/s and the exhaust velocity would most likely be quite low. Now consider the addition of a convergent-divergent nozzle. My question is this: The effect of the nozzle would be to increase the exhaust velocity, BUT due to the conservation of mass, would the mass flow rate (dm/dt) still be dm/dt = 2kg/s or close to 2kg/s?

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# Nozzles and Flow Velocity

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