What's the thrust coefficient for a convergent nozzle? As you know, the Ideal Thrust Coefficient of convergent-divergent nozzle is calculated using this equation:



But what about a convegent nozzle? Is there any equation to calculate the Ideal Thrust Coefficient for a convergent nozzle?

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It’s exactly the same equation, but now the throat is at the exit. So, Ae = A*, and so the areas disappear from the last term.