Question: With reference to Prob. 3.68, show that the thrust of a rocket engine exhausting into a vacuum is given by where Ae = exit area

With reference to Prob. 3.68, show that the thrust of a rocket engine exhausting into a vacuum is given by where Ae = exit area
Mae = exit Mach number
p0 = stagnation pressure in combustion chamber
Note that stagnation temperature does not enter into the thrust.

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