Use the linear momentum rate balance (LMRB) to show that the thrust force F of a rocket engine nozzle (given Figure) is given by
F = m(Vexit/gc) + (Pexit - Pa)Aexit
and show that the absolute maximum thrust produced as Mexit → ∞ is given by
Fmax = 2cp(ΡexitAexitTos) + (Pexit - Pa)Aexit
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