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Im wondering if an analytical proof exists that shows why maximum thrust in an ideal turbojet is obtained when the nozzle exit pressure is expanded to the ambient pressure. As in the equation..

F = mdot*(Ue-Ua) + Ae*(Pe-Pa)

my intuition tells me that we'll have to take a derivative with respect to Pe and set it to zero, but the expression gets a little complicated to perform by hand.

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# Turbojet maximum Thrust

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