In aircraft engine thermodynamic cycle analysis, perfectly expanded flow in the nozzle means that the static pressure in the flow at the nozzle exit is equal to
(A) the stagnation pressure at the engine inlet.
(B) the stagnation pressure at the nozzle exit.
(C) the ambient pressure at the nozzle exit.
(D) the static pressure at the nozzle inlet.

Question ID - 155379 | SaraNextGen Top Answer

In aircraft engine thermodynamic cycle analysis, perfectly expanded flow in the nozzle means that the static pressure in the flow at the nozzle exit is equal to
(A) the stagnation pressure at the engine inlet.
(B) the stagnation pressure at the nozzle exit.
(C) the ambient pressure at the nozzle exit.
(D) the static pressure at the nozzle inlet.