Air at 3.4 bar, 530 K, and a Mach number of 0.4 enters a converging–diverging nozzle operating at steady state. A normal shock stands in the diverging section at a location where the Mach number is Mx=1.8. The flow is isentropic, except where the shock stands. The air behaves as an ideal gas with k=1.4

The question has some details missing. The remaining part of the question says ;

Determine

a) The stagnation temperature Tox in K

b) The stagnation pressure Pox in bar

c) The pressure Px in bar

d) The pressure py in bar

e) The stagnation pressure Poy in bar

f) The stagnation temperature Toy in K

g) If the throat area is 7.6 x 10^-4m2, and the exit plane pressure is 2.4bar, determine the mass flow rate in kg/s and the exit area in m2

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The detailed step by step calculation and appropriate substitution is carefully shown in the attached files

so then what are you asking?

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what graph

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