The jet is flying at $\backslash (\backslash$mathrm$\{$M$\}=1\mathrm{.}3\backslash ),$ where the absolute air pressure is $65$ kPa $.$ A shock is formed at the inlet of the engine. Assume isentropic flow within the engine. $\backslash ($ k$=1\mathrm{.}40\backslash )$ for air. $($Figure $1)$

Part A

Determine the Mach number of the air flow just within the engine where the diameter is $0\mathrm{.}6$ m $.$

Express your answer using three significant figures.

Part B

What is the stagnation pressure in this region?

Express your answer to three significant figures and include the appropriate units.

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Part C

What is the pressure in this region?

Express your answer to three significant figures and include the appropriate units.

$\backslash ($ p$=\backslash )$