Question $28$

$3\mathrm{.}4$ A large bypass ratio turbofan engine $($JT$9$D engine from Pratt and Whitney, $1974)$ is described by its fan and core engine gas flow properties.

To Estimate the primary nozzle exit Mach number, is necessary to find static Temperature T$9$

Enter the T$9$ in Rankine

$\backslash$table$[[$State$,2,13,2\mathrm{.}5,19,3,4,5],[Pt(a),14\mathrm{.}7,22\mathrm{.}5,32\mathrm{.}1,22\mathrm{.}4,316,302,20\mathrm{.}9],[$Tt$(,59,130,210,130,880,1970,850],[$V$,,,,,,,]]$

$(2$ decimal$)$

SLS takeoff Thrust air fan