Question $26$

$3\mathrm{.}4$ 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 fan nozzle exit Mach number, is necessary to find static Temperature T$19$

Enter the T$19$ in Rankine

$(2$ decimal$)$

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

SLS takeoff Thrust $=43,500lbf,m($air fan$)=m19=1248lb\frac{m}{s},m($air propulsion$)=m9=247lb\frac{m}{s}$

$V19=885f\frac{t}{s}$;$,V9=1190f\frac{t}{s}$

FIGU

Source: $R_1$

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