$.$ Air $($R $=286\mathrm{.}55$ J$/($kg K$),\backslash$gamma $=1\mathrm{.}4,$ Cp $=1005$ J$/($kg K$))$ is flowing through a duct Problem $6.$ Air $(R=286\mathrm{.}55\frac{J}{kgK},=1\mathrm{.}4,C_p=1005\frac{J}{kgK})$ is flowing through a duct

and reaches a cross$-$section $2$ downstream where $M_2=1,T_2=350K,$ and the stagnation pressure

at that location is $(p_0{)}_2=230$KPa. The flow is adiabatic.

$($a$)$ Find, at the cross$-$section $2,$ the stagnation temperature $(T_0{)}_2,$ static pressure $p_2,$ and static

density ${}_2($in $K,$kPa, and $k\frac{g}{m^3},$ respectively$)$;

$($b$)$ Given the inlet conditions $T_1=400K$ and $p_1=200$kPa, find in kPa

and reaches a cross$-$section $2$ downstream where M$2=1,$ T$2=350$ K$,$ and the stagnation pressure

at that location is $($p$0)2=230$ KPa. The flow is adiabatic.

$($a$)$ Find, at the cross$-$section $2,$ the stagnation temperature $($T$0)2,$ static pressure p$2,$ and static

density $\backslash$rho $2($in K$,$ kPa, and kg$/$m$3$

$,$ respectively$)$;

$($b$)$ Given the inlet conditions T$1=400$ K and p$1=200$ kPa, find M$1,($p$0)1($in kPa$),($T$0)1($in

K$),$ and $(\backslash$rho $0)1($in kg$/$m$3$

$).$